Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned...
Transcript of Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned...
![Page 1: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/1.jpg)
@ Q
G_
VONKARMANCENTER
THERMAL STRAIN ANALYSIS OF
ADVANCED MANNED SPACECRAFT HEAT SHIELDS
Final Report
To
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
MANNED SPACECRAFT CENTER
HOUSTON, TEXAS
Contract NAS 9-1986
Report No. 5654-0Z FS / October 1964 / Copy No. 4
N65-30721(ACCESSION NUMBER)
o2I_<(PAGE:B)
(NAIIA CR OR "rMX OR AD NUMBER)
(THRU)
/(CODE)
GPO PRICE.1. $
CSFTI PRICE(S) $
Hard copy (HC)
Microfiche (MF)
AEIIOJET
https://ntrs.nasa.gov/search.jsp?R=19650021120 2019-12-31T12:36:17+00:00Z
![Page 2: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/2.jpg)
CONTRACT FULFII/MENT STAT_ENT
This is the final report submitted in fulfillment of the National
Aeronautics and Space _Administration Contract No. NAS_9-1986. This
report covers the period from I September 1963 to 31 August 1964.
Finite Element Analysis
Prepared by
Eo Lo Wilson
Senior Research Engineer
Finite Difference Formulation (Appendix G)
Prepared by
A, Zukerman
Head, Advanced Programs Department
Approved by:
W. T. Cox, Program Manager
Reviewed by:
Technical Specialist
Report No. 5654-02 FS
![Page 3: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/3.jpg)
I
I
I
I
I
IiI
ABSTRACT
Numerical methods and computer programs are presented for the
analysis of heat shields. The finite element technique is used to
determine stresses and displacements developed in composite axi-
symmetric solids of arbitrary geometry subjected to axisynnetrie
thermal or mechanical loads. This technique is then applied to the
development of an automated ccmputer program for the _nalysis of
axisymmetric heat shields subjected to axisymmetric thermal and pres-
sure loadings. Finallyj the numerical technique is extended to the
analysis of heat shields subjected to non-axisymmetric thermal
loading o
Several examples are presented to illustrate the application
of the method and to demonstrate its validity. FCRTRAN II card
listings and descriptions of the use of the above programs are given
in the appendices. _ _ _ _0 f
Report No. 5654-02 FS Page ii
![Page 4: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/4.jpg)
INTRODUCTION
PART I:
PART II:
TABLE OF CONTENTS
METHOD OF ANALYSIS
A. INTRODUCTIONi
B. EQU_ _UATIONS FOR AN ARBITRARY
FINITE EI_E_T
C@
De
_UILIBRIt_ EQUATIONS FCR A SYST_ (F
FINITE ELemENTS
SOLUTION OF EQU_IUM _UATIONS
E. EL_4_T STRESSES
GENIAL CCMPUT_ PROGRAR FOR THE ANALYSIS OF
ARB_Y AXISDRE_RIC STRUCTURES
A, INT_TION
B. ST_ OF TRIANGULAR
C. E_UILIBRI_M EQUATIONS FOR CCMPLETESTRUC_mZ
D. DETERMINATION OF DISPLAC_ENTS ANDSTRESSES
E. C(RPUT_ R_OGRAM
F. _MPLE
G. DISCUSSION
Page No.
I
3
3
3
8
I0
12
13
13
15
21
22
24
29
29
Report No. 5654-02 FS Page Iii
![Page 5: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/5.jpg)
PART III:
PART IV:
APPENDIX A:
APPENDIX B:
APPENDIX C:
APPENDIX D:
APPENDIX E :
APPENDIX F:
APPENDIX G:
TABLE OF CONTENTS (cont'd)
AUTOMATED PROGRAM FOR AXISYMMETPIC HEAT
SHIELDS SUBJECTED TO AXISYMMETRIC LOADS
A. INTRODUCTION
B. MESH GENERATION
C. DETERMINATION OF DISPLACEMENTS AND
STRESSES
D. COMPUTER PROGRAM
E. EXAMPLES
F. DISCUSSION
AUTOMATED PROGRAM FOR AXISYMMETRIC HEAT
SHIELDS SUBJECTED TO NON-AXISYMMETRIC LOADS
A.
B.
C,
D.
E.
INTRODUCTION
THEORY FOR TEE ANALYSIS OF ANAXISYMMETRIC
BODY SUBJECTED TO NON-AXISYNMETRIC LOADS
COMPUTER PROGRAM
EXAMPLES
DISCUSSION
SOLUTION OF EQUILIBRIUMEQUATIONS
MATRIX FORMULATION OF THE LEAST SQUARES
CURVE-FIT PROCEDURE
MATHEMATICAL MODEL FOR SANDWICH SHELL
PROGRAM LISTING-ARBITRARYAXISYMMETRIC
PROGRAM LISTING-AXISYMMETRIC HEAT SHIELDS
PROGRAM LISTING-NON-AXISYMMETRIC HEAT SHIELDS
SUMMARY OF EFFORTS TO SOLVE THE THERMAL STRAIN
PROBLEM BY THE OVER-RELAXATION AND DIRECT
INTEGRATION OF FINITE-DIFFERENCE FORMULATION
Page No.
32
32
33
35
36
40
43
45
45
45
55
59
65
AI
B1
C1
J_J__
E1
F1
G1
Report No. 5654-02 FS Page iv
![Page 6: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/6.jpg)
LIST OF SYMBOLS
aj,bj,ak,b k = Element Dimensions
E = Modulus of Elasticity
u = Displacement in the r Direction
v = Displacement in the 9 Direction
w = Displacement in the z Direction
- Thermal Coefficient of Expansion
B " Over-Relaxation Factor
V = Shear Strain
- Strain in the Radial, Circumferential and Longitudinal •erj9 ;z Direction
v = Poisson's Ratio
= Stress in the Radial, Circumferential and Longitudinal_r_8,z Direction
- Shearing Stress
[ IT . Matrix Transpose
[a] - Displacement Transformation Matrix
[C] - Matrix of Elastic Coefficients
_ - Displacement Transformation Matrix - Harmonic n
_] = Matrix of Element Corner Forces
[u] = Matrix of Element Corner Displacements
[k] = Element Stiffness Matrix
r_l = 1_nr1.1Pn_+. Di.placementsL_ ........
i
[R]- - Nodal Point Loads
_K_ = Stiffness Matrix for Complete Structure
Report No. 5654-02 FS Page v
![Page 7: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/7.jpg)
INTRODUCTION
The purpose of this investigation is the development of methods
of analysis and digital computer programs to aid in establishing the
structural integrity of manned spacecraft _heat shields. The results of
the analysis which are presented in this report indicate only the cap-
abilities of the computer programs and do not necessarily represent the
behavior of a specific heat shield. The final evaluation of the structural
capability of a heat shield must be based on a certain amount of engineer-
ing Judgement, in connection with the use of the computer programs.
In this investigation the finite element method is used to de-
termine stresses and displacements developed in solids of revolution.
First, a numerical procedure and a digital computer program are develop-
ed for the analysis of composite axisymmetric solids of arbitrary
geometry subjected to axisymmetric thermal or mechanical loads. Second,
this program is specialized to the analysis of axisymmetric heat shields.
Finally, the same numerical technique is extended to the analysis of
heat shields subjected to non-axlsymmetric thermal loading. A descriptioni
of the method of analysis and the use of the above computer programs is
presented. In addition, FCRTRAN II listings of the above programs are
incorporated in this report.
Report No. 5654m02 FS Page i
![Page 8: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/8.jpg)
During the initial phases of this contract, finite difference
techniques were used to solve the governing differential equations for
displacements of the system. However, considerable difficulty was en-
countered in the solution of the resulting set of linear equations. An
iterative approach, coupled with over-relaxation techniques, resulted in
inadequately convergent displacements. The direct solution technique
gave a matrix for the set of simultaneous equations which was ill-
conditioned. An additional difficulty of the finite difference technique
was encountered in satisfying the boundary conditions at the edge of the
heat shield. The finite element approach proved more practical and more
versatile; therefore, the finite difference method was discontinued. A
complete description of this initial investigation is given in Appendix
G.
Report No. 5654-02 FS Page 2
![Page 9: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/9.jpg)
PART I_ METHOD OF ANALYSIS
A. INTRODUCTION
The "finite element method" is a general methQd of structural
analysis in which a continuous structure is replaced by a finite number
of elements interconnected at a finite number of nodal points -- (such an
idealization is inherent in the conventional analysis of frsmes and trusses).
In this investigation the finite element method is applied to the determina-
tion of stresses and displacements developed in axisymmetric elastic
structures of arbitrary geametry and material properties which are sub-
Jected to thermal and mechanical loads.
An assemblage of different types of axisymmetric elements is used
to represent the continuous structure. Approximations are made on the
displaceme_s within each element of the system. Based on these ap-
praximations, equilibrium equations are developed for all elements.
From "direct stiffness techniquesU, the equilibrium equations p in terms
of unknown nodal point displacements, are developed at each nodal point.
A solution of this set of equations constitutes a solution to the finite
element system.
B. _UILIBRIUM EQUATIONS FOR AN ARBITRARY FINITE EL_4ENT
I. Strain-Displacement Relationship
The first step in the determination of the stiffness (corner
forces in terms of corner displacements and temperature changes), of a
Report No. 5654-02 FS Page 3
![Page 10: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/10.jpg)
finite element is to assumea solution for the displacement field within
the element. It is desirable that this assumed displacement field
satisfies compatibility between other elements in the system. Based on
this solution for the displacements within the eleaent, it is possible
to develop an expression for the strains at any point within the element
in terms of the nodal points (corner) displacements. This expression in
matrix form is
[,] - [_3[-]
where [,][-][-]
(i.i)
i_ a column matrix of the M components of strain
is a column matrix of the N nodal point displacements
is an M x N strain-displacement transformation matrix -
this matrix may be a function of space
Stress-Strain Relationshi p
For an elastic material, the stresses at any point within
the element are expressed in terms of the corresponding strains by the
elastic stress-strain relationship. Or, in matrix form
[_]-[_] [.] ÷[,] c_.,_
Report No. 5654-02 FS Page 4
![Page 11: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/11.jpg)
where _] s a colmnnmatrix of the M components of stress
c] is a column matrix of the M components of strain
_] s a column matrix of the M components of thermal stress
[C] is an M_M matrix of material property coefficients
The size (M) of these matrices will depend on the type of element
being considered. The coefficients of matrices [0] and IT] will depend
[o]on material properties. Since is completely arbitrary 9 anisotropic
materials can be handled. Also_ each element in the system may have
different properties; therefore_ ccmposite structures are readily represent-
ed by the finite element idealization.
3. Internal Work
The internal work, or strain energy, which is associated with
an infinitesimal volume element dV within the finite element is Eiven by
IdNI " _ (el_l + ¢2 _2 "'"" + eM _M ) dV
or in matrix form
T
dNI = ,_[e] [o'] dV
The substitution of Equation (1.2) into Equation (1.3) yields
(1.3)
Report No. 5654-02 FS Page 5
![Page 12: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/12.jpg)
Equation (I.I) may be written in transposed form as
[]' [u]- (1.5)
After Equations
internal work is given by
dWl= _ a C dV + I [u [I" dV2
(I.I) and (1.5) are substituted into Equation (1.4), the
(1.6)
The total strain energy stored within the element is found by
integrating Equation _1.6) over the Volume of the finite element. Or
wi2
@ E_-terrml WorkI I,
The work supplied externally at the nodal points of the
finite element is given by
w_ = _ uI sI + u2 s2 .....,.....+ v_
or in matrix form
w_-_ s
where[u_T
(1.8)
is a row matrix of the N nodal point displacements
is a Column matrix of the N corresponding nodal point forces
Report No. 5654-02 FS Page 6
![Page 13: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/13.jpg)
5. Energy Balance
The external work, Equation (1.8), is equated to the internal
work, Equation (1.7), yielding
(1.9)
where the element stiffness matrix
dV (1.zo)
and the .thermal load matrix
Equation (1.9).represents an energy balance (scalar equation) for a single
nodal point displacement pattern. If the final displacements [U_ are
assumed to be composed of N separate displacement patte_-ns_[_ij ] J - 1,...N,
[]ing sets of f=ces, B_ S " l, .... _, Equation(!.9) m_ be .ritten as
[<[,]. [<[,] [o]'[,.]T m
To eliminate the term [_] the displacement patterns must be
Teselected in such a manner as to assure an inverse of [_] An acceptable
matrix is a diagonal matrix of the'final displacement, or
r-_ T r.q r,,___qLuJ " L=J " L _J (!;l j)
Report No. 5654-02 FS Page 7
![Page 14: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/14.jpg)
Equation (1.12) is now premultiplied by _J" I yielding
r "-i
where [lJ is a diagonal unit matrix.
Since only linear systems are consideredj the N displacement patterns
may be superimposed. Or
Is] - [_][_]• [,.] (_._
Since
J'l,...N
Equation (i.15) expresses nodal point forces in terms of nodal point
displacements and temperature changes Within the element.
C@ _U._ BQUATIONS FOR A S¥ST_ OF I_-NITE _L_TS
The first s_ep in the procedure is to express all el_nent forces in
terms of sxternal nodal point displacements far each element in the
system. This is accomplished by expanding Equation (I.14) in terms of
the N possible nodal point displacements; this will yield H matrix equations
of the form
[_] . [_][,]+ [_] , +_,....where M is the total number of elements in %he system.
(1.16)
Report No. 5654-02 FS Page 8
![Page 15: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/15.jpg)
The matrix [km] is termed the complete stiffness of element m and involves
only terms which are associated with the displacements of the connecting
nodal points. Consequently, the majority of the coefficients of this
matrix equation are zero. The matrix [r] contains all possible nodal point
displacements of the complete finite element system. The matrix ISm] is a
column matrix containing the forces acting on element m in the direction
of the nodal point displacements [r]. The thermal load matrix [Lm] and the
element stiffness matrix [km_ are given by Equations (I.Ii) and (I.IO);
however, the order (size) of these matrices has now been expanded to
correspond with the total number Of nodal point displacements.
In order to satisfy equilibrium of all nodal points, the sum of the
internal element fOrCes must be equal to the external nodal point loads,
Or
m=Ij.. _M
of Equation (1.16) into Equation (1.17)yields
[,]. .[e][,]. Zm=lj., _M re=I,...M
is the eKternal_y applied nodal point loads. The substitution
(1.18)
Report No. 5654 o2 FS Page 9
![Page 16: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/16.jpg)
or rewritten in the following form:
M "[_I__] _ll_where
[.]-[P]- _ [,."]m=lj,, ,M
(1.20)
m-i 9,.,M
Equation (i.19)_ which is an equilibrium relationship between external
loads and internal foroes_ represents a syste_ of N linear equations in
terms of N unknown displacements.
D. SOLUTION OF _UILIBRIUM _QUATIONS
Equation (1.19) represents the relationship between all nodal point
forces and all nodal point displacements. Mixed boundary conditions are
considered by rewriting Equation (1.19) in the following partitioned form:
m !
I
_a I_
(1.22)
Report No. 5654-02 FS Page i0
![Page 17: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/17.jpg)
where E_2
Ira]
= the specified nodal point forces
= the unknown nodal point forces
= the unknown nodal point displacements
= the specified nodal point displacements
Equation (1.22) may be expressed in terms of two separate equations, or
[,_]. [_,][_j • [_] [_] c_Equation (1.23) is rewritten in the following reduced form:
(l.25)
where the modified load vector, JR2 is given by
In Part II of this report_ the Gauss-Seidel iterative technique
is used to solve _uation (1.25) for the unknown nodal point displacements
Ira]. direct solution which is used in theAppendix A gives approach&
automated computer programs for the thermal stress analysis of heat shields,
Parts I_Z and IV of this report.
Report No. 5654-02 FS Page 11
![Page 18: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/18.jpg)
E. EL_ENT STRESSES
After the nodal point displacements have been determined, the strains
within an_ elsment in the system are evaluated by the direct application
of Equation (i.I). The corresponding stresses are calculated from the
stress-strain relationship, Equation (1.2).
Report No. 5654-02 FS Page 12
![Page 19: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/19.jpg)
PART II GENERAL C(]MPUT_R PROGRAM FOR THE ANALYSIS
OF .l_trrtt_Y AXISgNN_IC STRUCTURESi ii ii
A. INTRODUCTION
The stress analysis of an axisymmetric structure of arbitrary shape,
subjected to thermal and mechanical loads is of considerable practical
interest. Although the governing differential equations have been known
for many years, closed form solutions have been obtained for only a
limited number of structures. Thus, the investigator must often rely on
experimental or nt_aerical procedures to solve this probl_,.
Experimental methods, such as Photoelasticity, have proven to be
versatile too_s in t_e analysis of many axis_etric structures. However,
for structures composed of several different materials or structures with
thermal leading, this approach is limitedo
The finite _difference method, Which involves the replacement of
the derivatives in the differential equations and boundary conditions with
difference equations _ has been the most popular of the numerical techniques.
However, for structures of composite materials and of arbitrary geometryj
the procedure is difficult to app_v.
In this section the finite element method is used to determine the
stresses and displacements developed within arbitraryj elastic solids of
revolution subjected to thermal or mechanlcal axisy_aetric loads. The
Report No. 5654-02 FS Page 13
![Page 20: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/20.jpg)
GeACTUAL RING
I II I
b. TRIANGULAR ELEMENT APPROXIMATION
FIG. 2.1 THE FINITE ELEMENT IDEALIZATION
Report No, 5654,-02 FS Page 14
![Page 21: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/21.jpg)
finite element approach replaces the continuous structure with a system
of triangular rings interconnected at a finite number of nodal points
(Joints). Loads acting on the structure are replaced by statically equi-
valent concentrated forces acting at the nodal points of the finite
element system. Figure 2.1 illustrates a finite element idealization of a
typical axisymmetric solid.
B. STreSS OF
i@ Strain-Displacement Relationship
Cont_uity between elements of the system is maintained by
requiring that within each element relines initially straight remain
straight in their displaced position". This linear displacement field,
which is illustrated in Figure 2.2, is defined in terms of u(r,z) and
L 'FID. 2.2 ASSUMED DISPLAC_ENT PATTerN
Report No. 5654_02 FS Page 15
![Page 22: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/22.jpg)
w(r,z) by equations of the following form:
u(r_z) = CI + C2 r + C3 z (2.1a)
_r_z) - C4 + C5 r + C6 Z (2.1b)
If Equations (2.1a) and (2.1b) are evaluated at the three corners i, J, k
of the triangle_ the following see of equations is obtaineds
ui
U
i
0
ri zi 0 0
0 0 I
I rj zj 0
0 o o 1
z rk "k o
o 0 o I
b
ri zi
o o
rj zj
0 0
C1
C 2
C3
C_
C5
C6
(2.2)
By solving the system of Equations (2.2) for the constants Ci,....,C6,
they are expressed in terms of corner displacements. The strains i_ the
rz-plane are obtained from the assumed displacement field by considering
the basic definition of strain.
Report No. 5654-02 FS Page 16
![Page 23: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/23.jpg)
_U
;r " _ = C2 (2.3a)
= _w = C6 (2.3b)
_rz = _'z_u+ _w = C3 + C5(2.3¢)
At any point within the element the tangential strain
=e-(r'=) . u(r,z)r
The average tangential strain is found by averaging the strains at the
Vertices of the triangle,
(2.3d)
After el_i_a_ing the constants c between Zquations (2.2) and (2.3),n
the average eleme_ strains are expressed in terms of corner displacements
by the following matrix equation:
Report No. 565_-02 FS Page 17
#
![Page 24: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/24.jpg)
¢r
cz
cg
_rz
II i
bj% o bk o %
0 ak-a j 0 -ak 0
X 0 _ 0
0
aj
0
ak-a j bj_o k -ak _ aj -bj
ui
w i
uj
wJI
or in symbolic form
[.] - [,,lE-Iwhere
aj = rj - ri
ak = rk-r i
bj = zj - zi
x = aj_-_bj
The geometry of a typical triangle is illustrated in Figure 2.3
Report No. 5654=02 FS Page 18
![Page 25: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/25.jpg)
k
rk
rj J
ri • i
TFD_. 2°3 _ENT DIM_SI_
2, Stress-Strain Relationshipm.
One important advantage of the finite element approach is
that structures with anisotropic materials can be treated. In generalj
the stress-Strain relationship is of the form
%
_Z
_9
_rs
cn c_ cI_ c_ "r
C21 C22 C23 C24 Cz
c31 c32 c33 cj4 eo
c41 c_ c_ c_4 Vrz
_Z
_9
_rz. •
(2.5a)
Report No. 5654-02 FS Page 19
![Page 26: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/26.jpg)
P _
.h_e L'J is the_tr_ of thez_al stresses for a given temperature C_eo
For example, the stress-strain relationship for an isotropic material is
given by
_r
z
! ee
E
(1÷_,)0.-2v)
-1-,_
1)
0
v 0
l-v u 0
l-v 0
o o I-2_2
F ¢ - Tr
Z
+
ce
7rz _
(2.6)
'1"
where 7 = AT (2.7 )
3. Element Stiffness
i
The stiffness of a typical triangular ring, which is an
expressioh for corner forces in terms of corner displacements_ is given
by Eql. (I_I0) as
Ek]-I [a]T[°][a]dV
And the thermal load matrix is given by Eq. (i.ii) as
EL_ = _I Ea_ T E_ dV
Since the coefficients in matrices Ca_ and ECI are assumed not to be
a function of space the above equations reduce to
Report No. 5654--02 FS Page 20
![Page 27: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/27.jpg)
(2.8)
(2.9)
If a one-radian segment is considered, an approximate expression for
the volume of a triangular ring segment is
V=_A
m
where r is the average radius given by
r = (r i + rj * rk)/3
and A is the cross-sectional area given by
A - (ajbk - akbj)/2
From Eq. ii,15) the six corner forces acting at the vertices of a
one-radian triangular segment is given in terms of the six corner
displacenents and the temperature change within the element by
[.].
(2 .ii)
(2.12)
(2.13)
C. EQUIW,IBRIUM EQUATIONS FOR COMPLETE STRUCTURE
The equilibrium of the complete system of triangular rings, which
is aft expression for nodal point loads in terms of nodal point
displacements, is given by the following matrix equation:
.[R] .= [K] [r]
Report No. 565_-o2 FS Page 21
![Page 28: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/28.jpg)
F7The stiffness matrix LK_ and the load matrix LR ] are determined
by
"direct stiffness" techniques as indicated in the previous section,
(1.20) and (1.21). In addition to the thermsl loads, the [R]Eqs.
matrix is composed of concentrated external forces acting at the nodal
points of the system. Hence, pressures acting on the boundary of a
segment of the structure are replaced by statically equivalent forces
acting at the nodal points.
Mixed boundary conditions are considered by a simple transformation
of Eq. (2.14); Eqs. (1.22) to (1.26) give the details of this
modification.
D@ DETE_IINATION OF DISPLAC_NT AND STRESSES
Equation (2.14) is solved for the unknown nodal point displacements
by the applicati_ of the well-known Gauss-Seidel iterative procedure.
This involves the repeated calculation of new displacements from the
equation
where n
.." Kniri "_ ani i
i=l, •.n-I i=n+l, •.n
(2.15)
is the number of the unknown and s is the cycle of iteration.
The,only modification of the procedure introduced in this analysis
is the simultaneous application of Equation (2.15) to both components
Report No. 5654_02 FS Page 22
![Page 29: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/29.jpg)
of displacements at each nodal point.
vectors with r and z components.
Therefore, rn and Rn become
The rate of convergence of the Gauss-Seidel procedure can be
greatly increased by the use of an over-relaxation factor. This factor
.'(s)is appliedby first calculating the change in displacement _rn of
nodal point n and then determining the new displacement from the
following equation-
r(S) _(s-l) SAt(s)n m _n +
where B is the over-relaxation factor.
(2.16}
The solution of an over-relaxation factor, which gives the best
convergence, depends on the characteristics of the particular problem.
However, experience b_s indicated that for most structures, the op%iimm
ever.relaxation factor is between 1.8 and 1.95.
Since only the non-zero terms in Equation (2.14) are developed and
stored by the computer program, a solution of several hundred eqna%Iona
is possible, thereby making it possible to solve large finite element
systems.
For each element the average strains are calculated directly from'
the nodal _oint displacements by the application of Equation (204). The
Report No. 5654-02 FS Page 23
![Page 30: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/30.jpg)
average element stresses are then determined from the stress-strain
relationship for the element, Equation (2.5). In addition, at each
nodal point, stresses are computedby averaging the stresses in all
elements attached to the point.
E. COMPUTERPROGRAM
The complete analysis of an axisymmetric solid by the finite element
method involves three separate phases, First, the structure must be
idealimed by a system of triangular rings. Second, this system iS sOlved
for displacements and stresses from given nodal point forces. Third, the
displacements and stresses are presented graphically for further evaluation
and utilization.
The Selection of the system of finite elements for a particular
problem is complet@ly arbitrary; therefore, axisymmetric structures,
composed _f many _terac_g components, of practically any shape may
be han_ed, By nu_ering all elements and nodal points, in a convenient
manner, the system can be defined in the form of three numerical arrays -
nodal point arrayj element array and boundary point array. The nodal
point array contains the coordinates and the loads or displacements that
are associated with each nodal point of the system. The element array
contains, for each element in the system, the location of the element
(the ÷.hre_ nodal noint numbers defining the corners of the element and
other possible parameters which are associated with the element (i.e.j
Report NO. 5654-02 FS Page 24
![Page 31: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/31.jpg)
elastic constants, density and temperature changes). The boundary array
indicates the type of restraint thst exists at boundary nodal points.
These three arrays, along with somebasic control information,
constitute the numerical input for the digital computer program. The
program itself performs three major tasks in the analysis of the finite
el_nt System of triangular rings. First, the equilibrium equations for
th_ System are formedfrom the basic numerical description of the system.s
Second_ this set Qf equations is solved for the nodal point displacements.
Third_ the internal stresses are determined from these displacements.
I. Input Information
To define the system of finite elements, all nodal points
and elements are numbered as illustrated in Figure 2.4. Based on this
n_be#tng System, the following sequenc e of punched cards constitutes
the input to the computer program.
a. (72H)
Columns 2 to 72 of this card contain information to
be printed with results
CONTm CARD (614,2 12.5)
Columns 1 - 4 Number of elements
5- 8 Number of nodal _points
9 - 12 Number of restrained boundary _oints
13 16 Cycle interval ...... _-_ ^_ ""_'°_o'_,'o,_forces
Report No. 565h-O2 _ Page 25
![Page 32: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/32.jpg)
Z
R- ORDI NATE
N
R_-LOAD
Z- LOAD
NODAL POINT NUMBER
2I
ELEMENT NUMBER
FIG. 2.4 NUMBERING SYSTEMAND NODAL POINTS
FOR ELEMENTS
Report No. 5654-02 FS Page 26
![Page 33: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/33.jpg)
C@
d@
17-20 Cycle interval for print of results
21-24 Maximum number of c/Ices problem may
run
25-36 Convergence limit for unbalanced forces
37-48 Over-relaxation factor
ELEMENT ARRAY - i card per element (414, 4E12.4,
F8.4)
Colu.m 1-4
5-8
9-12
13-16
17-28
29-40
-Sz
53-64
65-72
Element Number
Nodal point number i
Nodal point number J _ in counter-J
clockwise orderNodal point number k
Modulus Of elasticity E
Density of element 0
Poisson 's. ratio
Coefficient of thermal expansion
Temperature change within element. AT
NOmL POINT ARRAY - 1 card per nodal point (114,::'
Column 1-4
5-12
13-20
21-38
29-36
37-48
4F8.1,2m.2.8) -
Nodal point number
R-ordinate
Z-ordinate
R-loadTotal force acting
Z-load _ radian segment.
R-displacement
on a one
49-60 Z-displa cement
On free nodal points, the displacements are initial guesses for the
iterative solution. On restrained nodal points, the input displacements
at6 %,_ 3p_'ified fgDa_ displacements of the nodal point.
Report No. 5654-02 FS Page 27
![Page 34: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/34.jpg)
e. BOUNDARYPOINTARRAY- I card per restrained nodal
point (214,
Columns 1-4 Nodal point numbers
5-8 0 if point is fixed in both directions
1 if point is fixed in the R-direction
2 if point is free to move along a line
of slope S
9-16 Slope S (type 2 points only)
output o ation
The following information is generated and printed by th_
2.
co_q_t er program:
a.
b'
Ced.
Input DataNOdal Point Di-splacement
Average Element StressesAverage Nodal Point stresses
3 • Timing
For the IBM 7094 the computational time required by the
program is approximately 0.004 x n x m seconds, where n equals the
number of nodal points and m equals the number of cycles of iteration.
Depending on the desired degree of convergence, it may be necessary to
extend the iteration process.
4. Pro a m List ,
A card listing of the FORTRAN II source deck for the general
axisy_ric program!s included _ Appendix D of this rApnrt. This
:program is compiled for a maximum size of 550 elements or 340 nodal points.
Report No. 5654-02 FS Page 28
![Page 35: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/35.jpg)
F, EXAHPLE
An infinite cylinder subjected to steady state temperature
distribution, for which an exact solution is known, is selected as a
means of verifying the finite element analysis. A finite element
idealization of a section of the cylinder is shown in Figure 2.5a. The
temperature distribution which is assumed constant within each element,
is plotted in Figure 2,5b. The hoop stresses are compared with the exact
solution in Figure 2.5c. Considering the coarse mesh, agreement with the
exact solution is very good except at the two boundary points. This
discrepancy is due to _he fact that nodal point stresses are calculated
by averaging the stresses in the attached elements. Therefore, the
boundary nodal point stress reflects the average stress in the elements
near the boundary.
In general, good boundary stresses are obtained by plotting the
interior stresses and extrapolating to the boundary. This type of
engineering judgement is always necessary in evaluating results from a
finite element analysis.
G. DISCUSSION
This section demonstrates the application of the finite element
technique to the stress analysis of structures of revolution. The approach
reduces the stress anaiysi_ to o- __._-_-_pro__-_1_A..... In order to use the
Report No. 565_-02 YS Page 29
![Page 36: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/36.jpg)
6 7 8 9 I0 II 12* ' ' RADIUS i
a. FINITE ELEMENT IDEALIZATION- INFINITE CYLINDER
i- =°"
I-"
Radius
b. TEMPERATURE DISTRIBUTION
----- EXACT SOLUTION
Rodiu'-s0"r'
c. HOOP STRESSE_,
FIG. 2.5 ANALYSIS OF INFINITE CYLINDER
Report No. 5654-02 FS Page 30
![Page 37: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/37.jpg)
II
II
program, it is only necessary to select an element idealization of the
structure and to supply the computer program with data that numerically
define the system of elements. Therefore, the program may be used as a
tool in design since changes in materials and geometry of the structures
may involve only minor changes in the input data.
In addition, the program may be extended to include the effects
of anisotroplc materials. For this casej the input to the program must
be expanded to include the general elastic constants defined by Eq. (2.5).
For the analysis of a specific type of structure, this program can
be further automated by incorporating a mesh generator and the calcuiation
of temperature-dependent material properties, In the next section of
this report the program is specialized to the thermal stress analysis
of axisymmetric heat shields for manned spacecraft.
Report No. 5654r02 FS Page 31
![Page 38: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/38.jpg)
PART III AUTOMATED PROGRAM FOR AXISYMMETRIC HEAT
SHIELDS SUBJECTED TO AXlSYMMETRIC LOADS
A. INTRODUCTION
The general computer program for the analysis of arbitrary
axisymmetric structure, as given in the previous section, can be applied
to the thermal stress analysis of heat shields. However, the use of this
program for such a complex structure involves a large amount of detail
work to select the finite element idealization and to prepare the computer
input. In addition, the convergence of the Gauss-Seidel iteration procedure
is slow for this type of structure and a solution may require an excessive
amount of computer time.
By restricting the general computer program to the analysis of heat
shields and by automating the input, a considerably more efficient program
can be developed. The geometry of the heat shield is supplied to the
computer program in the form of R and Z coordinates and ablator thickness
at various points along the bond line. The required triangular mesh and
the temperature at the grid points are generated within the program.
Material properties at various temperatures are supplied in tabular form
and the program automatically develops analytical expressions for the
material properties by least square techniques. The flanges of the sand-
wich shell are idealized by special conical shell elements and the honey-
comb core material is treated as a separate material. This approach
Report No. 5654-02 FS Page 32
![Page 39: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/39.jpg)
eliminates the need for the establishing of a pseudo-thickness for the
composite sandwich shell. The solution of the equilibrium equations,
which was previously obtained by an iterative approach is accomplished
by a direct solution procedure. Because of their significance, stresses
within the sandwich plates and at the bond line are included in the
computer outputs
B. MESH G_ERATION
A typical finite element idealization of the cross-section of a
heat shield is shown in Figure 3.1. The basic element in this system is
a quadrilateral ring, which in turn is composed of two triangular rings
(Part II). In this particular case, the sandwich shell is represented by
the first two rows of elements and the ablator is idealized by four rows
of elements; there are 30points in themeridional direction. The specific
mesh configuration is a variable which is supplied to the computer program.
In general, the geometry of the shell is given by the R-Z coordinates
of the points at the bond line between the sandwich shell and the ablator.
The points on lines perpendicular to the bond line inside the variable
thickness ablator and inside the constant thickness sandwich shell are
generated automatically within the program. Thin shellcone elements are
used to represent the face plates of the sandwich shell.
From a given temperature distribution at the bond line, the grid point
temperatures are assumed td be constant within the shell and are assumed
to vary parabolicallywithinthe ablator.
Report No. 5654-02 FS Page 33
![Page 40: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/40.jpg)
Report No. 5654.-02FS Page 34
![Page 41: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/41.jpg)
II
I
|,
C. DETERMINATION OF DISPLACEMENTS AND STRESSES
Based on temperature dependent material properties, the equilibrium
relationship for each quadrilateral ring is developed and then combined to
form the equilibrium equations of the complete system of rings. Similarly
the stiffness properties of the face plates of the sandwich shell are
incorporated into the equilibrium of the system. The axisymmetric
behavior of a typical conical element is a special case of the non-
axisymmetric behavior which is given in Appendix C. The unknowns in
this set of equations are the vertical and radial displacements at each
grid point in the system. The satisfying of possible displacement boundary
conditions requires that these equations be modified as indicated by
Equation (1.25). Because of the physical characteristics of the heat
shield, the resulting set of equations is in band form. Appendix A
indicates the necessary modification to restrict the standard Gaussian
elimination procedure to the solution of symmetrical band systems. This
approach results in a definite increase in capacity and speed over the
iterative technique and it eliminates the problem of convergence.
After the equilibrium equations are solved for the unknown grid
point displacements, the average stresses within each triangular ring
are calculated as indicated in Part II of this report. Based on the
stresses in the two triangular rings, average quadrilateral stresses are
calculated for each quadrilateral ring in the system.
Report No. 5654-02 FS Page 35
![Page 42: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/42.jpg)
D. COMPI_F_PROGRAM
The first step in the stress analysis of an axisymmetric heat
shield is to select points at the bond line at regular intervals along
the meridian of the shield. A quadrilateral mesh is automatically
developed by the program from the R and Z coordinates. The material
properties vs temperature for the ablator and bond are supplied to
the computer in tabular form and the computer program automatically
determines analytical expressions for the properties by a least square
procedure (see Appendix B for details of method). Finally, the grid
points which are to be restrained and the external loads which act at
grid points are specified.
I. Input Information
The following sequence of punched cards numerically defines
the heat shield to be analyzed.
a.
b@
FIRST CARD - (72H)
Columns i to 72 of this card contains information
to be printed with results
SECOND CARD - (615, 2F10.2)
Columns I - 5 Number of points along the shield - NMAX
6 - iO Number of points thru the thickness-MMAX
I_ _ !_ T.n,,'.m+.Innn_"h_nd llnA - MB
16 - 20 Number of material property cards - NP
Report No. 5654-02 FS Page 36
![Page 43: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/43.jpg)
I
I
r
b
r
L
I
I
I
I
I
CQ
dt
ea
21 - 25 Number of points with radial and
axial loads - NL
26 - 30 Number of additional boundary
conditions - NB
31 - 40 Surface temperature of ablator
41 - 50 Zero stress temperature
THIRD CARD - Properties of Sandwich Core (4FI0_2)
Oolumns i - iO Modulus of elasticity
11 - 20 Poisson's ratio
21 - 30 Coefficient of thermal expansion
31 - 40 Thickness of core
FOI_TH CARD - Properties of Sandwich Face Plates
(_12.2)
Coltmms i - i0 Modulus of elasticity
Ii - 20 Poisson's ratio
21 - 30 Coefficient of thermal expansion
31 - 40 Thickness of single face plate
GEOMETRY CARDS - (hFlO,2)
One card per point along shield, in order from axis
of symmetry to edge (NMAX cards).
Columns I - IO R-ordinate at bond line
Ii - 20 Z-ordinate at bond line
21 - 30 Temperature at bond line
31 - 40 Normal thickness of ablator
Report No. 5654-02 FS Page 37
![Page 44: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/44.jpg)
f. MATERIALPROPERTYCARDS - (4FIO. 2)
One card for each temperature (NP cards)
Columns i - IO Temperature
Ii _ 20 Modulus of elasticity of ablativemateris i
21 - 30 Modulus of elasticity of bond material
31 - 410 Coefficient of thermal expansion forablator and bond materials
g. LOAD CARDS - (2]5, 2FI0.2)
One card for each point which is loaded externally
(NL cards). N and M specify the grid location of the point.
Columns I - 5 N(Meridional direction)
6 - IO M (Thickness direction)
II - 20 Radial Load,
21 30 Axial LoadTotal load acting on
one radian segment
h. BOUNDARY OONDITION CARDS - (315)
One card for each point which is restrained(NB cards).
N and M specify the grid location of the point.
Columns 1 - 5 N (Meridional direction)
6 _ i0 M (Thickness direction)
II - 15 Boundary Code
Code = I point fixed in R-direction
Code = 2 point fixed in Z-direction
Code = 3 point fixed in both the Rand Z-directions
Report No. 5654.-02 FS Page 38
![Page 45: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/45.jpg)
@ Output Information
The following information is generated and printed by the
computer program:
a@
b.
C@
d.
ee
f.
g.
Input data
Least squares evaluation of the temperature dependent
material property data
Coordinates and temperatures of all grid points
R and Z displacement at all grid points
Average stresses in quadrilateral rings
Stresses in sandwich face plates
Stresses in bond layer
3. T ing
The computer time required by this program for an axi-
symmetric analysis of a heat shield is approximately
time --A + B'(NMAX)'(MMAX) 2 (seconds)
The constants A and B depend on the specific computer system
which is employed. For the IBM 7094 A=20 and B=O.02, and the time required
for a 30 x 7 mesh is 50 seconds.
4. Program Listing
A card listing of the FORTRAN II source deck for the
automated computer program for the sxisymmetric stress analysis of heat
shields is Riven in Appendix E. The program is compiled for a maximum
Report No. 5654-02 FS Page 39
![Page 46: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/46.jpg)
grid size of 40 points in the meridional direction and i0 points through
the thickness. Material properties can be specified by a maximum of
50 cards.
E. EXAMPLES
Several axisymmetric analyses of a heat shield were conducted to
evaluate the significance of the various structural parameters. A
typical finite element idealization of the heat shield is shown in
Figure 3.1.
I. Effect of Mesh Size
The first example was selected to illustrate the effect
of mesh size on the accuracy of the displacements and stresses developed
within the heat shield. For a structure fixed at the edge, typical re-
sults of two analyses with different meshes are shown in Figure 3.2. This
example illustrates that two layers of elements in the sandwich shell are
adequate for the purposes of predicting stresses. It is of interest to
note that the stress distribution varies linearly within the sandwich
shell, thereby confirming the assumption made in thin shell theory. The
displacements for these two analyses differed by less than one percent.
2. Effect of Ablator Thickness on Stress Distribution
Figure 3.3 shows typical results of three analyses of heat
shields with different ablator thicknesses. In general, the magnitude of
Report No. 5654-02 FS Page 40
![Page 47: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/47.jpg)
I - 200
I-150
emm
Q.
I
elq)I,..
4=-
(t)
- I00
Q.00
-50
0
• Four-Layers in ShellFour Layers in Ablotor
x Two Layers in Shell
Six Layers in Ablotor
m
Sandwich Shellr
f Bond
< Ablator _ [
Line
Fig.3.2 Effect of Mesh Size on Stress
Report No, 5654-02 FS
Distribution
Page
![Page 48: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/48.jpg)
I -200
I i=,i'_II o_
i To-5o
O Normal Thickness
OnS,-Half Normal Thickness
m One-Fourth Normal Thickness
m
_s
Sandwich Shell _! : Ab,lator_,
Fig. 3.3
Report No.
Effect of Thickness of Ablator on Stress Distribution
5654-02 FS Page 42
![Page 49: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/49.jpg)
the nmximum stresses in the ablator were in good agreement. This example
illustrates that the thickness of the ablator is not an important
structural parameter at the temperature of re-entry.
3. Effect of Boundary Conditions on the Behavior of the
Heat Shield
The support condition which is imposed on the heat shield
is an extremely important parameter. Figure 3.4 illustrates the
deflected position of the bond line for two different support conditions.
The resulting stresses differ significantly. Therefore, it is important
that the boundary condition which is imposed on the finite element
system be a realistic approximation of the physical support condition
which exists in the actual heat shield.
F. DISCUSSION
The automated computer program presented in this section reduces
the analysis of an arbitrary heat shield subjected to axisymmetric
thermal or mechanical loads to a simple procedure. The program auto-
matically generates the finite element grid, evaluates temperature-
dependent material properties, solves the equilibrium equations for
the grid point displacements and calculates stresses within elements,
sandwich shell face plates and at the bond layer. Arbitrary1_oundary
conditions can be imposed since any oi _he grid pointu _._aybe restrc_ncd
in either the R or Z direct ions_
Report No. 5654_O2 FS Page 43
![Page 50: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/50.jpg)
//
////_
|
m
._
@u
0
ID
I1,,,,,0
UIP
I1,1
°_
Report No. 5654-02 FS Page 44
![Page 51: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/51.jpg)
PART IV: AUTOMATED PROGRAM FOR AXISYMMETRIC HEAT SHIELDS
SUBJECTED TO NON-AXlSYMMETRIC LOADS
A. INTRODUCTION
In general, the heat shield of a manned spacecraft is composed of a
constant thickness sandwich shell and an ablator which varies in thickness
in both the meridional and circumferential directions. The temperature
distribution experienced by the heat shield is also non-axisymmetric.
Because the ablator, at high temperatures, is not a major structural
element, contributing to the overall behavior of the heat shield, an
approximation of its properties in the circumferential direction is
justified. The approximation, that it is axisymmetric, reduces the stress
analysis of a non-axisymmetric heat shield to the stress analysis of an
axisymmetric structure subjected to non-axisymmetric thermal loads. This
involves the expansion of the temperature distribution and the final
displacements of the system in Fourier series. By making use of the
orthogonality properties of the harmonic functions the three-dimensional
analysis is divided intoa series of uncoupled two-dimensional analyses.
B. THEORY FOR THE ANALYSIS OF ANAXISYMMETRIC BODY SUBJECTED
TO NON_XISD_TRIC LOADS
£ theory is presented for the analysis of solids of revolution
subjected to non-axisymmeSrlc loads which arc s_-_-_etric,bout a plane
Report No. 5654-02 FS Page 45
![Page 52: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/52.jpg)
containing the axis of revolution. Figure 4.1, a view of a plane per-
pendicular to the axis of revolution, shows the trace of the plane of
symmetry. Anisotropic material properties, which are constant along
any circumferential line, are included in this formulation.
The structure is idealized as a series of rings with triangular
cross-sections; the rings are interconnected at their nodal circles,
i.e., at thecircles containing the vertices of the triangles,
(Figure 4.2). Loads acting on the structure are replaced by statically
equivalent concentrated forces acting along the nodal circles.
I. Strain-Displacement Relationship
By noting the ax_sym_ofA _-_.__._-'---.,,,'_,_'_,_'.._ __.__+_.... _a_al
properties of the body and the plane of symmetry for deformations, the
displacements in r, 0, z coordinates may be written in the following form:
Ur =ZUrn(r,z) cos n@ (4.1a)
ue =_Uzn(r,z) sin ne (4.1b)
uz =_Ugn(r,z) cos n9 (4.1o)
Within each ring element the r and z variation of the Fourier
coefficients of the displacements are assumed to be linear, i.e.,
Report No_ 5654-02 FS Page 46
![Page 53: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/53.jpg)
S Troce of Plone ofDeformotion Symmetry
Z
Solid of Revolution
Fig. 4.1 Cylindrical CoordinateEmbedded in a Solid of
System
Revolution
1Repot(, No. 5654-02 FS Page 47
![Page 54: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/54.jpg)
Z
rk , Zk)
(ritZl} " Ring Element
Nodal Circle
Fig. 4.2 Cross Section of o Ring Element
Report No. 5654_02 FS Page 48
![Page 55: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/55.jpg)
Urn _ kln + k2n r + k3nZ
Uen ._k4n * k5n r + k6nZ
Uzn _ k7n + k8n r * k9nZ
(4,2a)
(4.2b)
(4.2c)
Now expressing the constants k in terms of the corner values
of the Fourier coefficients of the displacements, i.e., in terms of
Uirn, i i uj UJn j k k kUSn' Uzn' rn' Uzn , Urn J Ugn and Uzn
%n
kDn k5n kSn
k3n k6n kgn
Urn ue n Uzn
uj _ ujrn n zn
uk k k irn U@n Uzn
(4.3a)
with
rjz k - zjrk rkz i - riz k riz j - rjz i
I Zj - zk zk - zi zi - zj
rk - rj ri - rk rj - ri
(4.3b)
and D = rj(zk - zi) + ri(z j - Zk) + rk(z i - zj) (4.3c)
Combining Fquation (h.l) with the strain-displacement
relationships, the following expressions for the strains are found:
bu¢ = r )__2-= __ m cos ne (4.4a)
Report No 5654-02 FS Page 49
![Page 56: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/56.jpg)
'e =_ e_-+-r=r Cen cos ne (4.4b)
'z = _ = ¢zn cos rm' (4.4c)
_Ur _% _7re = ( _T" + r_- " ) = 7ren sin n8 (4.4d)
au.. aur7rz = (r_ ÷ _T ) =Z >rzn cos ne (4.4e)
_ue _uzV0Z = (_- + I _ Veznr BT ) = sin nO (_._)
_ere
_U
= _- (4.5a)crn _r
1Con = _ (nUen + Ur) (4.5b)
_Uzn _' = -- (4.5c)zn _z
_Uen Uen nurn (4.5d)
7ren= -_r r r
BUzn BUrn
Yrzn - _r * -_ (4.5e)
8USn Uzn
Yezn = _--_-- n T (_.5_)
Within a given ring the approximate values of strain for the harmonic
n are calculated by combining Equations (4.2), (4.3) and (4.5). The
Urnhoop strain is assumed to be constant within the r_ng and -- iu
r
approximated by
Report No. 5654-02 FS Page 50
![Page 57: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/57.jpg)
i j ukU U
r__n + rn +_Z_ '
3_ 3_ 3rwith 1 (ri + rj + rk)
Thus, for the harmonic n the six components of strain within the element
are given in terms of the nine corner displacements by the following
matrix equation:
The strain-displacement transformation matrix (for convenience it is
written in its transposed form)ms defined on the next page, Eq. (4.6b).
2. Stress-Strain Relationship
The stress-strain relationship for the harmonic n is
written in the following symbollic form:
[oj: [o][,j÷ ['jr (4.7a)
For an isotropic material this becomes
(rrn
%n
_rzn
or.
L uzn
B _ B o
0 0 0 I_
0 0 0 0
0
0 0
0 0
0 0
0 0
t* 0
0 0 0 0--4
Crn
eUn
gzn
CrOn
trzn
Tn
T n
T
+ n_ (4'7b)0
0
0
Report No. 5654-02 FS Page 51
![Page 58: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/58.jpg)
D
Zk-Z i
D
0
0
.
O
0
1m
1i
3_
1
3r
1
l'lm
3_
n
0
O
0
0
0
0
0
D
ri-rk
D
D
nm m
m
3r
n
3r
nN m
3r
3r
0
0
0
D
ri-r k
D
0
0
0
D
Zk-Z i
D
0
0
D
D
ri-r k
D
X1
nm
3r
nm i
3_
Report No. 5654-02 FS Page 52
![Page 59: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/59.jpg)
- (l-u) E (4.8a)where _ = (l+u)(l-2u)
u E (4.8b)
(4°8c)
E_7n= -_-j_ Tn (4.8d)
Tn is the Fourier coefficient for the expansion of the average temperature
change within the ring
T =_ Tn cos ne (4.9)
3= Equilibrium Equation for Harmonic .n
By recognizing the othogonality of the harmonic functions
the same procedure which was used in Part I may be used to develop the
equilibrium equations for an element subjected to harmonic loading.
Therefore, Equation (1.15) is rewritten as
. e.e(4.z2)_Ln] = f EGJETj dV
Within a ring the matrices _G_ andIC_ are not a function of space;
therefore, Equations (4.11) and (4.12) reduce to
Report No, 5654-02 FS Page 53
![Page 60: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/60.jpg)
(4.13)
(4.14)
Equilibrium of the over-where the volume V is given by Equation (2_i0).
all structure requires that the sum of the nodal circle forces for all
rings with a common nodal circle must equal the applied nodal force.
This results in an equation of the following form for each harmonic:
where the displacement vector Ern_ contains all the displacement
amplitudes urn , uen and Uzn for all nodal circles in the system.
r •
The equilibrium of the face plates is incorporated by a
similar procedure. Appendix C gives the details of this development.
4. Determination of Displacements and Stresses
The number of harmonics required to represent the three-
dimensional temperature distribution indicates the number of two-
dimensional problems which must be solved. For each harmonic Equation
(4.15) must be solved for the unknown displacement amplitudes. The
corresponding strain amplitudes are calculated for each finite element
by Equation _(4.6) and then stress amplitudes are found by the application
of Eauation (4,7). The final displacements of the system for any angle
are calculated from Equation (4.1). The final stresses are determined
from the stress amplitudes by the followinff equations:
Report No. 5654-02 FS Page 54
![Page 61: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/61.jpg)
Or(r'z'e) = _" Srn cos ne
_z (r'z'e) =_ _zn cos ne
%_r,,.,e)- L %n sinn_
Crz (r'z'e)= _ _rzn cos n_
_e (r'z,e_=_ _n sinne
Cez(r,z'e)" _ _ezn sin ne
(4.16C )
(4.16d)
(4.z6t)
C. COMPUTER PROGRAM
The use of the non-axis}_mctric heat sbSe]d program _s similer to
the axisymmetric program (Part III). The only additiona]input reouired
is the three-dimensional temperature distribution. The com_mter program
automatically develops the necessary Fourier coefficients for the
temperature aistrJbution and sums the series of two-dimensional analyses
to oro_Jce the final disnlacements and stresses in the system,
i. Input Information
The following seouence of punched cards numerically defines
the heat shield to be analyzed:
a@ FIRST C_RD- (7_)
Columns I to 72 of this caz-d contaLns _-_._.,,_*_._..+_._
be pr_ntedw_.th results
Report I_o. 5654-02 FS Page 55
![Page 62: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/62.jpg)
t
l
I
t
l
t
t
I
be
Co
d.
e@
SECOND CARD - (615, 2FIO.2)
Columns i - 5 Number of _oints along meridianof shield - NI_X
6 - i0 Number of points through thickness -MMAX
II - 15 Location of bond line - MB
16 - 20 Number of material property cards - NP
21 - 25 Number of harmonic to be used in
analysis - NL
26 - 30 Number of boundary condition cards - NB
31 - 40 Surface temperature of ablator
_I - 50 Temperature of zero stress
THIRD CARD - Properties of Sandwich Core (_FIO.2)
Col_m_ns ! - I0 Modulus of elasticity
II - 20 Poisson' s ratio
21 - 30 Coefficient of thermal expansion
31 - _0 Thickness of core
FOURTH CARD - Properties of Sandwich Fact Plates (_w/O.2)
Columns 1 - I0 Modulus of elasticity
II - 20 Poisson's ratio
21 - 30 Coefficient of thermal expansion
31 - _0 Thickness of single face plate
GEOMETRY CARDS - (kF!0.2)
One card per point along shield in order from axis of
symmetry to edge (NI_X cards).
Report No. 5654-02 FS Page 56
![Page 63: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/63.jpg)
Columns i - i0 R-ordinate at bond line
Ii - 20 Z-ordinate at bond line
21 - 30 Temperature at bond line
31 - 40 Normal thickness of ablator
The temperature information is used by the program
to determine the axisymmetric temperature-dependent material properties.
f. MATERIAL PROPERTY CARDS - (4FI0.2)
One card for each temperature (NP cards)
Columns i - i0 Temperature
Ii - 20 Modulus of elasticity of ablativematerial
21 - 30 Modulus of elasticity of bond material
31 - _ Coefficient of thermal e_ansion for
ablative and bond materials
g. THREE-DIM_SIONAL T_PE3AT_RE DISTRIBUTION CARDS
A table of bond line temperature values at iO degree
increments along 9 circumferential lines is punched in the following form:
Ist. card - (9F8.O)
R-ordinates of 9 circumferential points onbond line
2nd card - (9F8.0)
Z-ordinates of 9 circumferential points on bondline
3rd t9 21st card - (9F8.0)
One card for each IO degree increment (O to 180°).
Each card contains the 9 temperatures which correspond to the above R and
Z-ordinates.
Report No. 5654-02 FS Page 57
![Page 64: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/64.jpg)
h. BOUNmRYCONDITIONCARDS- (315)
Onecard per restrained nodal circle (NB cards)
Column I - 5 N}mesh point N, M6 I0 M
ii - 15 = i restrained in R-direction2 restrained in 9-direction3 restrained in Z-direction
_ restralned in R and 9-directionsrestrained in R and Z-directions6 restrained in 9 and Z-directions
7 restrained in R, 8 and Z directions
i. PRINT AN_E CARDS - (]95.0)
Column I - 5 angle 8
For earth "print angle card" a complete set of
displacement an@ stresses are printed for angle 8.
2 • Output Information
The following information is generated and printed by the
computer program:
a@
bo
C@
d.
e°
Input data
Leash squares evaluation of the temperature-dependent
material property data
Coordinates and temperature of all grid points
Two-dimensional Fourier temperature coefficients
For each print angle
(I) R, Z, and e displacement at all grid points
(2) Average stresses in quadrilatoral rings(_ _+_°==_ _n _andwich face plates
Report No. 5654-02 FS Page 58
![Page 65: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/65.jpg)
3• Timin_
The computer time required by this program for the non-
axisymmetric analysis of a heat shield is approximately
time = A + B "(NMAX)'(MMAI)2.NL (seconds)
For the IBM 7092 computer A=20 and B=O.05, and the time required for a
30 x 7 mesh with 4 harmonics is approximately 5 minutes.
4. 5 sti.
A card listing of the FORTRAN II source deck for the
computer program for the non-axisymmetric analysis of heat shields is
given in Appendix Fo The program is compiled for a maximum grid size
of 30 points in the meridional direction and 8 points through the thick-
ness. A maximum of i0 harmonics may be considered. Material properties
can be specified by a maximum of 50 cards.
Standard input tape 5 and output tape 6 are used by the
program. Tape 20 is used for temporary storage within the program; it
may be necessary to change this tape unit to conform with local computer
center policy.
D• EXAMPLES
Two analyses of axisF_,etric heat shields subjected to non-axis_etric
temperature distribution were conducted to illustrate the application of the
Report No. 5654-02 FS Page 59
![Page 66: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/66.jpg)
program. In both cases, the sxis ymmetric finite element meshwas similar
to the meshgiven by Figure 3ol. For the purpose of reference the
station layout along the bond line is shownin Figure 4.3. The three-
dimensional bond layer temperature and ablator thickness distribution
for angles e - 0, 90°, 180°are plotted in Figure 4.4.
In Analysis A the axisymmetric properties of the ablator are
assumedto be equal to the properties of the actual ablator at e - O.
In Analysis B the ablator properties at e = 180° are used. For both
analyses the surface temperature of the ablator is I000 F and the temperature
at the bond surface is given by Figure 4.5. Station 20 (Figure 4.3) is
restrained at the inside surface of the shield to simulate the effect of
an intermediate support ring.
The computer output for a non-axisymmetric analysis contains
displacements and stresses at manypoints in the heat shield; however,
only the typical results are presented. For Analysis A the deflected
shape of the bond line at three sections is plotted in Figure 4.6a. The
non-axisymmetric behavior is significant. The displacements from
Analysis B are shownin Figure 4.6b; they are essentially the sameas
those found by Analysis A. This again indicates that the ablator's thick-
ness and property variations in the circumferential direction are not of
major importance at these temperatures. Hoop stresses at station 15 are
Report No. 5654-02 FS Page 60
![Page 67: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/67.jpg)
Report No.
ii0 0
m m
seqou! -
5654-02 Fs
I
0
m
e;ou!pJo Z
0O0
.
r,..
0
0
o
0re)
0
. 0
m
in@
J=(,)i=
end
!
Q)4"
0C
em
"0tm
0
IZ:
q,1C:
em
._J
"0C:0IX)
I=0
m
0
0em
.4-,,
0,4.-.
CO
ro
oDem
b.
Page 61
![Page 68: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/68.jpg)
i seqou! - SS3NHOIHJ.
I
4)C
U
.ICF-
I ' I '-- I " I
0 0 0 0
0 0 _ 0o4It) "¢
_0 - 31:llllV_13dlN31Report No. 5654=02 F$
IOOm
O
O
Page 62
0om
,4-.
J2em
U)em
C_
u)u)
CJ¢U
em
J¢p-
0
0m
J2
<C
"0t-O
q)k,,
,era
0
L_
Q)
0.J
"0
0r_
o
eemm
b.
![Page 69: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/69.jpg)
30
II 25
15
15
25
I
I 30
IOO
_,..e
Fig. 4.5Report No.
Temperature5654=02FS
at Bond SurfacePage 63
![Page 70: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/70.jpg)
I
I
i
!
o o
Report No. 5654,-02 FS
EtU0I:
'WC
0m
0
OIL0
"0o
0
IDa
104
0m
Page 64
![Page 71: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/71.jpg)
plotted in Figure 4.7 for two values of e. In both analyses the stresses
within the sandwich shell are in fair agreement since the material
properties do not change_t these temperatures. However, within the
ablator, where the material properties are strongly temperature-dependent,
the stresses differ significantly. Of course, the particular solution is
most reasonable if the assumed material properties correspond with those
at the _osition of the desired stress. Hence, for 6 - O, Analysis A is
considered the best approximation and similarly for e - 180 °, Analysis B
is the most reasonable.
E• DISCUSSION
In this section a method and the resulting computer program are
presented for the analysis of axisymmetric heat shields subjected to non-
axisymmetric thermal loads. The program may be used to analyze an
approximate solution to a non-axisymmetric heat shield if a number of
solutions are obtained and then are judicially evaluated. At the section
where the assumed axisymmetric ablator prope_ies (+...... +.... and
thickness) correspond to the local properties, the stresses will be a
good approximation of the actual state of stress in the non-axisymmetric
heat shield. Therefore, for each angle 0 for which stresses are desired
a separate structure must be evaluated.
Report No. 5654-02 FS Page 65
![Page 72: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/72.jpg)
I00
!
I
!
I I
! !
!sd- sseJtS do0H
I00m
I
I0
Report No. 5654-02 FS Page 66
![Page 73: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/73.jpg)
It should be pointed out that the computer program can be
extended to include non=axisymmetric pressure loading_ displacement
boundary condiditons and the effects of elastic supports° However_
this additional investigation was beyond the scope of the present effort°
F. COLD SOAK CONDITION
A necessary approximation of the method of analysis which is pre_
sented in this report is that the non_axisymmetric ablator of the heat
shield is approximated by an axisymmetric ablatoro Since the stiffness of
the ablatcr is reduced at high temperatures_ this approximation is justified
at the temperature of re-entryo However_ at low temperatures the stiffness
of the ablator, as compared to the stiffness of the sub-structure_ is signi-
fic ant °
Figure 4°8 illustrates typical stresses developed within two
different heat shields when subjected to a uniform reduction in temperature
(185°F to -250°F)o The ablator thicknesses used in the analyses correspond
to the thicknesses at sections 0° and 180 ° (Fig° 4°4)° The resulting
stresses are comparable which indicates that for an axisy_metric heat shield,
the thickness of the ablator does not affect the stress distribution signi-
ficantlyo It is also reasonable to expect that the actual behavior of the
nen-axisymmetric heat shield will be bracketed by these results.
Report Noo 5654_02 FS Page 67
![Page 74: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/74.jpg)
,
II I000
i
J 800
II ._ _oo
i :I _ _oo
g
I o _oo
I
i o
_ o Section at 180 °
• Section at 0 °
- Su,,d.,ch ,.,,,,,,°i"n! Ab!otorIv I
Fig. 4.8 Typical Results of Cold Soak Analysis
Report No. 5654-02 FS PsFe 68
![Page 75: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/75.jpg)
APPENDIX A
SOLUTION OF E_UILIBRIUM _UATIONS
The equilibrium equations for a System of finite elements may be
written in the following fo_mx
AlIX I +AI2 X2 +AI3 X 3 ................... ÷ AINX N • BI
A21 XI + A22 X2 + A23 X3 ................. ÷ A2NX N - B2
A3! XI ÷ A32 X2 ÷ A33 X3 ............. _.... ÷ A3NX N - B3
mm m emem _ _ mem mm _ euem a, emmmemm e_emem
ANI XI + AN2 X2 + AN3 X3 - . + ANN XN = BN
or symbolically
where [A] = the stiffness matrix
X] - the unknown displacements
[B] = the applied loads
(Ala)
(AIc)
(-)
(Al)
Report No. 565k-o2 FS Page AI
![Page 76: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/76.jpg)
Gaussian Elimination,,,i
The first step in the solution of the above set of equations is
to solve Equation (Ala) for X]_ Or
xI . B1/An . (AI#All)X24AI#AI,)x3 ..............(AIgA_)XN (A2)
If Equation (A2) is substituted into Equations (Alb, o, ....j N) a modified
set of N-I equations is determined.
A221 X2 + A231 X3 ............. + AINX N = BII (A3a)
A_2 X2 + A_3 X3 -- ...... ----+ AINx N - BI (A3b)
|mm, mmmmemmmm mm m -- ..ma,.em ! mm m(mmmmmmmmmmmmm|mmm| m m ----m--_e-- m m --mm
I ....• xN"X + AN3 -'
whereAI AIj/AIIiJ " Aij " Ail
B.I - B i BI/AIIl " Ail
i, J " 2, ...., N (A_)
i = 2, ...., N (A4b)
A similar procedure is used to eliminate X2 from Equation (A3), etc.
A general algorithm for the elimination of Xn may be written as
Report No. 5654-02 FS Page A2
![Page 77: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/77.jpg)
I
I
I
I
i
I
l
[
[
i
I
i
[
_n-l..n-l_ XjXn " (_n /Ann''_. "nJ"nn.''An"i/An'l_u n + ip ,ooo_ N (AS)
. .n-i .n-I (An-I/An-l_Aij Aij "Ain " nJ "nn"
ip J _ n + Il ,o.o_ N (_)
_I _n-1,.n-l•n . B'I-A (_n /Ann ; i- n+ i_ ...., NB i
Equations AS, A6 and _7_Y be rewritten in compact forma
(A7)
A_n. An-1_- A_ I c._ i, J d n + I, ...., N
i " n 4" lj eeoej N
where_n-1 ,.n-I
Dn_ _ _1_ /Arm
•n-lt. n-I
Cnj " Anj /Ann
After the above procedure is applied N-I times the original set of
equations is reduced tothe .following single equation.
AI_IxN = _i
(Ag)
(_o)
Report No, 5654-02 FSPage A3
![Page 78: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/78.jpg)
which is solved directly for XN
In terms of the previous notation, this is
The remaining unknowns are determined in reverse order by the repeated
application of Equation (AS).
Simplification for Band Matrices
For mar_ finite element systems it is possible to place the stiff-
ness matrix in a "band# form which resUlts in the concentratic_ of the
elements of the stiffness matrix along the rain dlagonal. Therefore_ the
following simplifications in the general algorithm (Equations ASp A9 and
A16) are poasible:.
T-!
Xn - Dn-__ CnJXj _ - n+19 ...., n÷,M-1
n .n-I .n-I O j i, J = n + I_ n +M-IAiJ = Aij - Ain ....
n . Bn-1 A..-1Bi i - in Dn i = n + i, ...._ n +M - I
CA14)
where M is the band width of the matrix.
Report No. 5654-02 FS Page ,_
![Page 79: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/79.jpg)
I
I
I
I
I
I
I
I
I
I
i
I
I
I
I
I
I
The number of numerical operations can further be reduced by
recognizing that the reduced matrix at any stage of procedure is
sy_uetric.
equati on:
Accordingly, Equation (AI3) may be replaced by the following
_n-i .n-i i - n + i_ ,,,,s n +M -1
_ - Ai -Ain cn I (nS)S S S S - i, ....,n+M-
since
n . AnAji iJ
The number of numerical operations required for the solution of a
band matrix is proportional to NM2 as compared to N3 which is required
for the solution of a full matrix. Also, the computer storage required
by the band matrix procedure is _ as compared to _ required by a set
of N arbitrary equations.
This technique has been used in the automated axisysuetric proEr_
for the analysis of a typical heat shield idealized by a iO x 40 mesh of
quadrilateral el_ts. A solution to 800 8i_ultanQous equations was
necessary, which required less than two minutes of computing time on
the IEM 7094e
Report No. 5654-02 FS Page A5
![Page 80: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/80.jpg)
APPENDIX B
MATRIX FORMULATION OF THE LEAST SQUARE CURVE-FIT PROCEDURE
Consider the problem of selecting the "best" polynomial of the
-cI+c_ +c_2+c,x_,....,c.__'Ito_,_°.__°_o__form YAI
set of data points:
n XI _ YI J X2| Y2| ..... ,.............. J
If the above po_omial is evaluated at points XI
following form are found:
Cl +02 Xm +C2 _ + ............. CN_-I = Ym
or in matrix form
r.lCI
C
w
m
i
CN.
Y1
Y2
mmm
M
N-iI XI X2 ..... XI
I X2 X) ----- X2N'I
mmmum lilil
gmm_Imo_ m m qmmmm_ mm4m i_mmi i i NQ i
• ......
%o XM, M equation of the
m n i| ****_ M
(Bla)
E
Report No. 5654-02 FS Page BI
![Page 81: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/81.jpg)
or symbolically
where
where
A] : M N matrixa x
Y] a Mxl matrlx
[.?'If Equation (BI) 'is premultipiled by _ a set of N linear equations.
in N unknowns is created, Consequentlyj
[0].- [0][A]'E.]
[D] = [A]T[_ - aNxl matrix
Equation (B2) can now be solved directly for the unknoml coefficients [0] @
This procedure is numerically equivalent to the standard least
square procedure. Howeverp it is presented here in .a form which is readi_
programmed for the digital computer The technique is not restricted to
po_Tnomlals.
Figure B1 illustrates the application of the method in the evalua-
,4^.._v..^ev.+ho.......,1,,tic modulus for temperature dependent materials, A
fourth order polynomial was used6
Report No. 5654-02 FS Page B2
![Page 82: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/82.jpg)
I
II
Ii
I
II
II
I
iI
I
I
I
E
r
_0m
)¢
o,m=
Q.!
m
qU0
3E
600
500
400
300 -
20O
I00 -
00
• Data Points
Fit
I I I200 400 600 800 IO00
Temperature - degrees farenheit..
Fig. BI Example of Least Square Curve Fit
Report No. 5654-02 FS Page B3
![Page 83: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/83.jpg)
I
APPENDIX C - MATHemATICAL MODEL OF SANDWICH SHELL
IThe sandwich shell substructure is composed of a honeycomb core
I material and two steel face plates. The orthotropic core material is
I readily represented by solid triangular rings as indicated in Part IV
of this report. However, for the description of the behavior of the
I face plates, a shell type element is used. The appropriate theory is
i given in this appendix.
It is assumed that the face plates are idealized by series of
I truncated cone elements which are connected at mesh points of the finite
I element system. The cross section of a typical truncated cone elementis shown in Figure C1.
Z _ _ Nodal circle
\ j rs,Z jK_\ _L_ of Thickness h
Truncated Cone Element
I ivlfri,zi _(,
FIGURE 01 - CROSS SECTION OF TRUNCATED CONE ELDEST
I
Report No. 5654-02 FS Page CI
![Page 84: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/84.jpg)
The displacements of the system in the r 9 @9z coordinate system
are written in the following forms
ur " _ _rn (rgz)cos
u " ) Cr,z) cos n@Z ¢_ Uzn
ue = _ _n (r,z)Binne
where Rrn (r#z), uzn. (rpz) and _n(r,z) are the two-dimensional displacement
functions (Fourier coefficients) associated with the harmonic n.
Within each truncated cone element, the two-dimensional displacement
functions are assumed to vary linearly. The displacement at some point
t within the element is given in terms of the nodal circle displacements
(ci)
(c2)
(c3)
Acc_dingly9 the displacement in the t-dlrection is
Report No. 5654-02 FS Page 02
![Page 85: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/85.jpg)
ut(%e) - ur(%0) ace ® .,-um(t,e)e_ ® (c4)
&where cos w • 7
sin (. • b
j The inplane strains within the truncated cone elemen% are
! % "_-" _'%" ooe .o (c5)|
, _ue
(C7)
By cc_bi_ing Ec[uatio_s (el)throuEh (C7)_ the inpla.e strains
for harmonic n are expressed _n terms of nodal circle displacements by
, the following matrix equations:
%,
_tn
m
. a b a b ¸
o
m
0
_-t n(_-t) t ntr--l" o r-"I _ o r-'/
i
iU_vl
!
I '
_n
(08)
Report No. 5654-02 FS Page C3
![Page 86: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/86.jpg)
If Equation (08) is evaluated at the center of the element, the average
element strains _re given by
. ,.,. ._ a _ -_
n "6n;'., = o _ o --.-.
t •- r,a ...._._b __ ...:._. ._ :z _
where _ = (ri + rj)/2
or Equation. (C9a)written insymbolic form
r, I . [_][o] (o,,,,)Ln..l
(Cga)
From Hooke,s law, the _stresses within the element are given by
r-
|I v 0
I0 0 I-__L -_-
m
¢%n
¢@n
n m
I"1° i
T2
mo
Report No. 5654-02 FS Page 04
![Page 87: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/87.jpg)
l+uwhere _I " _2 " -----'2 Fnt Tn
I-_
I Equation (lOa) expressed in symbolic form is
I [,j- Fo_[,j.,[_] (lOb)
From Equation (I.15)_ the nodal circle forces in terms of the nodal
circle displacement for the harmonic n are given by
where
[,J, [,j [,j. [_,.[KJ-,_[oj'[o][oj'E_J-- Eo._[,]
For the truncated cone element
A-h -_
(c_)
These forces are included into the overall equilibrium of the
system for the harmonic n by the same technique used for the system
of triangular rings. When n equals zero, these equations reduce to
the axisymmetric case.
Report No. 5654-02 FS Page 05
![Page 88: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/88.jpg)
APPENDIX D
LISTIIqI3- ARBITRARY AX_ETRIC STRUCTURESi, i W , i i , ,
Report No. 565,4-02 FS
![Page 89: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/89.jpg)
__ _ _ 0 _ __ _ O_N__ _ O_ __ _ _0_ _
00000000000000000000000000000000000000000000
XXXXXXXXXXXXXXX_X_XXXXXXXXXXXX_XXXXXXXXXXXXX
UUU
Page ]:)3.
U
![Page 90: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/90.jpg)
I
J• X
I
I
II-
NI-I
..J<
h,
Z
I °_D_4
UU
I Report No_
Z_eee_eee _
E 0 II II II II II II 0 II J Z
II Z It Z _ _ Z _ 0 _ U 0_ II _0 * e _ *_ _ O0
Z Z ZOO _m_ZZ Z _ ZO
0
_,__ i...O=
UUU
_X 0000_ _D *_ _ _ _0 _
Z Z Z _ X X _ F < _ 0 _ Z _ II II IIZ -- -- v It i, It It . -- E " -- -- 0 -- -- --
* ZZ Z_v_ _< _ , _ _
UUU
![Page 91: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/91.jpg)
XXXXXXX_XXXXX_XXXXX_XXXXXXXXXXXXXXXXXXXXXXX<<<<(<< (<<<<<<<(<(<<< <<<( <<< <<<< < << <<<<<< <<<
I
j _ _ Z.ZO _O O_O _ O_
0 100_O I O<<I! II II !III II II II II _
llllllllll
_NNNNNN_
|_
_zz_mlm<l
ii ii ii ii
<UJr_<
_r_r0U
UX
<O 0 0 _ Z
_0 0 0 •
_%e%e%e 0 q_o_o_o _,, ,, ,, ,, ,, ,,
UUU
_r _r_r_O0UU
--,xxZ I I
II II IILU_3_
A _ _A A Av• _ _ _ .
O_O_O0_OOUO_OII It II II II II It II It # II II II II II
Report No.._d_-,02 FS Page D3
![Page 92: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/92.jpg)
X XXX X X X X X XXX X X X X X XX XXXXX X X XX XX X X XX XX X XX X X X XX
IIII
II
I
i0II
<
m
Z
J I_
Z _ _ _ _ _
_ _ "_ _0 XXX
_ _ _ _ _ O_ XXX
÷ ÷ Z __ X_X_ _ _ _ I_ XX_
* * * _ * = _ _ _ * * _ Z Z Z * * X X J _ II t1 II
0 11 !1 I I! v II flu It fl I fl _ _ _ _ = H II * * _ 0 _ X X X
. ,, ,,_+ . ,, o zzz _ -j_=,o _
O0_O_O0_OOvOv _ _OOXXX__X_
UUU
I Report No.
UUU
(M
3
m+ UJ t
U Pl
* I_. ZX v.J )" 0"-* (3 O_
mIf ILl
;- .T.X 3 i-
:_ =[ <ZZ0 UJ v ..,J U _"_
<0.0.)" • 11ZZ),, Ul J II II
0
UUU
Page D4
![Page 93: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/93.jpg)
________0000000000 ____
XXXXXX_XXXXXXXXXXX_XXXX_XXX_XXXXXXXXXXXXXXX
IIII
i _ _ -.' " _ _ __ U UU U U U _ Z I _r _r
Z
_xox®x _o_._oooooo
Report No. 565%-o? _s
_ O0" 0 UU Z
_0_ ,,
Z_X_X_ Z
_tl II_X__
X__ U
_1111__
O0_x_ 0
0
N
:[ZD "ZN
-'5
.I ILl
;E
O..JO_..I "
_3
x_
-j
OZO
< U.I < mi-- _. I- =[
I- 1- I- Z
[1. _.- n .._1-31- tl30. :_ .JOZO
• J tU_i- P, 1- _
{Z U.I _ 0
UUU
Page
![Page 94: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/94.jpg)
Report No. 565h-02 2'$UUU
oo
U *UJ o3: 0U
I)
Z o
ty
Z _U< WDZ
..JZ÷P. U t I--Z >- UJ O,:_ U..J_
W 0 ZU3U II >" Z
Z EIU II,=, UJ .J Z I"-I,- ,.J UwO..Z U )- =[0 _* UU. 3U U Z_Z
o o0
UUU
Page I:)6
![Page 95: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/95.jpg)
I
II
XX
o_o_ _ o oo o ,__ __" ,_,o z
. _ _X _
• o,_ !
"_ tl It II ti 4. I.. i_ i_ Q UJ tl.I .U X _ X
II 0. n _ e{ U tl tl 11 It II )- _-_ ,i _.i
_OUlO 00 _ ._ t_ 0
UU U UUU UUU UUU UU
Report No. _6_02 FS Page D7
![Page 96: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/96.jpg)
XX
_. _=
,o == =o
I
Z E _
= = _z j o=oJ _ Z _ X _W < Z _ ---- •
+ +- Z omO
o o 0 _ 0 _11 _ _io. _ _ _ # o
oNo _ _ _ _ o Z_____ Z 0 < 0 OO • ZZZ_ZZ_ZZ$ I _ _ 0000 e e O0 O++w I I I++ ++<0< _ W 3 WO l i eO00 e !10___0_
II II • _ J _ II 1111 X _ 0 II _ 0 Z Z Z Z Z Z Z_ 0 _ @ E _ ¢ 0 X P P _ _ II X _ tl 0 II 1111 ¢ ¢ _ IIIt 0 H II_ _ U _ X_X _ _ _ _ __ __
0 _ o o_o
n,n,O0X>,
"1")
OOO3Z_÷
II1 m II1<{"< ItII II >-.<I: E} t_
0ID{0
uuu UUu
Report No. _6_-02 76
0 _Z_
% _xo
X _x_
i o gJ_Oo_ eX_
_ _I__v_X
XOXZO_v__1t
I °o
i Page D8
![Page 97: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/97.jpg)
II
Ii
N X X _ ,.e _ _p! v .1. .-*t9 o :,¢• * ¢q O I'- O o
•_ X *. 11._0 ::) _O•-* X ilk' Z O <_'
,', ,'- O I- Z,'* O :Z 5" • < ,., (_ _ _1" -',
"._ N * =[ " 0. 41' W>" X Z r_ % ®XO < J
• * Z UJ 0 X b") X n0 ' IZ>,"" "" " 3: X I' O_ < • I" UJ UZ Z >" "" I-- (_ % O >" N =[ O :_ .J Z
,- ,', ^ Z "T ,, =. ; w : "='..,_ _ _ :. O :_ _ ¢0 (_ X Lg-'_ _ 0. (L X N,-, P" I _0 • 0 e I-- I-- :[+ >" 1'I,'+ X _ Z :3 _" _ 5r,=.%-..,0_ n'l_ x " o N O :3 W I U
_ =.,,,, _v,.= • _l' _. ÷ I-. Z 0_ ='_ % I" V))- I- U U_ e < ,4, I Z _ U
ff @ <( II @ X ÷ X E I- _ % O. I X 0 X Z ,-',,,, _. I-, O. I- ,,_ ,.,,>- >" II X X _ II LU II "J" Z X >" 11 ILl II ar ILl ,,.,, It) < _ II II II _ Z_ II X tY I111 >" II X UJ OII I1 >" tl X IU II It II _" '_ < I,L, t_. < O '_ = O _., U._ >- _ u') :,< n' X LtJ X 1.. U X >. x t.iJ x i- N U _ X X O. ,..,+=+ O. _ O. _ U _ +..+
o 1110 Inoo O.tO 0 ,,_ ,-= e,I o_0 _0 _0 nO _00_ _1'
u
Report No. 5654-02 FSU
A
_m
Z • eO_NNoo
0 000000
Page D9
![Page 98: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/98.jpg)
XXXXXXXXXXXXXXXXXXXX
Z0
0
Z OOO_
DDD_ZZZ_O
O OOOO
0 __O OOOO
O
_|
Z >-O_O03
%
%%%%%%_o
II II It II II II II II
Z
_O _ OZ_
_O_>___OZ <__0_ _Z_• <ZZ< _0_
_OO _ ___Z__2<_
Z_ X_
O.£3,<0..JI
>- XI,,,.,
u')Z
UZ
O
mZD
U
mOZ_
O OI
X
_Z__0__UU
E
O OZ N
0
-3u_2 -Z_ Z
OU_O=_
__ _ I _
000000 0 000
__o _ _0OOOOO_ _ _
_NNNN_NN
XXXXXXXXXX< <<<<<< << <
_Z _Z_0 _0
NU NUmE =
Report No. 96y_-.02 F!E_
l-ZUJ m
UJm LUU')U ¢o') ,--E_
I,.-_ ,'--,¢ I--LLI-I _ n_ ,d,_ _ nf0,. I I- _ I I-
_-_ -_ e_-_I It 0 I
¢3 Z 0Z ZI _ O
>. E Z e _r0.
1,- • •Z .JZlU tU
_ 0
U 03_ < V) U.I,¢ UJ n' lU ).- tU _
_. I- V)-, < UJ I-- V)r_9 I N ,'_ _ _ I1 X end< t Xx<_ e>'_X_
X _ -'_#" _
Z X ,,, LIJ O.I" _XZ ek-
O_,Z ._ ZZ• :_ (_ , r_ 0 _0 0 _
.2 _0 _ _ 0 • _ _,,
_D LU LU I- IA _ w _ Z I-00_ U_ m U. UJ > v)Z • I ,,, _1" N O I0 _ ,.., >" 0 ,_ 00 _ >-
e_ < e[ <[ < <[ ,¢ <[
OOO_OOOOOU_ ZIA _ tk (/) IL I.I.U.. LL IA. _
•-_ -4 ,.4 ,,4 -._ h. t_ 00
U
Page DIO
![Page 99: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/99.jpg)
APPENDIX E
PROGP_M LISTING - AX!SYMMETR!C HEAT SHIELDS
Report No. 5654-02 FS
![Page 100: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/100.jpg)
I
I
I
I
1
I
!
I
I
!
I
l
J
II
II
I
I
,,t N rOooooooooo
3:3:3:00_ul
01
.!UJiml
3:Ul
I.-<UJ3:
Ui,-I
e:I.-Lu5-=E).ulI,-4
x<
n0
I/I
I,-I
).,J
Z<
0 0 0 O0 0 0 0 0 0 0 0 0 0 0 0 00 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0000000000000000000000000000000000000000
_<<<<<<<<<<<<<<<< <<<<<<_<<<<<<<<<<<<
0
o_t
:>.-.
*U
_0
oo..,_r
oF-
>-N
oQ_W
o
--..ox.._
....oo<t
0 .
":GO0.,+_0
,.+ _P (13
0 _. *-'__, 0 <1'
I/) ,.,, o _,
:[ x u) <,..mX _ ,,0
,..w ,..m ,ql.
UU
Report No.
Z
t- *_r _j
• 0a:l .:_:[Z • >".010. <
XI- * n',11: *U_ n'=[3:* <• r V) >.• <>- < Ul
<ZX < UJ:[(nx c) ZZX _, U.• *U U. U.
I"ZU 0 "D_ * al I"
X * * Z"_D _ X < IL
Zl-- • n, < :[ 0Z *1- O. I- s" =[
- _ < >, _ {1, <: *. I I il_ Ul 0• • Z Z ZXXXNZ
Z V) X 4; tOO *-* :1[ <,(< fl • I--
:[ * <_ G Z I.- J _ Z 3[ Z Z II _":i[ ($11AI _ ;[ =P J II II I! II ( 00 UJ:Z tU *-* 0 "< x U_ I Z a_ _ oU _ _ _: U Z Z Z Z _ Z ti.
U UUU
5654-02 FS
o
U U UUU
ZO<____Z:[
II 11 o oi.l -,) I! •
¢J 0 ") It
0 0 U) _'
_ OlDt_.1 _.
U
0 0 _+
II H' _ _ * Z Z Z ZZ_ 0 0__
• .:XX_X0 O 000 _ II H II !!00_ H__
000 O_X_XG_G_G_X X X X
0
![Page 101: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/101.jpg)
![Page 102: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/102.jpg)
![Page 103: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/103.jpg)
![Page 104: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/104.jpg)
II
I
0
I
II
w, I_ I! II U I || • _
Report No. 5654-02 FS
_UUU
0_0__"_
XX <Z<Z
llll_ _Z_Z
till 0_0_ <
II _ 0 _ _ If _ _ _ _
oo
U Uuu
U)h-ZtU3_
u) h-ul <UJ I-
o mI-- Intn _-
0 <J h- _r.j n,< 0 0U tO Lt.
U UUU
Page
![Page 105: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/105.jpg)
o ooo0 o O0 oo
ZZZZZZZXZZ
C_<[ (/1
I o z,.J 0
.J I,-
Jq;
I °Z >-< C[
<[
< Z
_ 0< I]0
J0,,_ <UJ_ Z
U.O ,.4
i _,,J I-U I ,,d
v) < _1.-ZZ
I _: "r UJUJI-- _ _-, I-. =[ sr
_0 e]_ UU
m I W_I.JoZ _ZOUI_
_In IZI_. I
-I- _: X3:_ ,.4_0 X _ _) _0
_ sr =[ =[ =[ sr sr
i 00mOO_OOZ
0o0 O0 oO000 O0 O0
I ,-_ -, _ O_ _ O_ _Report No. 5654-02 FS Page E6
![Page 106: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/106.jpg)
![Page 107: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/107.jpg)
I
I
z.._ Ul ,.4 ,._ JII !1 _1_ II
UJ UJ- Z Z h- In
O_ I- _., k- v 0 _0 0 0 * * 0 * _ * _ 0 000 0 ,.* ,,_ 0 ,-, 0 _ iJJ _ 0_1 oJ od 0 _3 _1 _ o • t_
,. * * 0 _r . _r Z 0,', * *
000 Z v 0 .-. I- Z ,-, 00v _ v Z I'.- X: I- _ Z *-, v _
Z Z _ *
n _ n F- , n , _ k- _ n n
D D D O_ _ D _ 0 O. * D D000 Z _ 0 _" _ ZAO0
II1__ --III ......Ill III _ v I[I III
k- k- I--0 _ _- _ _ 0 i- i- I-
UUU
_ep0rt No° %_ m-n_ Z_
zII II
_ 0 *_
UJ I,- ooujLU _ (MOUJ
* U :33*
tU _" 0 "_'.-'' _ I- n n UJ
"_ U II II II II ILl 0 0 " I"-
I-- _ i._ _ _ _ J _ _ 1" Z_,. 0 v --. _-- .-' _,.. ,,_ En'v 14.1
0o
U U _ U_U
I_Xm_m_x
_.
_I0011÷_JJZ
0III!!1o
o
Zo o
0 _
o oZ _
o _
I_**_Z÷_O _ Z
ZJ OlII !ill_llll_Z
JZ_O_U Z _U_
0 0
UUU
Page E8
![Page 108: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/108.jpg)
Z 0 X >- N _ X O O I--,..w,., 0 O I--..-,-,,-, _ r_ _ n" _[ O_ ¢[ LIJ 0 0 0 0 0 Pl P3 _ Pl P')
0 0 _ 0 0 0 ,'_ N 0h. CO CO O_ 0 0000•"_ _ _ ,._ _1 0000
uuu .uuu uu uuu uuu
Report No. 56}_+-02 Y8 Page E9
![Page 109: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/109.jpg)
rnm_0oo
m(nm
___o__
000000000000000
X
x
Z
0 0
x
_@_Z_
II1_IIIOOD
ZO _0
_ _0
_ X_
0_ _UOD_
_Z_D
O_Om_
D_O_O_IZ_
J
0 O_ o,oo__ 0o0o_
_ uu0 _ lltl_
_ III1_
ZZ II'01_
__ _ I _ I 0v _lZl___ _ t _ I •
_EO0 UI_IZ_ _lXl_0__ _ I _ I __ZZ_ _1 I_
_00_ _1_X I I _ _EZ I __N_O0 0 _
_ _ZUW _0 _ _00 _ O_ Z_
_ __ 0 0 0 _v
0__
h.h.In0
I"
,¢
0
O.
.I,¢
UJI-.,¢
UJ
0
0
Z0
I.,",¢
.I,¢
¢Z,¢
0
I-¢n,¢
.JXIn_n
Xtn
0_ 0
_0_
QD_
Z_IX_ XXXX_X_I_X
_O_O0000000N_O0___l__ _
0 0 000000 O _o o o0oo0o oo
m_I,.. i,.r_ploomm3:3:mm
I.,,4
Z
.1
z0
.I
O"
o
I
O
D
Z
ILl>0m
Z
0e¢Ix
oI
k-
_,-OZ
N
Report No. _65:_-02 F8 Page EIO
![Page 110: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/110.jpg)
I •
!
J 0_ _ I_ I_1 ..4,,
I
A
P3 ,-.
©_ u_w:3 _,,
_)..,
rn,.,
z
0 Z LLI _' 0 _ _' _ X X )" >" tl II v' O II II _ 0 "_ Z UJ LU 0 0 U') ,_ X _J If 0 I| :D_ LLI "r _-" _r _. E_ I-- X X > )- O. _ U I/),-_ -'_ U _D _-i v LLI II It t- LU II II ._ • U Z
I_ =[ _. =1£ U) IH I_ It !t II If Z U.I _-_ i..i _-i j G II I_. :3 It Q. :3 II _" II _r O_:3 _ _ - 0 LU _ Z "_ v "1 _ W n' Z: 0,,.,., < 0 IJ. D..J Z 0 O. J Z l-- 0 W 0 0oq Q U .-, < < 03 rn I.- < I- _ < (O U (3 LU _ W < X L9 W < X < U I- U tl.
0 0 0 0 0
III
U U UUU UUU UUU
Report No. 565_--02 FS Page Ell
![Page 111: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/111.jpg)
I
II
I
I
I
I
I
II
2
2
U
XZ _O0 _ _
OZZQWWWQWUWWQ H _ I _ I ¢<_ I _ I _UUU It _U X X II 11 I1 II II II II II ii ii _ II 11 tt II tl II H Ii II tl It II _ III| II _ --
m
x
i-<
I/!
u.
i-ul
t-ztlJ_rUJ.I
.3
k_Z.,<
I-.
s"p,.,
IJ..
Report No. 565&-02 FS
UUU
goo_g_
.<
,¢ _I" +_ <I"+ ,_ I, +,',_ ..,,+ _ o .,,+l,.J II II • II
T nI--00 _0I100:_0
_r .jO00vOUOQUe_
UUU
Page El2
![Page 112: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/112.jpg)
_ __ __ __ __ _____000000
00000000000000000000000000000000000000000
i
i..J
i"I" U
II
Zv
÷
II fl * II --_oz_
II II00_0_
__0_
doo_o _
o oo o
Report No.
0 i- * I_.
UJ X X X [_ V)
UJ X") _ ,"* ,"_ Z"-,' I',, X X _ X m II 0 II '_," [,L#
I! LU #"" * l- 1- I-. t- 0 ILl"" )=" _ 0 _[ _[ _[ _[ 0 II 0 II .J
_ It If U II II II ¢_I_ ¢_I"_ ILl
-.., 0 .., ... ,., ..., _, w 0 LU OI.U O
0 0
0q
U UUU
==
,,=,
° 3,., o
v ,,
W
I!1=* _**
_ _1_ _1_
II _ II _ 0 _ _ II 0 0 _ _ _
_ _ _ II II _ II II _
o
Zn,2)I..- OU.I ZO_ UJ
U
Page E13
![Page 113: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/113.jpg)
II
00 O0 0000000 0 O0O000 ooooo oooo ooo___
<
•"_ _"_0 _
o0. _ _-
,--OZ
-- )" (/) -- _0 _ X
0 "-* X _1'
_,oo _
- ._® ,..:_'*._"J _*_"..t " o_) .=_ . .. + . _..
tLI _' m 0 0 Z "1" • Z ,._ ,._ : , - + + • • + + w I" _r sr .-_ _ _r :E
i Z Z )" I d" ,d" I-_ f_) e [,lJ Q ,'_ NII II Z Z Z Z Z Z Z Z l "_ U_ " e + + " * II
_- .-. *_x_ _ .a_ xx xxxx>)->)- _ , = ._,.,,,,.._0 Z _ O_ L9 L9 0 X " _ UJ =E _' 0 0 ,'_*=,,,_.,_ *,_,,_ ,,_ _,_ 5" _ II I1 11 I1 II il
"_ X ,. - . 0 _ 3:: • Z • 0 0 X X X X >* )" )")'.' Z I.... ,( ,,.,_,.,.,.,,,.,,.._ 0(/') C3 U Z :_ _ 0 X X X X >" >, >- >- Z I- U 0.. _. _ P- 0
UU U _U U U U U
Report No. 96_--02 FS Page EI_
![Page 114: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/114.jpg)
ooooooooooo oo oo__ ___
|
oo
^ __ o_
_ _ _ _Z
I °° __ _" _ _i_
U U , U U U UUU
I _epo_ _o. _-_ _ _age _5
![Page 115: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/115.jpg)
I
II
I
NN
UUU U U UUU
R_t No. _6_-.02 FS _ge
![Page 116: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/116.jpg)
I
Z
I
Ii
Report No. Page ZI7
![Page 117: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/117.jpg)
Report No. _.,_-02 _73 Page El8
I
![Page 118: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/118.jpg)
000000000000000000000000000000000000000000
0 0 0 0 0 0 0
u u uuuuu uuu uuu uuu uuu uuu
Report No. _6_k-O_ FS Page _9
![Page 119: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/119.jpg)
![Page 120: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/120.jpg)
Report No, .5654--02 FS
IIInIt_
W--_UH
•., j11 ,-_ _", ,.'., 0") J _ ") U
_1' e(U UJII II II Z Z
") ..I v J _ >0 _' '-' _,,_ I1 II ,-9
4'
UU
Fage E21
![Page 121: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/121.jpg)
[
OO _0oo0 0ooooo0oooooooo0 oo o0o0OO
< .
_ o _
Z _ _ *_ _ • _ .
U UUU UUU UUU
Report No_ 56_-02 FS Page _2
![Page 122: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/122.jpg)
_0_
0000
ZO_
I-tU Zc_ iii
I U UReport No. 5654-02 FS Page E23
![Page 123: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/123.jpg)
Il
00000000000 O0
i_ Q
g _o D
_ o D
U_
ZZO
°_z_
._ _ _,-_ ." " 0 @ It ÷ " It It _ I
OOZ_ I_
U U U U U
Report No. 565k-02 _S _ge _4
![Page 124: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/124.jpg)
APP_DIX F
PROGRAM LISTING - NON-AXISYMMETRIC HEAT SHII_,DS
Report No. 565_-02 FS
![Page 125: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/125.jpg)
I
II
0000OO00000000mmmmmzzzzz<<<<<ZZZZZ
0000 _oooooooooooooooooooooooooooooooooooooooooooooooooo_oooooooooooo_ooo_oooooooooo
zzzzzzzzzzzzzz zzzzzzzzzzzzzzzzzzzzzz
o <
o XV)•,, _(/)
o _ _
_ _UJV
"'ru
.J 0 ,'_ _I.- •W rO 00_ _ O0
I U ,_nn .>.
I
.J CO ,..- _ Z _-
Z 0 -I-_J
k- O0 .-,h. 3:UJ -,--,-- _ (,')_r OV)_O_
X Z _- _-, 0< 0 >" 3: O_I _ _0 U3Z _I ",_I Z X LO _] 0
i o z_o_ . . zZ UJ --,--, _ Z _ '-"
'_" x u) _" u') Z D _l
_ X U') 0 UJ _ 0 _u _ v
I ° °I m<ZUU UU
I Report No. }6S_-02 FS
U
+X
x << :[
Z _xxxt_z I +
_r _r _r Q:_ !r 3El_JZ @ Z _ 'ItII I!
.I II II I1 II _ 0 _ U
< _ m :E Z _ LU m UU Z_Z_Z@_
.J
uZ Z
V) "-" 0Z UJ0 Q n,
_- v v 3:
Z • • Z 00 " Z 0 _1 li.U Z _: '
,. _ -- (/)
_" o 0 o 3: o Z,< 0 _ o o UJ
:3 I- I- < I-0 _ • D _ Dm o Z 0 0 tc
Z _ _ v_1 _ 0 0
Z _ _0 < _ <[ UJ < r_
X X t- O. I-- O: I--I- < < < D I
_' _" I- m !-. v !- I- Z I-O Z_roDz _D U _D D
II II _ _ II 13. _i' _ UJ k _JZ Z _ • 0 _ Z • 0 D U_ 0 1_1
Z _Z Z 0 ;.-0 0 _-- W 0 _- llJ _ _ 0 llJ D
0 _O _ LIJI- h- O UJ _- l- > L_ P- (3.
klJ O 0 0 _ 0 ILl 0 n' 0 0 0 _ 0
o o_D I',.
U uuu UUU UuU
Page FI
o
oII.Ix
![Page 126: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/126.jpg)
0000000000000000000000000000000000000000000000000000000000000000000000000000000000000000
ZZZZZIZZZZZZZZZZZZZZZIZ_ZZZ_ZZZ ZZZZZZZZZZZZZ
ZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZ ZZZZZZZZZZZZZ
I_l --,
" G.j _-X+ Z
J N- i
LU Z
X Z+ "-" I•"- N XJ <{ (M
m•... A I.- Ig
-1 0 _"X :E J ,._+ • U. IL
Z _ _-J
0J
_J _ _
,-- =E Z X
o / ,_ U _-•"_ X + I--X +
+ Z "" I _: ""
0 < J -_ _ O0 :E >_ :E =E
Z I" "_ A "-" =E Z Z U Z
0 "_ _" LU J I-- ,-_ U _ =E U..i _ X II m _,. II I- Z II _"
Z _ A _:) 0 3E II ,-" :E II--, =E m .. (/) ,_ U -_
0 ,,_ E) :E Z W .I- _ =E I-- _ =Em I !JJ 0 . .. _ / 0 _ _-- 0 i.
0 J I--- ,-_ Z Z J X ,.-_ Z il r_ ZII tl X tl X
I-. _ I- C_ k.. I-- _( _ I-- I- C_ I.-.
0 0 O 0
L)
Report ],]o. 5654-o2 _s
o
m
X
ZO _
_XX_ _ Z ;O_U _ O_ _ _+
• Z_Z_ _ Z_ Z_ _ _ _+ - =_+ _ •
_ II II _ Z Z II II 0 0 I| II _ li e Z Z Z Z Z Z Z ZZ _ II _ 0 _ _ Ite Z _ _ 0 _ O _ _ V _ _ _ _ _
_ _ _ _ O _ II _ _ _ _ N N N N_ h h Z E _ _ 0 _ I! 00 000 _ II II II II II II II I!I O0 = _ _ -_ O0 _ II _ ___
_OOU_ 0 00_ O0 0_0_ XX
_ o_ 0o oo _
U Uu L; U U
Pa _e F2
U
![Page 127: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/127.jpg)
00000000000___________00000000000000000000000000000000000000000000
IIIIII IIII iIIIIIIIIIIIIIIIIIII IIII IIIIIIII II
ZZZZZZ ZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZ
UUU
Report No. _65_-02 _S
UUU U U
f,.o(M
Xq4
--_ O liII N."-
0 I __1 .J UJ
OILO
ID0
UUU
Page F3
![Page 128: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/128.jpg)
O0 O0 O000 O00000 O0 O00 O0 O000000000000 O0 O0 O0 O000
• ZZZZZZZZZZZZZZZZZZZZ_ZZZZZZZZ_Z_Z ZZZZZZZZ_Z
ZZZZZZZ ZZZZZZZZZZZZZZ ZZZZZZZZZZZZZZZZZZZZZZZ
X
n,i-.
_E
u3tuz x xLL < ,_LL _ =£
Z _rq I_. I..- = ,= =£ii i! U*./ ,,_ _ ,..
CO _' CO "'_ II II O O O Z
o _E o _" ILl >- Z _" II II II _.-OJ .,, O,J = D LL '-''" ,", LU
•"_ ,"= Z _ O O ,., _ I'q C_
i-- LU f-- U3 i-. 0 _ P3 L9 _ 0 v(_ E3 Z _E _ '_ _ _£ II
0 0 0 0 0 H 0 0 I-- I- I- ,1
O o OO,I _ O4
UUU.
g
g
g
g
og
og
v
"_' 0_'I-
U. 0
0
0_
Z
Z O
= Z
U
z g _
_0 _
_0_11 _0 0
lllll_ _ lie _ u__ _0_ 0
__Z_Z _0__0_0 0
0 _0 0_ 0
![Page 129: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/129.jpg)
000000000000000
IIIIIIIIIIIIII_
ZZ ZZZ Z Z ZZ Z ZZ Z Z Z
DCU O.
LU t1-
U_ Z 0
_J _-1 Z .j
U _ U
00U_
Report No.
,%0u
Z
I
Z0
Z0
m 0
Z D _
_I_
_XXX
0 0000
00_00000000
0Z_J
Page F5
![Page 130: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/130.jpg)
Report No. 5654-02 FS Page F6
![Page 131: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/131.jpg)
II
I
ooo0oo000o00o0o0ooooo0000ooooo0o000oo00ooo00
_UU UUU UUU UUU UUU
Page F7
![Page 132: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/132.jpg)
![Page 133: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/133.jpg)
I
I
I
I
II
I
III
I
II
I
!I
II
I
000000000000000000000000000000000
• _ • _ Z = • • = Z = Z = = • _ Z Z Z Z._ Z Z Z Z Z • Z _ = Z • Z
ZZZZZZZZZZZZZZZZZZ-ZZ ZZZZZZZZZZZZZ
U
N
0
Z
_ NU I
m N
om _
Z _
U _
0 _U _
÷
W JJJvXXX_
0 _ __
II tl It !III IIe00__+
U __IIJO__JXO__X
UU
Repo_ No. 5654.-0£ FS
Z
@
C_
8
=: =z ;
l# I,m"3 It
"" tU0") .I0 ,,r,1 ,._ .J
,., .JOUJ <
o0
U
Z
I,...U,J
U
oo
e
o II I IllI_ I III
• _ I _01_Z I Z_l
N _ I 0_1• ZU I _ JI
0 _ I _ _ I
_ _ Z_
Z_ _0_% O_ZU
_Z_OQ_ZZO_Z_
__0___ _00 _0_
Z _ _ 0 _
_ , % i .0 OOZO00_000_ 0 _
__ _ _ _ _ 0
__ ZZ JZZZ_N__o
Z Z__ III IIII I
0 00000___
0_000000oooo0
UUU
o 0o0ooo oo oo
ZZZZZZZZZZ Z
Xm
X
QZ0
o 0
x
_*_0 OJ •O0_N U_ 0
N_O_ ZZ=_=* UU
0.=0 ;_ I_0. _ I
X_ _ ZZ I_X_ _< I
Z%3Z_3
O_mZQO_+_ J
__00=_U_XII___N_O0 0
00_00
< < <u< _< (< _
0_00000000_
o o 0o00oo0 0 000000
Page F9
![Page 134: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/134.jpg)
00000000
IIIIIIII
ZZZZZZZZ
ooo_.
U. IL tl. 04
I I L_ "_I I O_I Z II 111I 0 N
I Z tUI _ I O.I _, I_ 0I X _, ..,-n,
0_. I N t,.J
I- I 11...,,..,_I- I _l_t_r_z t IIO_W
tO _-,iO O_ZU_J 0X0__
l--I-k-
iI I_'_" _
0_0_ O_ 000U._U.
_rO__O,1,0 ,l_ ,,_000
Report No.
mmo o
ZZ<<ZZ
UJn,
t-.
O.
I-
0
UJD
0<0en_<UJI_
_.Z
OUJQ.
Z m
,1, Z_
<ZmmO_lmee
D 00 U.m
m,.l_
wz__1<o
I_'O
O00Z
ooo
56_+- 02 FS Page FIO
![Page 135: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/135.jpg)
II
u uuu uuu
Report No. 565_-02 FS
![Page 136: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/136.jpg)
XXXXXXXXXXXWWWQW_W_UUUII II II II II II II |I II II II
_mm_mmmmm
X _ i I: I _
_ llllIlll
x_j = ._0 X X IIII + Z
gggggg ggg_ggg_'oo oo'_gg
ZZZZZ
OOO.
XXX
_111_ _ ___ I I I
_ZZZXX. X______XXX_ I I I _0___II II II II II II II ,II II II II II II II II II II II II II II II
Qe _ Q_ QQ _Q QQ Q
U. UU
Report No. 5d54.-02 FS
u
Page FI2
![Page 137: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/137.jpg)
I[! [ """ II II II_' 0 0 ,",, 0 _ I_ _ "_ 0 "_ '' k"_ x I-I,IJ I-, 0 IX"'oOrO_O_
UUU
OO_O_ 000_0_ o W_ WOW
o O_ o
U UUU UUu
m _ _ II II¢ ÷ _ II X * _ II
_ _I_ _I_II II II 0 0 _ _ II 0 0 _ _ _
_ _ _ II fl _ It Ii __ • 00_ _00 _
o
N
Report No. 5654-02 FS Page FI3
![Page 138: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/138.jpg)
0000
ZZZZ
Z
UJ ZW
U
Report No. 5654-02 FS Page FI4
![Page 139: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/139.jpg)
-., _)U UJ
• I-
0 I-"
mA.-, W
O O_ I--
•- O_ O0 ,,W ',., Z _
O _ D •
"0_ on0 oi..._ O_ sr ¢t)
l- ,,IX)>'
-X X
=d
I .gz=.=.I- re) , _£ _. v ¢q ._ ,..
_. kO Z _) 0
I ' .z?Z Z>. Z0 >" 0
:D m,,,,= Z X I-
j 0 Z=O0 =_XO_ 0
_ l _ U
_lq
L_
Report No.
ll*J"
"'_Z
IZZ<OII
II_N_II_Zllll_JmX<_XX_
UUU
5654-02 FS
x X
< e_ o_ eZ e_ e X eX_I 0 I I 0 I _XO_O I _ I _ I _I| tl II II II II II II II II II II ii Ii ii ii ii ii
U UU_
Page FI5
![Page 140: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/140.jpg)
00000000000000000000 O0000000 O0
ZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZ
!i
I
ii
I
iI
is
i.-
L_
X
I.-
=E
,n
LL _ _ O
"" _ _ U 0 ",
X ,_, • _ _ ,._
"_ -J CO (/1 LgU _ Un ÷ I=. 4, _ E i.-
I I_J Z tl II t I# _," E I1 II • II _ ',,' _, Z
#t I/ _'_ 11 II E3 II II II ILl U
robwv 0 00vO_ O00wO_ 0 _Ja_ rn LL _ O U C_ U U 0 _ _ O (_ _0 U I--
O O _1
UUU U
Report No. .R.6_l_02 F,::;
Uuu
_w
3:u%xI
"r UJ
x _w4. ,--
U.I U It ,-_
LLI I-, O ,_I- 1- I_ U11 II _ _'_
I-- LU O ,-,
Oh-
U
Z
D
UJ Zn, LU
U
Pa ge FI6
![Page 141: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/141.jpg)
I!
I
I ooo_ o.oo. _.__ ®__00000 _ _
_ ______®____ooooooooooo ooo oo oo oo __000 O0 0000
<<< <_<<<<<<<< _<< << << <<<ZZ ZZ ZZ Z
I o_ _UN_
| --
o-" " 1 i
0_ _
zz_- i;i,_ = -.,, ._-zzzzzz _ ---+++.' _ _ ' _ ZZZZZZZ
I
I
I
OZ_O_
D_XUO_
Report No.
00_00__
_ ZZZ_
00
UUU
5654-,o_FS
< ¢ 0 0 II II II II II II II II
U Z_ _ _ ___+J II II Z _ _ w _ w v _ _ _
Z_O fl 0 II X_ XX _ _U Z_ Z _ _XX X X _ _ _
_w_w
It II I1 H II II l!
UUU U U
Page FI7
![Page 142: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/142.jpg)
I
r
ooooo ooooooooooo _oo ooooooo ___oooooo
i zzzzz_ zzzzzzzzzz_ <<<<_<_zz ZZZZZ
iI "
_ _ _̂ _
----- _ _ZZZZZ
__ . . . _.^+++ ..... o
_-_ _ _* • *++++++ ___ _ _E_+_z ,. - z_z__ ,,,,..... _ ,.__
O_ 0
U U u U U UUU
Report No ,;_pi;-,O_2_ Page FI8
![Page 143: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/143.jpg)
|
000000000000
II IIII IIII II
ZZZZZZ ZZZZZZ
I
I
I
1 Report No Page FI9
![Page 144: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/144.jpg)
I
II
I
III'i
I
_0 O+ 0 ,-+no oo o_ @
0000m ul ul (n
ZZZZ
D
411
or_
_N
_ofe_
>vX_o
_n_x
XO
e tlL
o im
o om_
e _
_.- o x
wz z_
I,.,,
0 Zv_ uJ_
u
0000000000000000000000000000000000ooo0o0m_m_m_m__m_mm_m_mm_mmm_mm_mm_mmmI"<Z
x
I-
I-
raZ
Z
Z
W
<IEZ
,.J
Z
I.-
0
Z
Z0
0
ZZZZZZZZ_ZZZZ_ZZZZZZZZZ_ZZZZZZZZZZZZZZZ
ZZ ZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZ ZZZ
A
_D
A A
Z* Z
Z
"" Z
e,4
U.I LU t!"" Z Z
" _ Z U') ZZ 0_0__9 v U_UU_ =
X < _0 ,". ,,+
" z m z tutu ,-, _" m © ._J I- _ v ZZ v _,_ Z
= 0 ,-' X (/) _) Z _ _ _ _
'=' 0 " "" U U _ X X X X
X m, _ m_ --,.,._,.., ,...,.,,_.,.A ¢¢)
Z I- Z" _ _ _r _ _ _ _ O.
_ @: :3 '< Z Z Z Z Z Z Z v
UJ X X 0 ",", ,-- • X X X X X ,,_ vX n < ,< o . "r ..,+I- .,.,.+ < < + + + _ _ _+ < _r _" II 0 Z I I'' +''_+ 0 II _ '_r_-_,.._,A _"__',_W"_n.-m .
> I-- Z _" _0 0 (_ f_ II _ .,.Iv _ Od _ Z _r _ _r "s" I_ _ U1 (/') (/) o× • . . ,, • . .. ., ._. _. . . ..... ,, ,, ,, ,,Z Z Z
,_ "4 3 II II • • • II _r II II • 0 ..I U. 0 U. O., X II llvvv
._ X X Z II II It Z • _ II o._ I-- ][ II tl U ; Z Z Z Z
_ _" "_ 0 _" _" _" 0 _ "_ _'_ v Z 0 .I Z II • 0 0 _ _r _r I_ _-_ _' It) _0
II II < Z Z Z _9 _ _ l! 4/) Z < II Z Z Z LD LD LD L,O _:D Z X I_I 0 0.,., v-" 0 " 0 0 _ W 0 I" 0 "_ _J Z 0 0 w-._,-' 0"* _ _ "_ ILl
0 0 0 0 00 ,._ _ 0
Report No. 5654-02 FS Page F20
![Page 145: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/145.jpg)
00000000000000000000000
ZZZ ZZZZZZZZZZZZZZZZZZZZ
tUUJZZ
00_-.UU_
L_ L_
O. 0., O.XXX+ + ÷
E E E
Z _ZNIIIIII
IIIIe._Z_ZZZ
00_
00_
00
U U
U)UJ
_Un_
OZ<
h-ZUJs__JU
ln(/I
.i 0
Z _-
Z I-0U 0
oo
UUU
< < <
ooooooo_o_o_
O_O_O_
x x _
_Z_Z_Z
_Z_Z_Z
O_OEOE
_ J_ J_ J--J_j--j
_U}U_U
U
zZ
e
UZ
_0
II
_r
Z
ZZ
o oooo4o
o4
I-k-
OOvv
a.O.
I,-h-
_r I.- I-
•-_ a. 0.II I-I-
_r_OO
oo_J_O I.- k,
oO
I0U')
0(/)Z
Z
ZZ
IIZ
II
II
Z
I- n
U
o oNo
O0vv
LUllno.<<
0.0.
O0
IIIW
o ooo oo oo ooo
ZZZZZZZZZZZ
0I/I
0I-"
0
U U
N
Xo
N ON
X _ o
I III
X oooo o,o
_0
x__ ZO___ZZZ
UUU
JJJ QN__
Z__
_III_<_N_OOO__*I_III_
_N_N_
_@X_@__O__OO_OOOOO
OO __OO OOOOOOO OOOOO
I_. _00_ 0 ,._
00000
"r Z _r Z "r< < < <[_<ZZZZZ
tU_O@
I"
O_-rt0_tU._0
_(_
tU
UJ%(U UJ< i,i_-
IJLUU_Z
3O..JoonZ_- I<IZ
ZX
Iii _ItO_UJ
n_l_1
n=£ O
IiiOOtg_-T
O_OUJm>'I"
3:
@XU_
<%u>
• UJ •OUJ_ Z
0o
Report No. 565_02 F$ Page F21
![Page 146: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/146.jpg)
I "|
o + ÷ ÷
i < _ " " " " " " " _ "'_'" J ....Z Z II II e II _ tl • !1 _ U _ i II II • II _ _ II II t II
_ _ II II It II Z U II II X II II_ _ 00_0_0_ 0 _ _ _ _ 00 _ 0 _ 00_0 _
0 Z _ 00_0_0_0_ _ I! 00_0 _ _ 00_0_D _ U 00wO_ O_ O_ Z _ _ 0 0 _0_ I 00_ O_
I o 0 o o0 0 0 0
U UUU UUU
I Report No. 5654-02 FS
UUU UUU
Zr_
ZLU
U U
Page F22
![Page 147: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/147.jpg)
,II
00000000000000000000000000000000000000000000
• ===ZZZZZZZ=ZZZZZ =ZZZZZZZ_Z_ZZZZZZZZZZ_ZZ_=
ZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZ
i 0 Z v Z 0 _I"n, tU U Z I- ,._rn Z UJ ,.-3 _ 3: I_. O 0Ul C_ U _ +,9 C_
II
o_p_
o
o_
• ...;- -<
__,,, o° o_
__ _o° I_!oo . . 3-I U.I _,-" 0 ,.., O0 "" ZZ0 II H 0 _ _' _"_ _' _ "'_ Z _"_ _"_
_ U 0 _J It tl '_ "_ Z Z"' O ',,_ O II 0 U- II 0 IJ, U. t_ e'_ iI II 0 0
o oo o _u_ cOo_ih. O00_ 0 00 0 ,'_ ,_
UUU UUU
ReT)ort No, 5654-02 FS
U U UUU
t
,,,,,, +_ .. ,+,., '_ .++-,U I II II _" < < Un, II ,.-, ,-_ ,'+ II II IILU O. C_ 0 C3 13 .-.--,-_-_t-- _r j _ j E -_ j _:Z LU -,,, v I| !1 0 +._ .,., ,..-
UUU
Page F23
![Page 148: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/148.jpg)
II
Immmmmmmmm_mmmm_mm_mmmmmmmmmmmmmmmmmmmmmmmm_oooooooooooooooooooooooooooooooooooooooooooo
• _zzz z_zzzzz_zz_zz_zz_zz_-zz_z _zzz_ _z zz
ZZZZZZZZZZ ZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZ ZZ ZZ
ZZ
0U
Z
m o
0 _
Z _
_ Z Z ZO Z_Z ÷ _ _ Z_ *_
• Z% • _ ZI0 _II_ _ _ _ _iI _
IZ _ _ _ __+_ _ _.1 _ Z
÷_ _ _Z_ _ _÷_÷_
UUU UUU
0
Z 0
0 oZ U Z _ ZZO Z _ Z
0 * I1 _ Z tl _ Z Z _ II _ _ _
U _ @ II Z _ 0 _ _ I III II 0 II II II
_ II 0 _ fl Z 0 U II _ II II _ _ 0 _ _ _
o o o
UUU UUU
Report No. 5654.-02 FS Page F24
![Page 149: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/149.jpg)
Ii
II
iI
II
_oo000
0oooo0
ZZZZZZ
ZZZZZZ
Z_ fY
l! II UJ
0 oo o
U U
Report No.
0ZIJJ
5654-02 FS Page F25
!
![Page 150: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/150.jpg)
0 0 0 0 0 0 0 0 O0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 O0 0 0 0 0 0 0+0 0 0 0 O0 0 0 0 0 0
ZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZZ
Report No. 5654-02 FS
![Page 151: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/151.jpg)
o ..
ooooo00 o00o0
ZZZZZZZZZZZZ
U.I f'.t- rO
U (_ (t Z
0 + | II* OZZ
_1" Z,".II _'Z
Q_l_m
_U
0_Jo
Z Z_0 r_
Z I- _3O0 W Z
o oO O._o 0
U U
Report No. _6_1_.-0_ FS Page F27
![Page 152: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/152.jpg)
00000000000000000000000
Z Z Z ZZ ZZ ZZ Z Z Z Z ZZZ ZZZZZ ZZ
i °3
.-)
o_
z.o o _ _ _ _m _ml
_,_ . ^ . .
:_*'* 0 0 '_ U. "* 0 _ O_ O.J "r (_ ILl 00 Z
000 0 O0
U U U
Report No. 5654_02 FS Page F28
![Page 153: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/153.jpg)
APPENDIX G
SUMMARY OF EFFORTS TO SOLVE THE THERMAL STRAIN PROBLEM
BY THE OVER-RELAXATION AND DIRECT INTEGRATION
OF FINITE-DIFFERENCE FORMULATION
I. ACCOMPLISHMENTS
During the initial phases of this contract, finite-difference techniques were
employed in an effort to solve the governing differential equations for this prob-
lem: The _]iowing work was accomplished:
A. Derivation of basic equations suitable to the given geometry
B. Derivation of the finite-differences model of the equations
C. Development of a thin-shell model for the thin layers (bond, face-
plates) and its finite-differences equivalent
D. Attempt to establish proper boundary conditions for the finite-dlfference
model
E. Programing of the finite-difference model(s) and attempts to solve the
equations by (i) the over-relaxation approach (in several versions) and (2) direct
matrix, inversions.
F. Investigation of alternative methods and recommendations.
A summary of the results in each of the above areas is presented in this appendix.
II. DERIVATION OF BASIC EQUATIONS SUITABLE TO GIVEN GEOMETRY
A complete set of equilibrium equations in terms of displacements in spherical
and toroidal coordinates was derived and is given below. A singular point exists
at _ = O° The equations for this point are also presented.
Report No. 5654-02 FS Page GI
![Page 154: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/154.jpg)
For orthogonal curvilinear coordinates (6l,__ 62, 63), the element of arc ds isdefined by
3 2ds2 = Z gii d6.
1i=l
(al)
where gii represents the metric coefficients
_/axis of sy_netry
R,4
III
xx I
axis of symmetry
2
\\
V
Fig. GI - Coordinate Axes
Spherical Coordinates Toroidal Coordinates
_i R r
62
63 e e
gll I i
R2 r2g22
R2 sin 2 _ (a + r sin _)2g33
g = _gllg22g33 R2 sin _ r(a + r sin _)
Note: Toroidal coordinates reduce to spherical coordinates in the limit
as a ---_ 0.
Report No. 5654-02 FS Page G2
![Page 155: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/155.jpg)
Equations of equilibrium with zero body force take the form shownbelow.
= o (02)
where g _ _gllg22g33 and T.. and _.. are normal and shear components of stress, re-im mjspectively.
After substituting the respective components of 5.m and gii in Equation (G2)
and performing the indicated differentiations and summations_ there are obtained the
following equilibrium equations in terms of stresses for each coordinate system:
A. SPHERICAL COORDINATES
STRR i _ i STR@ 2TRR - + cot+ R + R sin _ _ + - T_ RTO@ TR_ - 0 (G3)
= + -+ R d9 + R sin _ 00 + (T_ T@@) cotR : 0 (G4)
STRe i _ i _@@ 3TR@ + 2T_@ cot-_ + R + R sin { -_ + R = 0 (G5)
B. TOROIDAL COORDINATES
rr
-_r +-
i _Tr8+
(a + r sin _)
+ (a + 2r sin _)Trr - (a + r sin _)_ - T@@ r sin _ + Tr_ r cos
r(a + r sin _) : 0 (06)
r + sin
+(20 + 3r sin _)Tr_ + (T_ - TS@) r cos
r(a + r sin _)=0 (07)
Report No. 5654-02 FS Page 03
![Page 156: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/156.jpg)
i
II
II
+-r +_a+ r sin_) -Y@-
(a + 3r sin _)Tr@ + 27_e r cos
+ r(a + r sin 9)-0 (G8)
C. HOOKE'S LAW INCLUDING TEMPERATURE TERMS
T
To
(G9)
where
• .. : 2_e.. (OlO)
0 = e_ + e_ + e_=
and I and g are the Lame constants defined in terms of Poisson's ratio _ and Young's
modulus E according to
_E=
(1 + _)(1 - 2u)
E } (all)
D. STRAIN - DISPLACEMENT RELATIONS
u 3 uki i Sgiie. = + _
@ii 2gii k=l _ _gkk(GI2)
e.. -
10(G13)
Report No. 5654-02 FS Page G4
![Page 157: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/157.jpg)
Let u, v, and w be componentsof displacement in the three principal
directions r or R, _ and @. Then substitution of these displacements in Equations
(GI2) and (GI3), with the metric coefficients of Page G2, yields the strain-dis-
placement relations for the coordinate systems shownin Sections II_E and II,F.
E. SPHERICALCOORDINATES
_U
eRR =
i _v u
:
i _w U v cot
e88 - R sin _ _+ _ + R
eR_ : _ _ - [+i
e_@ : _ _ R R sin
eRe : 2 R sin _ _ - [ +
(Ol4)
F. TOROIDAL COORDINATES
_uerr
_i _v u
e_ = --r _ + --r
i _w u sin
e88 = a + r sin _ _ + +a + r sinV COS
a + r sin
(o15)
if!er_ : _ _ + _r - r
Report No. 5654-02 FS Page G5
![Page 158: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/158.jpg)
e_@: _ la + r sin _ _ r _ a + r sin _I
zl l _u _w w sin_ 1
er9 = _la + r sin _ _ + _rr - a + r sin _I
G. EQUILIBRIUM EQUATIONS IN TERMS OF DISPLACEMENTS
Expressing the stresses in terms of displacement using Hooke's law(Equations G9) and (GIO) with the strain-displacement relations _quations (GI4)
and (GI5)], the equilibrium equations _quations (G3) through (GS)_ may be written
in terms of displacements in the form
-,2 -,2 -,2 -,2 -,2ou ouk _0_1 k _0_2 k _0_3 k OC_ldO_2 k dOC2dO_3
-u Ou Ou ou
_2 -,2 _2 -,2+ _- V -- 0 V -- V --- 0 V --- _2VU---Z+B U----z+c_ U---_+o y&-y.&.U+-_.
82+- v +- 8v - 8v +- 8v -
+ A ----_ + B ----_ + C ---'_ + D _----_--- + E
5
- -- _0_ ' - ' '_
Report No. 5654-02 FS
(_15)
Page G6
(GI6)
![Page 159: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/159.jpg)
TABLE GI
COEFFICIENTS OF EQUILIBRIUM EQUATIONS
SPHERICAL COORDINATES
(_io)
Ak
Bk
Ck
Dk
E k
Fk
Gk
Hk
Ik
Jk
%
%
%
%
%
%
%
£k
k=l
K+2_
_/_2
I_/(R 2 sin 2 ¢)
0
0
0
2(x + 2_)/R
I_ cot _/_-
0
-2( x + 2_)/R2
0
0
0
(x + _)IR
0
0
(;_ + k) cot ¢/R
-(X _- :_,,_/.,:,2
0
-(X + 5_) cot ¢/R 2
0
0
k=2
0
0
0
(x + _)IR
0
0
0
2(X + _ix_/_-
0
0
(X + 2_)IR 2
_/(R 2 sin 2 ¢)
0
0
0
21_/R
(),. + 2i_) cot ¢/R 2
0
-(X + 2_)I(R 2 si 2 ¢)
0
0
k=3
0
0
0
0
0
(X + _)/(R sin _)
0
0
2(X + 2_)/(R 2 sin ¢)
0
0
0
0
0
(;_ + _)I(R 2 sin ¢)
0
0
0
(;< + 5k) cot ¢I(R 2 sin ¢)
0
_/R 2
Report No. 5654-02 FS Page G7
![Page 160: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/160.jpg)
TABLE GI (cont.)
COEFFICIENTS OF EQUILIBRIUM EQUATIONS
SPHERICAL COORDINATES
(_/0)
k=l
_k o
5k o
_k o
_k (X + _)/(R sin _)
_k 0
_k 0
Ik -(_ + 3")/(R2 sin _)
_k
1.... • _=2
: 0
0
(k + ,)/(R 2 sin ¢
0
0
0
-(k + }_) cot ¢/(R 2 sin ¢)
0 O
......... 7:-"ETI--_<-_-ii _:l. IU: i _ ----i_ .... _. "
TABLE G2
COEFFICIENTS OF EQUILIBRIUM EQUATIONS
TOROIDAL COORDINATES
A k
Bk
Ck
D k
-k
Fk
Gk
Hk
k:l
_+2_
_/r 2
./(a+rsin¢ )2
0
0
0
(X+2_) (a+2rsin¢)/ Jr(a+rsin¢)_
_cos¢/Er( a+rsin¢ )]
k= 2
0
0
0
0
0
2( },+2_) rs in¢+ (k+5,)a
r2(a+rsin¢)
k=3
(4+ 2 2
0
0
0
2_/R
, cot ¢/R 2
0
-_/(R 2 sin _ ¢)
k:3
0
0
0
0
0
(k+_)/(a+rsin¢)
0
0
Report No. 5654-02 FS Page G8
![Page 161: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/161.jpg)
TABLE G2 (cont.)
COEFFICIENTS OF EQUILIBRIUM EQUATIONS
TOROIDAL COORDINATES
Ik
Jk
\
%\
_k
Gk
Hk
\
k =i
-(_+2_) [i/r2+sin_/(a+rsin_)_
0
0
0
(X+_)/r
0
0
(k+_)cos¢/(a+rsin¢)
-(_+3_)/r 2
0
(X+3 )rsin cos + oos r(a+rsin¢ )2
0
0
0
0
0
(X+_)/(a+rsin¢)
0
0
-(k+}_)sin¢/(a+rsin¢) 2
0
_k
_k
_k
_k
_k
_k
_k
_k
3_
k = 2
0
k=3
r(a+rsin¢) 2
0
0
0
0
0
i (k+_)/_r( a+rsin¢ )]
)
' 0
(k+2_)acos_/ _( a+rsin_ )_
(X+2_)/r 2
_/( a+rsin_ )2
0
0
O
_(a+2rs in_ )/rr( a+rsin_ )]
(_+2_ )cos_/jr( a+rs in_ )]
0
0
0
(_+3_)cos_/( a+rsin_)2
(X+2_)r2+_a2+( X+3k)arsin{I
r 2(a+rs in¢) 2 ,
O
_/r 2
(k+2_ )/( a+rsin_ )2
0
( _+_)/[r(a+rsin_)]
0
0
0
0
0
_+3_)cos_/( a+rsin_ )2
0
0
(a+2rs in_ )/Jr( a+rsin_ )]
#cos¢/[r(_+rsin¢)]
i -_/(a+rsin¢) 2
Report No. 5654-02 FS Page G9
![Page 162: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/162.jpg)
TABLE 03
COEFFIC IENTS OF EQUILIBRIUM EQUATIONS
POLAR COORDINATES [FOR APPROXIMATE TWO-DIPIENSIONAL LOCAL
SOLUTION FOR ANY (8 = constant) CROSS-SECTIONAL PLANE]
Ak I _ + 2_ 0
Bk | _/R2 oDk
Gk
0
TT_-_]__
J_-
-_ i_ IR
R !u'i'! !o_/ ..... -"
\\
\
0
0
(x + _)/R
_ _2
(_ + _)/R
_ ;_ + X + 5_)/R2
Im___llbl , _., _m
(X + 2_)/R 2
0
-_ (_ + 2_)_
Note: Temperature-dependent material property derivativ_ t_rms are
also included. Only applicable coefficients are listed. By replac-
ing R with r, the above coefficients are applicable in the torus
cross-section region.
Report No. 5654-02 FS Page GIO
![Page 163: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/163.jpg)
H° EQUATIONS FOR STRESSES IN TERMS OF DISPLACEMENTS
From Hooke's law_ Equations (G9) and (GIO)
[ f 1Tij : 2_eij + 8ij @ (3X + 2_) _(T)dT
9o
where 5.. is the Kronecker delta defined bym$
(o17)
and
6.. :i, i :jzj
:0, ilj
(_ -- + +ell e22 e33
Writin_ the strains in terms nf ai_1_r_m_+_ f_m =_+_=- _....+_- {_),_
or (G15) and shortening the nomenclature by defining the stresses
i
I
I
I
T1 : T orrr TRR
T5 : T_e
T6 = Tr8 or TRe
Equation (GI7) may be written in terms of displacements according to
T
_Z + h_ (3X + 2_) / _(T)dT = _u r + _u_ + y_u 0 + 8zu
To
+ _v r + _v_ + _v e + Y_v
+ _w r + _w_ + _w e + 6_w
Report No. 5654-02 FS
(618)
Page GII
![Page 164: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/164.jpg)
where
TABLE G4
COEFFICIENTS OF STRESS EQUATIONS
SPHERICAL COORDINATES
(_/O)
% 1
(%
B%
8
B%
7_
8%
%
_+2_
0
0
0
X/R
0
x oot ¢/R
0
0
X/(R sin ¢)
0
2
X
0
0
2(X + _)/_
0
(x + 2_)/R
0
X cot ¢/R
0
0
X/(R sin ¢)
0
3
0
0
0
X/R
0
(),. + 21_)cot ¢/R
0
0
(4 + 2b)/(R sin ¢1
0
4
0
dR
0
0
0
0
-_/R
0
O
0
O
5
0
0
0
0
0
0
p/(R sin ¢)
0
0
_/R
0
-_ cot ¢/R
6
0
0
_/(R sin ¢)
0
0
0
0
0
0
0
-_/R
...................................................... L.:LIZL 2:_;--- L 12 L'L:IJLI,yLLL'__'_ZZIL-I:Z..LL_.T.'-_L::[JIJ.',£,'ZL_.."
Report No. 5654-02 FS Page GI2
![Page 165: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/165.jpg)
TABLE G5
COEFFICIENTS OF STRESS EQUATIONS
TOROIDAL COORDINATES
B
7_
8
F
0£
i
k+2_
0
0
X(a+2rsin¢)
r(a+rsin_)
0
X/r
0
_cos_
a+rsin_
0
o
_ kl(a+rsin_)
_ o
2
k
0
0
X+2_____+ ksin_
r a+rsin_
0
(k+2_)/r
0
a+rsin_
0
0
X
0
4
0
00
x_+ (X+2 )sin r a+rsin_
0
X/r
0
a+rsin_
0
0
k 1 X+2_
a+rsin_ I a+r_in_0
5
0
0
0
0
0
0 0
0 _/(a+rsin¢)
- t_/'r : 0
0 0
_/r
0 0
_cos_0 a+rsin_
6
0
O
_/(a+rsin_)
0
0
0
0
0
0
0
_sin¢- a+rsin_
TABLE G6
COEFFICIENTS OF EQUILIBRIUM EQUATIONS
POLAR COORDINATES IFOR APPROXIMATE TWO-DIMENSIONAL LOCAL
SOLUTION FOR ANY (@ = constant) CROSS-SECTIONAL PLANE]
.......... i .....
I
8_
8_
I 2 4
k +2_
0
X/R
0
X/R
0
k
O
(k + 2_)/R
0
(X + 2_)/_
0
0
_/R
0
0
- [_/R
Note: Only applicable values of _ and coefficients are listed.
By replacing R with r_ the above coefficients are applicable in
the torus cross-section region.
Report No. 5654-02 FS Page GI3
![Page 166: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/166.jpg)
I. EQUATIONSAT THEAXIS OFSYmmETRY
Certain of the coefficients in the displacement equilibrium and stress
equations becomesingular at the axis of symmetry (_ = O). For the nonaxially
symmetric case the axis of symmetry has no special physical significance and this
point can be avoided. For the axially symmetric case, however, the axis of symmetry
is generally quite important and the singular coefficients maybe evaluated by the
use of L'HSspital's rule. For example, the coefficient HI in the displacementequilibrium equations in spherical coordinates is _ cot _/R2 which becomesinfinite
as _ approaches zero. From Equation (GI6), this term multiplies the displacementcomponent_. The conditions for axial symmetryare
u_
_fw(R,¢,0) = _ = 0 (GI9)
where f is any function of R,_,@. From this it can be shown that
_,, 82- _ = 0 at _ = O.
v : _- _2(G20)
_U
Hence, since _approaches zero while HI approaches infinity, L'H_spitalXs rule is
applicable to the product
as _ ---_0. Taking the limit, there is obtained
cot _ _u __ lim
R2 "_ : R2 ¢ --_o
= _ . 82u
R2 _¢2
sin ¢
cos
Report No. 5654-02 FS Page GI4
![Page 167: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/167.jpg)
Hence, for this case, the coefficient HI becomeszero and the coefficient BI which2
_u 2multiplies _2 is increased by _/R • Applying this limiting process to all thesingular te_s, the following sets of coefficients are obtained:
TABLE G7
COEFFICIENTS OF EQUILIBRIUM EQUATIONS ON AXIS
OF SYMMETRY (_ = O) FOR AXIALLY SYMMETRIC CASE
SPHERICAL COOHDINATES
k :, I i 2 ' 3 k ; i
Ak X+2_ i! 0 0 _k _ 0
Bk
Ck
Th
_k
Ek
Fk
Gk
Hk
Ik
Jk
2p./R 2
0
0
0
0
2(X+2 )/R
0
0
-2( X+2_)/R 2
I
1 0
0
0
0
0
0
0
0
0
itoI
I°0
0
0
0
0
0
0
i 2 .3 kt ................
\
u k
\
\
\
A
o o _k
0
0
;,-'t,_+lJ,) / ._
0
0
0
-2( X.+3 IJ.)/R 2
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
_k
_k
_k
_k
_k
_k
_k
_k
Jk
....... ? .............
l i 2 3F ...........
0 0 0
0 0 0
0 0 0
0 0 0
0 0 0
0 0 0
0 0 0
0 0 0
0 0 0
0 0 0
Report No. 5654-02 FS Page GI5
![Page 168: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/168.jpg)
%
7%
F%
Y_
2%
TABLE G8
COEFFICIENTSOF STRESS_QUATIONSON AXIS OF
S_TR¥ (_ : 0) FOR AX_r,LY S:_XETEC CASE
SPH_aICAL C00RDINAT_,S
1 2
k+2_ _ k
0 . 0
j 0
2_/R 2(_ + _)/R
0 0
2X/R
0
0
0
0
0
0
2(x + _)/R
0
0
0
0
0
0
3
k
0
0
2(x + _)/R
0
2(_ + _)/R
0
0
0
0
0
0
4
0
_/R
0
0
k
0
0
-_/R
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
0
- -t ........
5 6
0
0
0
0
0
0
0
0
0
O
0
0
J. TEMPERATURE DEPENDENCE OF ELASTIC CONSTANTS
If, in addition to the coefficient of thermal expansion, the elastic con-
stants are strongly dependent on temperature, then additional terms must be included
in the displacement equilibrium equations to account for the special derivatives of
these constants. For example, in differentiating the stress component _.. withii
Report No. 5654-02 FS Page GI6
![Page 169: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/169.jpg)
_Tii
1
_0 _X _e.
- X _-_ + @ _. + 2# _-- + 2 eii _.1 i 1 i
5T 5- (Sx -_2_) _(T) _- _7. -
1 1
(3X + 2#)
T
_('_) dTT O
T
= O _ + 2 e..mm _ - (3X + 2k) G_ i
To
50 5e..ll
+ X _. + 2_ _--. - (3k + 2_) _(T) 5T1 1 1
(G21)
where the first three terms to the right of the equal sign have not been accounted
primed quantities, Equation (GI6) becomes
(A k + AI_.) _+52u + Bk), _+52u ... = (3X + 2#) CZ(T) 5T
T
_ 5 5m f a(T) aT, k = l, 2, 3
0
(G22)
' are tabulated below for spherical and toroidal coordi-The coefficients A_, Bk, ...
nates, and for the special point in spherical coordinates on the axis of symmetry
for the case of axial symmetry.
Report No. 5654-02 FS Page GI7
![Page 170: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/170.jpg)
TABLE G9
ADDITIONAL TERMS IN COEFFICIENTS OF EQUILIBRIUM EQUATIONS
FROM TEMPERATURE DEPENDENCE OF ELASTIC CONSTANTS
SPHERICAL COORDINATES
Ai
cl
El
-k
!
H k
I !
I k
!
Jk
k
--I
Ck
W,
E k
I F-;
k=l
0
0
0
0
0
0
(x+2_)
R
k=2
0
0
0
0
0
0
1 _ _T
R2s_n2 _ _ _-_ 0
0 0
0 0
0 0
0 , 0
0
0
0
0
8_ 8T
k=3
0
0
0
0
0
0
Rsin_ _Y
0
Rsing _
2 (_1 (_+_)_TR2_in¢
0
0
0
O
0
0
0
Report No. 5654-02 FS Page GI8
![Page 171: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/171.jpg)
TABLE G9 (cont.)
ADDITIONAL TERMS IN COEFFICIENTS OF EQUILIBRIUM EQUATIONS
FROM TEMPERATURE DEPENDENCE OF ELASTIC CONSTANTS
SPHERICAL COORDINATES
I
Hk
Ik
I
k =2
Jk
m
z%
----I
Bk
Ck
-----I
Dk
Ek
----!
Fk
G k
----I
H k
0
0
0
0
0
0
0
Rsin_ _
0
Rsin_ _ _-R
=I
Ik
R2sin2¢ _-8
0
0
0
0
0
0
R2sin¢
_gR sine
k=3
R2sin_ _
R2sin¢
cot@ (_T)(%.+2_)8TR2sin_
0
0
0
0
0
0
(_T) (_+2_)3TR2sin2_
'_ 1 8_ _T _ _T
I -__- R
Report No. 5654-02 FS Page GI9
![Page 172: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/172.jpg)
TABLEGIO
ADDITIONAL TERMS IN COEFFICIENTS OF EQUILIBRIUM EQUATIONS
FROM TEMPERATURE DEPENDENCE OF ELASTIC CONSTANTS
TOROIDAL COORDINATES
Ai
Cl
Di
El
O]K
-!
I k
Ji
B __!
A k
--I
Bk
I cD.| '
--!
D k
--!
Gk
k=l
0
0
0
0
0
0
OT" '_ -'-"_r
(a+rsin¢)2[_Y]_
0
0
0
0
0
0
k=2
0
0
0
0
0
0
0
sine [_k I_T
+ r(a+rsin_)_/_-'_
0
0
o
0
0
0
_ _T
ii ........
k=3
0
0
0
0
0
0
k_+rsin_ )IOT_ O_
0
(a+rsin_) _l_-rr
(a+rs in¢ ) 21 _"T-I ( X+2.1_
8k 8T
+ r(a+rsin#)
0
0
v
0
0
0
0
Report No. 5654-02 FS Page G20
![Page 173: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/173.jpg)
TABLE GlO (cont,.)
ADDITIONAL TEEMS IN COEFFICIENTS OF EQUILIBRIUM EQUATIONS
FROM TEMPERATURE DEPENDENCE OF ELASTIC CONSTANTS
TOROIDAL COORDINATES
=I
A k
=I
Bk
=I
Ck
=!
Dk
=I
Ek
=!
i
Ik
I
!
0
0
0
0
0
0
0
0
0
0
0
0
0
r(a+rsin¢) t_l_
r(a+rsin¢) I_I_
/ _'_"_'_I _'_'_
(a+rsin¢)= _u" IU_
(a+rsin_) 2
0
8_ 8T
(_+r_n_)21_l<x _m
_k
_ sin_ Ic_p.l_T _" ___T( _d_ _T leo___
, + ,,91_l_-_ -'(a+rsin¢)_r "si--"' _ 8_| r IJ
Report No. 5654-02 FS Page G21
![Page 174: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/174.jpg)
Ko AXIS OFSYMMETRYWITHAXIAL SYMMETRY
The only non-zero terms in the coefficients of Table G9 on the axis of
symmetry in the axially symmetric case are the following:
' _T aTaI = (x + 2_)y_
The integral term in Equation (G22) is also non-zero for the equilibrium
equation corresponding to k = i.
L. EQUATIONS FOR THE SINGULAR POINT, _ = O, FOR THE NON-AXISYMMETRIC CASE
The components of displacement u, v, w in the R, _, e directions, re-
spectively, have the following properties at _ = O:
8u a3u 8u
_w _3w = - 2 aev
= v ae2a---_ y_
_v a3v= 2
_._.= w _e2.-.-..-_ oeop
T
= o _ = _(T) aT
T O .2
(G23)
These results are derived beginning on page G26 of this appendix.
Report No. 5654-02 FS Page G22
![Page 175: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/175.jpg)
M. EVALUATIONOF STRAINS
From Equation (G23) the singular terms in the strain-displacement equa-tions can be evaluated. Thus we find
eee = R sin _ _+ [+ R _ --_0)[ l_l + uR
and from Equation (G23)we note that the bracketed part is IO) and thus we have the
result
Similarly we find
+ (G24)
ece= Z w cot_ + _i-_-y
and again through Equation (G23) we obtain
e_e = 2-_ - _ +
i _2v
(_: o)
(¢ : o)
(G25)
Finally,
N.
ere = 2--R _ - w + R
ere = 2--R - w + R
EQUATIONS OF EQUILIBRIUM
The equations of equilibrium
(_= o)
TRR i _TR(_ i _ TR8
-Y_-+[ -_+R_in¢ --_-+2_RR - 'I'_ - '1"@@+ TR_ cot
R=0
(G26)
(G27)
Report No. 5654-02 FS Page G23
![Page 176: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/176.jpg)
+ R + R sin _e + _R_ ÷ (_¢ - _ee) eotR
-0 (G28)
-y_- + _ +3'rRe + 2,','_e cot
R=0 (G29)
have the indeterminate parts indicated below.
From Equation (G27), we have
i 8TR@ TR_ cot
Rsin_ -_+ R(a3o)
Putting in the values of TR@ and TR_ in terms of displacements, we get
L '1
(G31)
From Equation (G23) we find that the expression (G31) is zero at _ = O. Thus we may
write, for Equation (G30)
+
which is the evaluation of the indeterminate portion of Equation (G27).
tion (G28), the indeterminate part is
From Equa-
R sin _ + R cot (G32)
In terms of the displacements
sin_ + v
Report No. 5654-02 FS Page G24
![Page 177: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/177.jpg)
From Equation (G23), the terms in parenthesis are zero. Thus we have
which is zero by Equation (a23). Therefore we may write Equation (G32) as
which is the evaluation of the indeterminate part of Equation (G28).
From Equation (G29) , the indeterminate parts are
and
R sin + 2 cot (a33)
(034)
For Equation (33) we have (at _ --_0)
+R sin _ - w R sin
i 0It can be seen from Equation (G23) that the terms with _ have the form
and that the terms in u and _ are zero. Thus we can write
ST@@ i I $2V
-_-+ 2 %_ :s 12_Y_+ (x+ 2_) _3w
83___Z_w+ 2 _---._,-/8e28_
= 0 by Equation (G23)
Report No. 5654-02 FS Page G25
![Page 178: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/178.jpg)
Thus we maywrite Equation (G32) as
For Equation (G34) we expand the functions in powers of _ thus:
w =Wo +Wl_+W2 _2+ "'"
Then we may write (for _ -_ O)
_ [w w +wlg+w2 _2=_ i +_2_ o _ +
_vO
w - by2o= 2W_ + W_ "_
_V
And since wO = _ from Equation (G23), we have
e_-+ e_-_ +e_-¢ 2/_
_v2 1
:w2+ e_- (¢:0)
i{_ _3v 1
: 7 * : o)
Thus, the one term, __m , in the equilibrium equations is not evaluated by simple
differentiation with respect to _.*/-
0. RELATIONS BETWEEN DISPLACEMENTS AT _ : 0
To obtain the equations given in Equation (G23), we take the gradient
and the Laplacian of the displacement vector, i.e.,
See note on page G28.
(a35)
Report No. 5654-02 FS Page G26
![Page 179: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/179.jpg)
and
v2Y = v2 (_u+ _ + g)
Expanding in powers of _ viz,
u = Uo + Ul _ + u2 _2 + ...
and letting { = --> 0 after obtaining _ and V 2 _, we find the foil owing terms in-
I
volving _ as a factor:
_V
_ o_r dO 0
R _02 + uI
0 _chO2 + 2 c_@ ,/
Since _7__ and _72 -_must be finite wheu _ : O, the above expressions (having 1. _ _ _ as
a multiplier) must all vanish. Thus we have
bw0
: - V 0
_V
O
O_- : Wo
Report No. 5654-02 FS Page G27
![Page 180: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/180.jpg)
_uO
$2 Sv I
Wl - 2_e2
_2v I Sw I
The equations in (G25) are e_ivalent to these when _ = O. The equation
where
T
To
can be seen from the fact that at _ : O, there is only one point for all @_ so that
cannot vary with 8. (The same argument could have been applied to the quantity u.
It could not be applied to w or v since these are functions which have extension in 8.)
III. DERIVATION OF THE FINITE-DIFFERENCE MODEL OF THE EQUATIONS
The finite-difference model of the basic equations is presented below. The
difference analogs to the partial differential equations are constructed on a grid
network as shown in Figure G2, for which _I - _i_o_ lines ............... -_s_s _v_ th_ sub-
script i, _2 : constant lines by the subscript j, _ = constant lines by the subscript
k, and the intersection of grid lines (nodes) by the triple subscript i_ j; k.
Note: The further evaluation of Equation (G35) may reduce the expression to a simple
derivation process, but such a possibility will not be investigated since the
expression has already been made determinate.
Report No_ 5654-02 FS Page G28
![Page 181: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/181.jpg)
Axis of Symmetry
Axis of Symmetry
j - i.
_ j+l
, • /
/ /_Q'_k 1
_s
k
-_k+l
k
Flg. G2 - Grid Notation for Finite-Difference Formulation
For the general case, the grid spacing will be irregular and the incre-
ments in the vicinity of a node will be designated by the following notations:
_l_: (_l)i+1" (%)i
h12--(_l)i+2- (_l)i
_13: (_l)i- (%)i-1
_x4: (_l)i- (_l)i-2
h21: (%)i+l- (_)i
I % g_' \
n22 = k_2Ji+2 - k,._2Ji
h23 = (%)i" (%)i-i
h31 = (_3)i+i - (a3) i
_132 _3Ji+2 _3'i
_33: (_3)i- (%)_-_
h34 = ((_3)i - (_3)i_2
Report No. 5654-02 FS
Page G29
![Page 182: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/182.jpg)
Let f (51, 52, 53) be any function of the coordinates such that it and its partialderivatives (up to any order required in the analysis) are continuous_ and expand
the function about the point i, j, k. Using a new coordinate system with origin at
i, j, k and with _i' _2' _3 directed along @i' 52' 53_ respectively, the function f(_i' _2' _3) is written
f (:i' :2 :3) = f + Bl:l + + + +' z, j ,k B2_2 B3_ 3 B4_I_2 B5_2_ 3
+ B6_3_ I + B7_I 2 + B8_22 + B9_32 + BI0_I_2_ 3
2+ BlZ_I:22 + B12:1_32 + B13:Z2:2 + Bl_:2:3 + ... (G36)
The first and second derivatives of f (@i' 52' 53 ) with respect to 51, 52, @3 are
obtained from Equation (G36) according to
i,j,k o,o,o)
o .9 _
= B4' _--_121 = 2 B7= BI' &_l &_21i_j,k i,j,k
i,j,k (o,o,o)
_2f I= % =2B 8
_f / = _f = B3, &a 3 6c_1 = B6, -- = 2 B9_7ti, j,k (o,o,o) i,j,k _c_32/i, j,k
By considering the values of f (_i' _2 _ _3 ) at the 12 nodes adjacent to i,j,k, the
constants B. are evaluated in terms of the function at these nodes and the gridz
spacings as shown in Figure G3.
(a3T)
Report No. 5654-02 FS Page G30
![Page 183: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/183.jpg)
2Node
q oI
Coordinate
12
(i+2,J,k)
(±-l,j,k)(i-2,j,k)(i,J+l,k)
(i,j÷2,k)
(i,J-l,k)
(_,j-z,k)(t,j,k+l)(i,J,k+2)
(i,j,k-1)
(i,j,k-2)
Fig. G3 - Coordinates of Irregular Mesh Intervals
Note that the grid spacing increments h.. do not, in general, have the dimensions of10
length but have the dimensions of Jl' _2 _ and _.
At points i and 3, Equation (G36) becomes
2
f(hll,o,o):f + +B_lli, j,k Blhll
f(-hl3,o,o): f. + B 1321,j_k - Blhl3
@38)
where terms of higher order are deleted. Solving for BI and B 7 from Equation (G38)
gives, for the first and second irregular central derivative with respect to _l'
= h132 fi+l,O, k (hll2 - h132) ;k
hllhl3 (hll + [_3i
" hll 2 fi-l;_;k
=2hl3fi+l,j,k
- (hll+ hl3)q,0,khllhl3 (hll + hl3)
i(a39)
li/
Report No. 5654-02 FS Page G31
![Page 184: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/184.jpg)
Substituting hll = h13 = hI into Equation (G39) gives for the first and second
angular central derivatives with respect to _i
Sf I fi+l,j,k - f"= z-l_j_k_2 i,j_k 2hlJ
$2f I fi+l,j_k - 2f. += z,j,k fi-l,$,k
$_12]i_j,k hl 2
(o4o)
By a similar procedure, the following first and second regular and irregular cen-
tral derivatives are obtained with respect to the coordinates _2 and 63:
First Regular Central Derivatives (h 2 = h21 = h23 , h3 = h_l = h3_ )
Sf I f" - f"z,j+l,k z_j-l,k (G41)_ = Phi
--2 !i.j,k
Sf 1 fi,j,k+l - f"= ,0,k-i (a 2)
_3 i,j_k 2h3J
First Irregular Central Derivatives
2 2 h212_f ' h2_-f" + ) fi, - f= z,j+l_k (h21 h23 j_k i_-l,k (G43)
i,j,k h21h23 (h21 + h23)
h_2 2 2 h312
_f_3) = fi,j,k+l + (h)l - h_3 ) fi, j,k - f',j,k-lz (G44)i,j,k h31h}3 (h}l + h33)
Second Regular Central Derivatives (h 2 : h2i : h23 _ h3 : h_l = h33 )
_2f ) fz,j+l,k - 2f. + f.
_ " z,j,k 1,j-l,k
_22 i,j,k h22
Report No. 5654-02 FS
(c45)
Page G32
![Page 185: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/185.jpg)
$2f I f. - 2f. + f.= m,j_k+l z,O,k z,j_k-i
_32Ii,j,k h32
(G46)
Second Irregular Central Derivatives
_2___I _ 2 Eh23fi,_+l,k- (h21 + h23 ) fi,j,k + h21fi,j_l,k_
_22Ii,j,k h21h23 (h21 + h23)
(G47)
_2-!f/ _ 2 [h3Si,j,_:+l+ (hi + b3) fi,j,_ + blfi,j,_-l] (a48)_ff32]i,j ,k h31h33 (h31. + h_3)
Forward and Backward Derivatives
By applying the same procedure as above with respect to two nodes located either
i._ _,__ • and second r_gl]lar and irregularforwer_ _r backward from the origim (i,j,_j, .... fmrst __ _
derivatives are obtained in terms of the function f(_1'__ _2' _3 ) evaluated at these
nodes. The results are summarized below for the three coordinate directions:
First Irregular Forward Derivatives
_f I - (h122 - hl12) fi,j,k + h122 fi+l,j,k - hll 2 fi+2,_,k
G_I i,j,k/ = hllhl2 (h12 - hll)(a_9)
2 _ h212 ) fi- (h22 ,j,k + h222 fi,j+l,k - h212 f':].,o+2,k (G50)
i,j,k h21h22 (h22 h21)
_f._.--I -(h322 - h312) fi,J, X + h322 f" 2= z,0,k+l - h31 fi,_,k+2 (G51)
%1 i,j,k h31h32 (h52 - hsl)
First Regular Forward Derivatives
For equal grid spacings in each of the three coordinate directions,
according to
defined
Report No. 5654-02 FS Page G33
![Page 186: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/186.jpg)
hll = h12/2 _ hI
h21 = h22/2 _ h2
_31 = _32/2 _ h3
(Q52)
Equations (G49) through (G51) reduce to
_f - 3fi,j, k + 4fi+l,$, k
i,j,k
- fi+2_j,k (G53)
- ]fi,j_k + 4fi,j+l,k - fi_$+2,k
,j,k
(_5_)
_ 5f±_O,k + 4_. _i,k+]-- #l, z,j ,k+2_
91].?g _L -#
(Q55)
Second Irregular Forward Derivatives
,j,k
= 2
_- hllhl2 _n12 - mllJ J
(Q56)
,j_k
=2 _ +(h -_ )f.-h22fi_j+l,k _ _22 _'21_ -m_, k
_---_121h22 (h22 - h21)
(a5T)
(G58)
Second Regular Forward Derivatives
With equal grid spacing_ according to Equation (G52), Equations (G56) through
(G58) reduce to
_2fl - 2fi+l,j_ + fi,j,____k+ fi+2,j,k
$_12_i, j ,k hl
Report No. 5654-02 FS
(G59)
Page G34
![Page 187: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/187.jpg)
_2__f.I - 2f. + f" + f" j+2,k= z,j+l,k m_j,k z,
_22/i_j,k h22
(G6o)
- 2f. + f" + f' $,k+2
_ m,j,k+l z,$,k z,
i,j,k h32
(G6I)
First Irregular Backward Derivatives
2h132 fi-2,j.,k + (h14 - h132) fi,j,k
h13h14 (h14 - h13)
h142 fi-l, j,k(G62)
,j,k
= h232 fi,o-2,k + (h242 - h232) fi,i,kh23h24 (h24 - h23
h242 f. z,j-l,k(063)
h33'2 2 h33'2 h 2fi,j.,k-2 + (h34 - ) fi,j_k 34
h93h34 (h34 - h93)
f°
z,j_k-i(G64)
First Regular Backward Derivatives (hl_ = h14/2 _ hi, etc.)
8%) = f±_2,j,k + 3#±,j,ki, j, k 2hl
- 4fi_l_, k(G65)
_ i_j-2,k i_j,k i,O-l,k
i,j ,k 2h2(G66)
8f____l f" +3f i -4f= z,_,k-2 _j_k i,j,k-i
i, j, k 2h5(G67)
Second Irregular Backward Derivatives
_12_2f ) = 2 I hl}fi-2'i,j,k
j,k + (h14 - h13) fi,0,k
h13h14 (h14 - h13)(G68)
Report No. 5654-02 FS Page G35
![Page 188: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/188.jpg)
=2h23fi,j-2,k+ (h24 - h23) fi,j,k_23h24 (h24 - h23)
(o69)
=2h33fi_0,k_ 2 + (h34 - h33) fi,O,k - h34 fi,0,k-i ]h33h34 (h34 - h33 ) J (aTo)
Second Regular Backward Derivatives
_2f I fi-2, j,k + f= i,j,k
_i 2ji,j,k h12
- 2fi_l,j, k(aT1)
_2f I = fl,j-2,k + fi,O,k - 2fi,0-l,k
_22ii,j,k h22
(G72)
_2f _ f. + f. - 2fl,j,k-2 z,j,k i,0,k-i
_321 = (G 73 )i,j,k h32
Mixed Derivatives
It can be shown from Equation (G36) that mixed derivatives require values of the
function at any six nodes in the vicinity of the point under consideration. Figure G4
shows various combinations of mixed derivatives with respect to the coordinate axes
_i and _2" It is noted that the mixed central derivatives involve the four corner
nodes as well as two adjacent nodes in either of the two coordinate directions. The
various combinations shown in Figure G4 are summarized below for the coordinate
directions Jl and 62:
Second Mixed Irregular Central Derivative with Respect to _i and _2
a) 1h21h23 (hll + hl3) (h21 + h23) 232 Ifi+l,j+l,k
-fi-l,j+l,k)- (h232- h2! 2) (fi+l,j,k- fi-l,j,k)
Report No. 5654-02 FS
2- h21 Ifi+l,j-l,k - fi-l,j-l,k (G74)
Page G36
![Page 189: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/189.jpg)
Central
Forward
Backwar_
Corner
_)
T
c)
e)
bh,,
P
O(Z
hi/
_03
f)
5
_ss
I.
(_Xi
A
_u
C_1
g)
.[_o< z
Fig. G4 - Irregular Mesh Intervals for Mixed Central, Forward
Backward, and Corner Derivatives
Report No. 5654-02 FS Page G37
![Page 190: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/190.jpg)
b) a2t" /hZZhl_ _ll + hl3) (h2:L + h23) 1,32 (f±+]_,j+l,k
2 hl12)
2
(fi-l,j+l_k - fi-i -l,k)]- hll _J
)m,j-l,k
(oT_)
Second Mixed Irregular Forward Derivative with Respect to _i and _2
c)
d)
i
h21h2) (hll - h12) (h21 + h2_) Ih232 Ifi+l,j+l_k
- - - h 2 (fi+l,j_l, kfi+l,j,_ fi+2,j+l,k + fi+2,j,k I 21
- fi+l_j,k - fi+2,j-l_k + fi+2,j,k
hllhl3 (h21 h22) (hll + h13) 132 (fi÷l,j+l_k
- f.m,j+l,k
- f.m,j+l_k
- fi+l_j+2,k
- fi-l,j+2_k
fi,j+2_k I - hll 2 (fi-l,j+l,k
+ fi,j+2,k) 1
Second Mixed Irregular Backward Derivative with Respect to 51 and G2
e)h21h23 {h13- h14) (h21 + h23) 232 Ifi_l,j+l,k
fi-2, j+l,k + fi-2,j _k
fi-l_j,k - fi-2,j.-l_k
h 2- fi-l_j_k) - 21 Ifi_l,j_l,k
I]l-2,j,k
(o_6)
(aTr)
Report No. 5654-02 FS Page G38
![Page 191: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/191.jpg)
_)-i lh
- *f" -f" 1fi+l,j-2,k ' z,j-2_k z,j-l_kh 2ii (fi-l, j-l,k
N- f. - + f II
z,j-l,k fi-l,j-2_k i_j-2,k U
Second Mixed Irregular Corner Derivative with Respect to 51 and (_-2
(G79)
_)_2f i lh= ll l.2hah22 (%2 - h21) 12h222{%+l.,j+l,k - fi+l,j,k
- f.z, j+l ,k
- f.z,j+2,k
+ fi,j,k} - hllh212 (fi+2,j+2_k
+ fi_j,k_
fi+2,j,k
@8o)
Second Mixed Regular Derivatives
All of the above results can be reduced to regular derivatives with respect to
either 51_ 52 or both coordinates by making the substitutions
h12 h14
hl/ : hl] - 2 - 2 = hi (a8l)
h22 h24 _
h21 : h25 = 2 - 2 : h2 (G82)
hI : h2 : h (a83)
The various derivatives are s14_m_marized below for the case in which all grid spacings
are equal (i.e., hI - h2)°
Report No. 565&-02 FS Page G39
![Page 192: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/192.jpg)
Second Mixed Regular Central Derivative with Respect to _i and _2
$2f ) _ ia)_ b) _i $_2 i,j,k 4 h2 Ifi+l'j+l_k - fi+l,j-l,k - fi-l,j+l,k + f'l-l,j-l,k I
(G84)
Second Mixed Regular Forward Derivative with Respect to _I and _2
_2f ) -i Ifi+l'j+l'kc) 8_i $_2 i_j,k - 2 h2 - fi+2,j+l_k - fi+l,j-l_k + fi+2,j-l,k} (G85)
_2f. I
i,j_k
- -i2 h2 {fi+l,j+l,k '" fi+l_j+2,k - fi-l,j+l,k + fi_l,j+2,kl (G86)
Second Mixed Regular Backward Derivative with Respect to _i and _2
$2f 1 _ i (fi-l, j+l_ke) __Ji,j,_ 2h2 - fi-2,j+l,k - fi-l,j-l,k l-2,j-l,k
f) $2f 1 _ i (fi+l, j-l,k_i _2}i,j,k 2 h 2
fi+l_j-2,k fi-l,j-l,k +f. }l-l,j-2,k
Second Mixed Re6ular Corner Derivative with Respect to _i and _2
g) li, ,k 2 I - fi+l,j,k- f.
l,j+l,k
Ifi+2,j+2,k - fi+2,j,k -' fi,j+2_k
(G87)
(G88)
(G89)
Report No. 5654-02 FS Page G40
![Page 193: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/193.jpg)
IV. DEVELOPMENT OF THIN SHELL MODEL FOR THIN LAYER AND
ITS FINITE-DIFFERENCE EQUIVALENT
A. THE THIN SHELL IN SPHERICAL AND TOROIDAL COORDINATES
The thin-shell analysis used here has been derived from a rigorous_
direct expansion in appropriate powers of z (the distance from shell center
surface). The equations are derived in the toroidal system since the spherical
case can be obtained from these by putting a = 0.
(a95).
Strain-displacement relations are shown in Equations (G90) through
i (_v v l_u)er_ = _ _rr - r + -r_ (G91)
i !m w sin _ + 1 _u ! (092)_r@ = _ l_Tr a + r sin _ a + r sin _ _-@
i _v u (G93)_ : r _ + r
¢@@ = a + r sin _ + u sin _ + v cos _ i (G94)
1 {1 _w 1 6v w cos _ ) (G95)_@:7 _r_+_ +r sin} _ a+rsin¢
Report No. !_654-02 FS Page G41
![Page 194: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/194.jpg)
Thus_
The stress-strain relations are as follows:
_ rr
_rr _ _ o_¢+ %0 +off
= s -_ _rr +%0 +os
!
¢00- E E r o-_
The first-order expansion is
r =p + z
i i z
r p 2P
z
ll = l_ +-- U 1o O
•._' f
P ,
! "• " // /
etc., including _, E_ G_ _ T since these are variables.
(G96)
(097)
(G98)
(G99)
(GIO0)
(GIOI)
\
\
Median surface
(not necessarily
center)
From Equations (G90), (G91), and (G92), we have
uI
rr po
(GI02)
Wherever terms are to be differentiated with respect to r and then combinedz
with first-order terms_ they must be carried to second-order in _, since thedifferentiation reduces the order by one.
Report No. 5654-02 FS Page G42
![Page 195: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/195.jpg)
Put
V_ V _Uo 1 o
_r_ o P P P
wI w sin _ _uo i o
_r@ p s sO
z
e¢¢: _¢¢o+-0 _¢¢ietc.
(s : a + sin _)
(alo3)
(aio4)
From Equations (G93), (G94), and (G95
_v ui o o
_¢¢o= _ _- * --P
i _Vl i _v uI uO o
o
_ O
=71 _Y_-+ _osin _ + v cos
o
_i : s - _- + _isin¢ + _icos¢
p sin _ i _Wo2 I- _-_- + u sin _ + v
S _ 0 0
cos¢)
aw w cos _ _vi o o i o
p a_ s s @_-_-
p + ]4 cos-- _ 0
s
(GI05)
Gi06)
OiO?)
GI08)
Gi09)
GIIO)
get_O-
i rr go i 0-_o +% i+_Ul = Pl E E I o o
_ o 0 0 O_
_tl (7o r_o
vI :v - + -o _ P G0
(Gill)
(GII2)
Report No. 5654-02 FS Page G43
![Page 196: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/196.jpg)
_UoI %%wI =P Wo sin _ + @_@-I + P G--_-
(all3)
For boundary stresses; second-order terms are needed because of
later differentiations.
2
z -IO- =(3- +-- O-- + I Z
rr rr° p rr I _p °rr2
{h)At upper and lower surfaces + _ , we have the pressures
- P2 : O-rro + _p _rr I + _r 2 (for upper surface)
h- P7 :o- G
rro 2P rrlo-
rr 2(for lower surface)
Thus,
= D
°-rrl (Pl P2 ) _h (GII4)
(pl + p2' (_12 (alzs)rr 0 2 ) 20;, Crrr2
For _r_' Gr@' in terms of the upper and lower shear stresses, it is seen that
: / - P-- (all6)
_r@ I : (T@I T@ 2_- (OZlT)h
(D1 + _'¢j /h /2%¢0 - * !_) %¢2 (Gll8)
T@ I + T@_I i__ 12
To put o-_ O + %@0 in Equation (Gill) in terms of displacements, use Equations
(GI00) and (GIOI); thus
Re)ort No. 5654-02 FS Page G44
![Page 197: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/197.jpg)
i- _ 2J
°i )÷O O O O
Using Equations (GI05) and (GI07), we have then
O
EO
i _v u %wo o i o
+%e 7_ -+-to o 0 s
o-rr
o
u sin _ + v cos _ 2_O O O
+ +=--- o- -25 Ts E rr o o
O O
+ 2_ TO O
(GI20 )
Then by putting Equation (GI20) into Equation (Gill), we get
uI -o +p_
i -_o _- + u° s
bw0
- @_--+U 0
(i- 2_)(io+ %)+_..
E (i - _)) o-rr +PO O O
(i+_} ]0
i _ %T- 00
(GI21)
Equations of equilibrium are as follows:
rr i i _C_r@
-_r +- - =0r a +r sin_ -_
+-- - : 0r a +r sin_
-57-r +- 7J- - =0r a +rsin_ -_
These result in six equations in zero-order and first-order terms; thus
_%_o p o
_rr I +--_ s _-_ : 0
%¢1 + -_-m -o
_¢5_° _%_O o
%_i +-_ s _- :0
(G122)
(Gi23)
(G124)
Repoz't No. 5654-02 FS Page G45
![Page 198: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/198.jpg)
2 o-
rr 2÷-_r--s _ _ -S -+ 2 _-_-_=o
S
2 %¢2
2_¢¢_ _ _o_% _¢¢o _ sin+_ - s-%_---%-g-+ 2
S
(a125)
O
-_ - 0 (G126)
(a127)
Equations (G99), (GI00), and (GI01) give o-_, _@, _8@ in terms of
the strains; thus
0-_ 1 - 9 2 ¢_ + _ ¢e@ i -9 + i_ Crrr (G128)
E
These relationships give six equations for the quantities cr_¢O 0"_¢1, etc. Thezero-order expressions are
o-_ ° : Equation (G128) with all quantities given zero subscript
(e.g., Eo, _o' 0_°' etc.) (GI_I)
O
= Equation (G129) with all quantities given zero subscript
, •(e.g., Eo, e¢¢o _o' ete ) (GI]2)
O
= Equation (GI]0) with all quantities given zero subscript
, •
(e.g., Eo, ¢_o C_°' etc ) (G133)
The first-order expressions are much more complicated. Thus,
Report No. 5654-02 FS Page G46
![Page 199: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/199.jpg)
E__) E 9 [ E10 o 0
2 ¢@@I + e +___2 ¢¢1 1-9 210 0 0
2 E0
(1-
+I EI_ ° E _)i (i +k) 2)]2 + o o
(1 - k) 2)2 _oi - _o o
E cz TI E oal T E1 _ T E c_ T k)IO O + O O O O O O oi- _ + i- _ +
1 - _)O O O (i - 9 )2O
]+ "i -'9 °-rrl + )2 o-(i Q rr- 0
E E k)O O O
l v 2 _dd1 +- i - 9 2 e@@ IO o
E1 2 E° o 91
+ 1-9 2+ 2)2(j-90 0 _
'¢¢o
+
X} 2 + 2)2 I eee(i - V _1 00 0
_, _ TI E %T El%_Oo o + o o+
i - 9 0 i - _)o 1 - 9o
+Eo % To 9z|
l
:Vo)2J
o ° ] 0
i
+ I o- + 90)2 o-]i _ _oj rrl (i rr- 0
( G155 )
E i E E _)IO O O
1 - Qo)2 ,0_@ 1 1 + 90 e¢@l + + 9o (1 + _ 0
(G136)
Equations (G!12), (Gl13), and (G121) are substituted into Equations
(G!06), (GI08), and (GII0); then Equations (Gl05) through (GIIO) are substituted
into Equations (GI31) through (G136). The resulting equations give _@@o' _@i'
_¢o' _i' G_@b' _@i in terms of Uo, uI, vO, Vl, Wo, Wl, _ro' _rl' _9o' _o"
Report No. 5654-02 FS Page G47
![Page 200: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/200.jpg)
Thus,
_¢o is obtained from Equations (GI05), (GIO7), and (GI31)(G137)
_i is obtained from Equations (GIO5), (GIO6), (GIO7), (GIOS),(GII2), (GII3), (GI21), and (G135). (Q138)
_@@ is obtained from Equations (GIO5), (GIO7)_ and (G132)O
(G139)
%@1 is obtained from Equations(G134),(GIO5), (GIO6),(GIO7),(G108), (azz2), (azz3), and (aZ2l) (al_)
_e ° is obtained from Equations (GI09) and (GI)])(G141)
is obtained from Equations (GIOg), (GllO), (GII2), (GII3),_@i and (GI}6)
When Equations (G137) through (G142) are substituted into Equations (G122) through
(G127), the result is six differential equations in the six quantities u ,O Vo_ Wo_
E_ ' _r ' etc. are already given in terms of surface stresses,°-rr2' _r_2' _r@2 rl o
Equations (GlZ4)through (Gll9)J. The corresponding equations for the spherical systemi
are obtained by letting a = O.
The first-order expansions of the tangential stresses are
(a143)
IZl _ku-_-P )
where _o' °-_l' _@ ' c_@@l" _e ' and o_@ 1 have been derived in Equations (G117)O O
through (G142). Substituting these equations into Equations (GI4}), (G144), and (G145),
the stress equations in toroidal coordinates are obtained in terms of u° _ Vo_ Wo, and
o- I
rr 2
Report Noo 5654-02 FS Page G48
![Page 201: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/201.jpg)
v0
11o
_ o o..__o
o
o + -
+ c2 _ - cl. o _ %
2 _2 1 _eo]sin _ u uo 1 o
o s " s 602 o
t# ol+ c:_ o -S- + _o%_
+ 21_l_c_I_suo
qs- °Ivz +. o,,..£_
+c 1 p ]]:L L
+ tl0
+ V0
+ (1-2%)(>%)!£_ o-E° 1- _)o rro
o
i 1+ p:_":P2- _ i-%)2J
Zero-
order
terms
First-
order
terms
_J
(G146)
Report No. 5654-02 FS
Page G49
![Page 202: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/202.jpg)
o
Fs.i_!_ pD__o] EaT
o 0 0
+ C1 + uL s o i-_)0
2_rr2
21 0 " 0 1A + 0+c 3 T¢-- cl. 2 o _¢2p C2 z o- e_-Go
_ C1 u +P- ___E+£-o s _e2 GO
P/ o pl---:v - _'--__l o T¢- ' o reO O
ps j o
0 Is (z-2%)(1* %1_--_o _d"rr
o
s_ ( sin+ L10 + II0
I .q rJL " '_J I../J
C'% "]
L'J L "oiL ._.1
z
P
Zero-
order
terms
First-
order
terms
/
(GI47)
Report No o 5654-02 FS Page G50
![Page 203: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/203.jpg)
Where
_V
oob_-+ c5W
O
c_v
oo;_-V-, c5 z
+C 6 !_] o
+GO
+ C5 s Wo
. 0 iTj--+- s
W o
_2U.
Wo
+l$u ol
_ o i
oJ
Zero.
Order
terms
First_
Order
terms
S = a + r Sin
E
CI = o___2___
0
C2E 2E OV_
=_+ 0 0 i
i- %2 (I- %%2
c 3
E U
0
%%h %%%c 4 = _ +o i - x)
o
E'(_T E_c_ T V+_+_
o (i. _ )20
@i5o)
(GiSl)
Report No. 5654.02 FS
Page GSl
![Page 204: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/204.jpg)
E
c5 = 1+5° (a154)o
E 1 E _;o i
C6 = i + _o (i + 4o)2 (G155)
B. THIN SHELL SOLUTION: FINITE DIFFERENCE FORMULATION
The generalized finite-difference analog formulation is directly applicable
to the thin-shell solution with the following changes: coordinate _lWill be eliminated
since it corresponds to the radial direction,* and subscript i will be dropped to con-
form with the above statement.
The finite-difference solution of the equilibrium equations will first be
obtained for the general case where the grid spacing is assumed to be irregular. Then
a solution will also be obtained for regular grid spacing. In both cases the first,
second, and mixed derivatives are needed for the central, forward, and backward grid
combinations. A typical general grid spacing is shown in Figure G5.
This coordinate
leliminated
hs_ _ h33
t I
Fig.G5 - Coordinates of Irregular Mesh Intervals
The partial derivatives in the equilibrium equations given in Equation (G36) are
taken with respect to _2 and _3 (¢ and e, respectively).
Report No. 5654-02 FS Page G52
![Page 205: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/205.jpg)
The increments in the vicinity of a node will be designated by the following nota-
tions, in accordance with Figure G5.
h21: (_2)i+l- (_2)i
h22: (_2)i+2- (_2)i
h23= (_2)i- (_2)i_I
h24= (_2)i- (_2)i_2
h3_: (%)i+l- (%)i
h32= (%)i+2- (%)i
%3 : (%)i - (%)i-1
h34: (%)i - (%)_-2
(G156)
From Equation (G36) it can be seen that f({l_ {2' {])' the function of the coordinates
with the origin at i, j, k, is
f({l' {2' {3) = f" + + + + + B5{2{} +z,j_k Bl{l B2{2 B3{] B4{I{2 B6{3{I
+ B7{I 2 + B8{22 + B9{32 + BIO{I{2{ 3 + BII_{22
+ BI2{I{ 2 + + BI 23 B13_12_-o _2_3 + ...
The first and second derivatives of f(C_l, 52, _3) with respect to 52 and (_3 are ob-
tained from Equation (G36).
Sf = _f :
i_j_k io,o_o i_j,k o,o,o
$2f _2f i = B5 _ $2f
o _22
_ _2f = 2B8 ,
_2f
O_2fI
- _-T-21 = 2B 9 (G157)i,j,k ()_3 o,o,o
The constants B. are evaluated in terms of the function at these nodes and the gridi
spacing as shown in Figure G5 by considering the values of f(gl' g2' g3 ) at the eight
Report No. 5654-02 FS Page G53
![Page 206: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/206.jpg)
nodes adjacent to j_k, and proceeding in a mannersimilar to that outlined on pages
G30 and GS!.
I. General Case - Irregular Grid Spacin_
a. Central Derivatives
I 2f + (h212
_f _ h2> j+l,k
_Y_2 j_k - h2ih25
P
h23-) f______k- h2!2fj-l,k
(h21 + h2})
(a158)
I 2 _ h332) fi
_f h3_2fj_k+l + (h31 . _ ,k
= t h3j,_ h_h_._ (h) 1 :5"
- h312f_,k_l(G159)
9i h_ - (fj+l,k+l - fj_l,k+Z)
(h552 2 _ f ) 2 )]- - h.51 )(fj+l.,k j-l,k - hs1. (fj,-_,k-1 fj-l_k-1 ._(Gz6o)
_2f i l [h__!j_k - h21h25 (h21 + h25)(hs1 + hss) _232 (fj+l,k+l - fj+l,k-1 )
- [h2_ - h2l "(_j,k+.i j_k-1 - h21 fj-l,k+Z - fj_l,k_l )]
2 ]h25fj+l,k_ (hgl + h2}) fj.,k
h21h2} (hpl _ h2))
÷h f l_]211j-z,
I
8c_521J
- b :)_).I,k*l [hsl PP" o,k
h)lhs) (h31 + h>_3)
-1
* h)lrj ,k-zJ
(GI6i)
(G162)
(oi 6_)
b. Forward Derivatives
h222fj+l,k - (h222 - hol 2) fj.,k
h21h22 (h22 - h2l)
9
- h21-fj+2, k(G164)
Report No. 5654-02 FS Page G54
![Page 207: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/207.jpg)
_ _,k+l
_n_3j, k -
2 9
h sih32 hR_] 2 - h.31)
- h312fj,k+ 0
(G165)
_2f I i
_lj,k = h31h3} (h2_h31 + h337 _332 (_'j<z,k+i " fj+l,k
j+S,k+.l + fj+2,k ) - h3L- (fj+l,k-1 fj_l,k -fj+2,k-1+ fj+2, k)_
(G166)
82f t _
- fj,k+l
- fj+l,k+2 + fj,k+2 ) - h21- (fj-l,ktl " fj,k+l - :fj-l,k+2+ fj,k+2) 1
(C167)
'52f J 2[--h2f + + ] f ,k+2]__ :_,k z (h32 - h3z" j k + hN/j8o_ 2i
.3 Ij,k h31h}2 (h}p - h31 ) (G169)
c. Backward Derivatives
r_-" l -h-P_fi_2"k + ['h2h " hps2) fj,k 2q- j-l,_, = - _ . - - h_l- f
.... (_i,7o)
_/ : h332fj'k-2
!j,k
+ (h3L2 [ _3 2) fj,a - h342fi,k...1
(Gi7i)
Report No, 5654-t,2 FS
Page C55
![Page 208: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/208.jpg)
+ fj-2,k - fj-l,k ) - h_l (fj-l,k-i - fj-l,k - fj-2,k-i + fj-2, (G172)
_2f I = __ i lhj,k h21h25 (hg} - h54--_hgl + h23 7 252 (fj+l,k-1 - fj+l,k-2
- " h 2 - - + _I+ fj_k-2 fj,k-i ) - 21 (fj-l,k-i fj,k-i fj-l,k-2 fj,k-2 ,j
(G173)
j, k
!--
2 mh2_rj_2,k . (h24 _ h23 ) rj, k
(h2L - h2 )(G174)
2 [h_fj,k_ 2 + (h34 - h33 ) f¢,k
h}_h34 _h34 - h33)
- h34fj,k_l](Gm?5)
, General Case - Regular Grid Spacing
When the grid spacing is regular_ then
i i
h2 = h2l = h23 = Zh22 =[_2_
I i
hi : h]l : hi] = _ hi2 : _ h]L_
(G176)
Substitutim_ the eooaitions of EQuation (G176) into Equations (G158)
through (Gi75) the first, second, and mixed derivatives for the central, forward, and
backward regular grid spacing combinations are obtained.
a. Central Derivatives
_f I fj+l,k - fj-l,k
I_2j,k 2h2(GITT)
Report Noo 5654-02 FS Page G56
![Page 209: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/209.jpg)
(G178)
k = h2_3 j+l_k+l - fj+l,k-i - fj-l,k+l(GZTg)
j,k = h_ j+l,k - 2fj,k
(ozSo)
_cz32 I J ,k h32 j, k+l j., k , k-
(G18Z)
b. Forward Derivatives
_f I = i _fj+l,k- 3fj_- fj+2_k]_2 j,k 2h-_ k(G182)
j,k_ l 14fj k j,k+212h3 ,k+l - 3fj, - f
(az83)
= 2h2h _ j+l,k+l - fj+2,k+l - fj+l,k-i + fj+2,k-(oz84)
-i _ fj _ fj + fj_l,k+212h2h 3 j+l,k+l +l,k+2 -!,k+l(Gz85)
= h_ 2fj+l'k + f"j,k + fj+2, kl
(G186)
Report No. 5654-02 FS Page G57
![Page 210: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/210.jpg)
k = i____h32E 2fj'k+l + fj,k + fj,k÷21(G187)
C. Backward Derivatives
E J_f = 1 - 4fj,k 2h--_ j-2,k + 3fj,k j-l,k
(al88)
_f' _l_ -4f J_31j, k - 2h--_ j,k-2 + 3fj,k j,k-(G189)
-i Ifii,,.
2h2h3 LJ-l'k+l fj-2,k+l - fj-l, k-i + fj_2,k_ll(GI90)
_2f i _ -1 if 2] (GI91)
_2f i 1 _ fjj,k-2 ,k
_32 j,k h32- 2fj,k_l] (G193)
Vo OVERALL THREE-DIMENSIONAL BOUNDARY CONDITIONS
Given the notation and equations previously developed, and with Figures G6a,
G6b, and G6c illustrating the geometry involved, the following described boundary and
..... ÷_k_7_÷ ..... a_+{m_ _ hhn_e which will _overn the solution to the full three-
dimensional heat shield problem for the two significant cases ("fixed" and "free-free"
conditions, respectively, at the structural juncture surface).
A. On inside and outside boundary surfaces OB and IB for both cases:
Trr = Tr_ = Tr@ = 0
Report No. 5654-02 FS Page G58
![Page 211: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/211.jpg)
B. On interface surfaces Ii and 12 for both cases (index denotes which
material mediumis indicated):
\
i = 1,2
C. In the r - _ plane for which @ = 0° for both cases:
W --
8e 2 - _--@-= _ = o
D. In the r - _ plane for which @ = 90° for both cases:
u(r,_,90 °) = u(r,-_,90 °)
v(r,_,90°) = v(r,-_,90 °)
w(r,_,90 °) = .-w(r,-_,90 °)
Report No. 5654-02 FS Page G59
![Page 212: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/212.jpg)
E. On the structural juncture plane (SJ) for the "fixed" case:
U = V =W = 0
F. On the structural juncture plane (SJ) for the "free-free" case:
'1"_ = Tr_ = ff'@_ = 0
G. Along the circles at the intersections between the structural juncture
plane and each interface surface for the "free-free" case (IPI, IP2), the conditions
of Condition F are replaced by (index denotes which material medium is indicated):
V]i+l = _rVli
+
li -I+ 3+ ad - 3+ O_T =O
T TL_ 0 I.._ 0-_ ±_± L_ -- _i
i = 1,2
H. Along the circles at the imtersections between the structural juncture
plane and each of the boundary surfaces OB and IB for the "free-free" case (PI,PO),
the normal stress condition (T_ = O) of Condition F is replaced by
_u _v
u=r_rr- _
Report No. 5654-02 FS Page G60
![Page 213: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/213.jpg)
AB is edge view of planeof temperature and thickness
distributional symmetry.
\\ o
\
\oo \" \
e=9°° !
B
Fig. G6a - Front View of Shield
OB
OB
Fig. G6b - Cross section of Shield
PO
Fig. G6c - Portion of Structural Juncture Surface SJ
Definitions:
r - Radial direction (both sphere and torus)IB - Inside boundary surface
OB - Outside boundary surface
SJ - Structural Juncture plane
IP1, IP2 - Intersections between the structural Juncture plane and eachsurface interface
PI, PO - Intersections between the structural juncture plane and each
of the boundary surfaces OB and IB
Report No. 5654-02 FS Page G61
![Page 214: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/214.jpg)
VI. PROGRAMING OF THE FINITE-DIFFERENCE MODEL(S) AND ATTEMPTS TO SOLVE THEEQUATIONS BY THE OVER-RELAXATION APPROACH AND BY DIRECT MATRIX INVERSION
A. OVER-RELAXATION APPROACH
The first approach in an attempt to solve the displacement and stress
equations was point relaxation. The reason for this choice was the apparent success
of this method in the previous work by Morgan and Christensen. Repeated attempts
with different values of the over-relaxation experiments were not successful. Evi-
dently the reason for the difficulty in point relaxation was the incapability of this
method to bring in the effects of boundary conditions.
An alternative form (i.e., line relaxation) was then attempted. The
first trial with line relaxation was made utilizing a radial line to the boundary.
Repeated attempts were made with this method with various boundary conditions. It
was demonstrated that this method is also incapable of meeting the remaining
boumd_ly cmliuLb±uLio. A "_ __'- "
that all boundary conditions could not be met simultaneously; the solution diverged
as it proceeded radially outward.
The basic difficulty in these methods seems to lie in the formulation of
an acceptable and consistent system of boundary conditions. Similar difficulties
have been reported in the literature for very much simpler cases.
B. DIRECT MATRIX IICV-ERSION
A second approach (i.e., direct matrix inversion) was then attempted. Due
to the relatively small size of the computer memory, the mesh size was too large to
achieve a successful solution. However, direct matrix inversion cannot be ruled out
as a method for the solution of this problem. It should be noted that the very
short time allotted to the attempts at the solution using relaxation and direct in-
version methods did not allow a complete exploration of these procedures.
VII. ALTERNATIVE METHODS AND RECOMMENDATIONS
Additional methods for the so±utlon of the complete non_xi_y_H_1_L_lc c_ w_
investigated. It was determined that the possibility exists for a direct matrix in-
version solution of the whole problem provided machine language is used throughout for
the programing. An additional memory capability utilizing magnetic tape or memory
disks would be employed.
Report No. 5654-02 FS Page G62
![Page 215: Q G VONKARMANCENTER - NASA · @ q g_ vonkarmancenter thermal strain analysis of advanced manned spacecraft heat shields final report to national aeronautics and space administration](https://reader030.fdocuments.in/reader030/viewer/2022041221/5e0b40ee1c968d1a9c244f02/html5/thumbnails/215.jpg)
A second approach was also investigated which would utilize equivalent analog
circuits to transform the equations into a set_ the behavior of which is well known.
This approach seemsto offer another possibility of solving the complete three-
dimensional nonaxisymmetric problem.
Report No. 5654-02 FS Page G63