m CR7J*G ,uc- THE AEROELASTIC CHARACTERISTICS OF THE ...

m C R 7 J * G ' ,uc- THE AEROELASTIC CHARACTERISTICS

LAUNCH VEHICLE OF THE f lAlURH4B f $1-201

Q 1 III i 1 R c I

M-37-65-2

THE AEROELASTIC CHARACTERISTICS OF THE SATURN-IB

SA-201 LAUNCH VEHICLE

August 1965

Aero-Hydrodynamics

Checked By: Lars-Eric Ericsson Flight Technology

APPROVED: M. Tucker, Manager Flibt Technology

Prepared Under Contract NAS €3-11238 for

Aerodynamic Division Aero-Astrodynamics Laboratory

George C. Marshall Space Flight Center National Aeronautics and Space Administration

Huntsville, Alabama

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I LOCKHEED MISSILES & SPACE COMPANY

M-37-65-2 r

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SUMMARY

The flow environment surrounding the Saturn IB SA-201 vehicle is dominated by

regions of separaied fiow in the transonic ?via& number range. The highly nm-hear

loadings resulting from flow separation coupled with the modal deflections of a long

flexible vehicle as the SA-201 have a dominant influence upon vehicle dynamics. A

quasi-steady method requiring an experimental static load distribution a s inplt has been used in analysis of the SA-201 vehicle to obtain the aerodynamic damping for the first three bendmg modes. The analytical results indicate that the SA-201 vehicle is aerodynamically damped over the critical Mach number range (0.8 5 M 5 2.0) and

therefore is expected to be damped over the entire ascent Mach number range.

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LOCKHEED MISSILES & SPACE COMPANY

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CONTENTS

1 1

Section

SUMMARY

ILLUSTRATIONS

NOTATION

1 INTRODUCTION

2 SATUFtN-IB SA-201 ANALYSIS

2.1 Static Aerodynamic Analysis 2.2 Aerodynamic Damping Analysis

8 c 3 CONCLUSIONS

4 REFERENCES

Appendix

iii

vi i

ix 1- 1

2- 1 2- 1 2- 1

3- 1

4- 1

A DOCUMENTATION OF SA-201 LUMPED LOADS

I A-1

V


ILLUSTRATIONS

Figure

2-1

2-3

2-3

2-4

A-1

A-2

A-3

A-3

A-4

A-5

A-6

A-7

SA-201 Configuration

Cexnprisco ef S4-201 Integrated Lumped Lwds with Force Dzta Results at a = 0

Comparison of Saturn-lB and SA-201 Damping Characteristics atcr=O SA-201 Aerodynamic Damping

SA-201, Definition of Lumped Normal Force Vectors

SA-201 Local and Forebody-Dependent Command Module Loads atcr=O SA-201 Local Normal Force Derivatives at (Y = 0

SA-201 Local Normal Force Derivatives at Q! = 0 (Cont. )

SA-201 Induced Normal Force Derivatives a t (Y = 0

SA-201 Lumped Load Centers of Pressure at a = 0

SA-201 Local and Induced Command Module and Flare Axial Force Moment Derivatives a t a = 0

SA-201 Separated-Flow Velocity Ratios a t (Y = 0

LOCKHEED MISSILES 8c SPACE COMPANY

2-3

2-4

2-5

2-6

A-2

A-3

A-4

A-5

A-6

A-7

A-9

A- 10

I

C

D~~~ M

m

P

4 S

N

CY

P

W

U U

P

-

e

~

M-37-65-2

NOTATION

2 force coefficient = Force/pm (um/2)S

Mach number

generalized mass (kg - sec2/m) 2 pressure @g/m )

dynamic pressure (kg/m2)

-caFnvnllc.cI L CLCl CUCU I€ag?il (6.5278 El for Saturii-fB w-201)

reference area = ?rD &F/4 (m2) angle of attack (deg or radian)

density (kg-sec2/m4)

free-free bending frequency ( r a d i d s e c )

velocity (m/sec) average velocity (m/sec)

equivalent spike deflection angle (deg or radian)

rotation angle (deg o r radian)

Subscripts

m pitching moment (kg-m)

N normal force (kg) S separated flow 00 undishrbed flow

Super scripts

i induced, e. g. , AiCN = separation induced normal force coefficient


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33-37-65-2

Section 1

INTRODU C TION

The present study of the Saturn JB SA-201 vehicle has been conducted in support of the

&brirn Fiqg-am ii; py-j~id% & ~ @ g &zac&ris;%cs; f ~ r in&i~;id~si fQ$t cecf@Lrg-

tions as required. The resuits presented herem provide the damping cnaracreristics,

in percent of critical, for the Saturn E3 SA-201 launch vehicle. As is characteristic

of the Saturn IB series, SA-201 is a long flexible vehicle over which large regions of separated flow exist in the transonic Mach number range. The highly nonlinear aero-

dynamic loads resulting from flow separation are known to considerably influence the

damping characteristics of such vehicles. A quasi-steady analytical method, described

in Ref. 1, which includes the effects of separated flow has been applied in the present

study to determine the SA-201 damping. The following section, in two parts, describes

the static aerodynamic loads used in the quasi-steady analysis and contains a discussion

of the damping results for the SA-201 vehicle.

1-1


I

Section 2

SATURN IB SA-201 ANALYSIS

2 . 1 STATIC AERODYNAMIC ANALYSIS

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M-37-65-2

I 1

A s is characteristic of the Saturn IB series vehicles, the Apouo payioaci is responsive

for the major effects of flow separation on the SA-201 vehicle. (See Fig. 2-1. ) The

escape-rocket wake represents the most prominent single region of flow separation

Furthermore, due to the large modal deflections occurring a t the forward portion of the

vehicle, the Apollo-payload has a significant influence on the vehicle damping. Subse-

quently, the analytic and ewr imen ta l effort was in great part directed toward obtaining

an accurate description of the loading over the Apollo-payload portion of the vehicle.

The static aerodynamic load characteristics for SA-201, presented in Appendix A, cor-

respond to the Saturn-IB characteristics presented in Ref. 2. A small difference in

length of the lunar excursion module, on the order of 2 .5 percent, has no measureable

effect on the static load characteristics and thus the inclusion of the results of the

Saturn-If3 analysis is expedient. Within the Saturn-IB analysis, pressure data were

correlated with segmented force data such that the magnitudes of the ill-defined negative

load peaks were varied until agreement with force data was achieved for both normal

force and center of pressure. Experimental data used in the analysis were obtained

from Refs. 3 through 16. Excellent agreement between summed, lumped force distribu-

tions and overall force data for SA-201 is shown in Fig. 2-2.

2 . 2 AERODYNAMIC DAMPING ANALYSIS

The damping derivatives obtained as a result of the quasi-steady analysis may be con-

fidently discussed by considering the geometric and elastic characteristics of the

vehicle in relation to the loadings generated by the surrounding flow. The static load

2-1


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8

M-37765-2

distribution provides a knowledge of the location and magnitude of the important non-

linear loads resulting from flow separation.

tics of the vehicle constitute the primary factors influencing the equivalent damping

distribution resulting from the quasi-steady analysis.

This coupled with the modal characteris-

The SA-201 damping, as in the case of the Saturn-IB of Ref. 2, is most heavily

influenced by the Apollo command module. occur for this portion of the vehicle. As seen in Fig. 2-3 the damping curves at Q! = 0' for Saturn-IB and SA-201 are very similar for all three bending modes. In

the first mode SA-201 exhibits slightly smaller command module deflections causing the damping to fall below that of the Saturn-ZB.

relate primarily to the smaller critical damping factor, -pUsoS/4wG , for the SA-201

vehicle.

were taken from Refs. 17 and 18. The results of the SA-201 analysis a re indicated in

Fig. 2-4 which presents the damping in percent of critical for 0, 4 and 8 degrees angle-

of-attack, In all cases SA-201 exhibits positive damping characteristics indicating

that the vehicle is dynamically stable.

Large loadings and large modal deflections

Second and third mode differences

The modal characteristics and trajectory information used in the analysis

2- 2

LOCKHEED MISSILES & S P A C E COMPANY

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1 2-3

M-37-6 5-2

T 4 0 cu

I s rl

I @a


w I I-

I- O

10

M -37 -65-2

REF. DIA. = 6.5278 h

0 FORCE DATA; REF. 12 A INTEGRATED LUMPED LOADS

1 I I I 1

1 I I I I 0.8 1 .o 1.2 1.4 1.6

MACH NUMBER 1.8 2.0

Fig. 2-2 Comparison of SA-201 Integrated Lumped Loads with Force Data Resul ts a t Q = O

2 -4


R I I I 1 I 8 8 I I I t 8 8 R I 8 I I

! 1 I 1 '1

0.8

0.4

1.2

-

3RD BENDING MODE

-

0.E

0.4

z UJ 0.4 2 n w Y

-SATURN 1B

2ND BENDING MODE

Fig. 2-3 Comparison of Saturn 1B and SA-291 Damping aaracteristics at =O

2-5


M-37-65-2

0.8

0.4

I 1 I I I

2ND BENDING MODE

0 I I I I I

0.8

0.4

0

3RD BENDING MODE -

-- - ---- -- 8 1 .o 1.2 1.4 1.6 1.8 2

MACH NUMBER

Fig. 2-4 SA-201 Aerodynamic Damping

2-6


M-37-652

0

8

Section 3

CONCLUSIONS

The Saturn-IB SA-201 vehicle has been sludied using a quasi-steady analysis to deter-

mine he damping &;irackri&ics. i*esdts h-L&czte h\& M-201 is ~ ~ y & ~ ~ ~ ~ f i J v

damped over the critical Mach number range (. 8 5 M 5 2.0) for the first three bending

modes. It may be concluded that the vehicle will be damped throughout atmospheric

ascent.

3-1


Section 4

REFERENCES

1. Lockheed Missi les & Space Company, Report on Saturn I - Apollo Unsteady Aerodynamics. by Lars-Eric Ericsson and J. Peter Reding, LMSC A650215, c,8&9~*~m.r&, cssf., FCt ; 1964 (E)

2. ----- , The Aeroelastic Characteristics of the Saturn IB and Saturn v Launch

Vehicles, by Iars-Eric Ericsson and J. Peter Reding, LMSC M-37-65-1, Sunnyvale, Calif., March 1965 (U)

3. NASA Ames Research Center, Turbulent Boundary-Layer Separation Induced by Flares on Cylinders at Zero Angle of Attack, by Donald M. Keuhn, NASA TR R-117, Moffett Field, Calif., 1961 (U)

4. Jet Propulsion Laboratory, California Institute of Technology, The Fluctuating Pressure Field in a Supersonic Turbulent Boundary Layer, by A. L. Kistler and W. S. Chin, TR 62-277, Pasadena, Calif., Aug 1962 (U)

Brown Engineering Company, Inc. , Wind Tunnel Investigation to Determine

Transonic Stabilitv Characteristics on a 0.8117 Percent Scale Model of the

5.

Saturn IB and V Upper Stages with Several Service Module Lengths and LEM

Adapter Angles, by W. Dewayne Radford, Tech Memo AA-8-64-1, Huntsville,

Ala, 3 Aug 1964 (U)

6. --__- , Wind Tunnel Investigation to Determine Transonic Stability Character-

istics on a 0.8117 Percent Scale Model of the Saturn IB and V Upper Stages

with Several Service Module Lengths and LEM Adapter Angles; Series II, by

W. Dewayne Radford, Tech Memo AA-11-64-9, Huntsville, Ala, 30 Nov 1964

(U)

7. The Boeing Company, Saturn V Upper Stages Pressure Distribution W/APS

Units Lonrritudinal Pressure Distribution and Local Normal Forces for Future

Studies in S-II and S-IVB Region of Separation (0.505% Scale), by J. Wright,

Project AD-5-63, 6 Apr 1964 (U)

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8.

9.

10.

11.

12.

13.

14.

15.

16.

M-37-65-2

NASA Marshall Space Flight Center, Wind Tunnel Investigation to Determine the

Effect of an Axial Rod in the LES Tower on the Static Longitudinal Stability

Characteristics of the Saturn IB Upper Stage Components, by William C. Pope,

J r . , MSFC T N AA-12-64-1, 3 Dec 1964 (U)

Chrysler Corporation, Space Division, Static Pressure and Normal Force Co-

efficient Distributions on the Saturn IB Launch and Aborted Launch Configura-

tions as Determined by Wind Tunnel Tests, by F. Chianese, J r . , TN-AE-63-12,

New Orleans, La, 30 Dec 1963 (U)

----_ , Results of a Wind Tunnel Investigation to Determine the Pressure and

Local Normal Force Distribution Over the Saturn IB Vehicle, by H. B. Reese,

TN-AE-63-3, New Orleans, La, 1 Aug 1963 (U)

----A , Unpublished Data for Wind Tunnel Tests Described in "Test Plan to

Determine the Stability and Axial Force Characteristics of the Saturn IB Launch

Vehicle and Components,

16 Nov 1964 (U)

by F. Chianese, TN-AE-64-61, New Orleans, La,

NASA Marshall Space Flight Center, Static Longitudinal Stability and Axial

Force Characteristics of the Saturn IB/Apollo Launch Vehicle as Determined

from Tests of a 1.32 Percent Scale Model at Langley Research Center, by

J. Johnson, MSFC Memo NR: R-AERO-AD-64-94, Huntsville, Ala, 15 Oct

1964 (U)

----- , Experimental Static Longitudinal Stability and Drag Characteristics of

the Saturn IB/Apollo Vehicle, by Robert E. Pitcock, MSFC Memo NR: R-AERO-

A-108-63, Huntsville, Ala, 7 Oct 1963 (U)

Cornel1 Aeronautical Laboratory, Transonic Wind Tunnel Tests of a .0175 Scale Pressure Model of the Saturn C-1, Block I1 Launch Vehicle, by D. L. Millikan,

Cornel1 Report No. HM-1510-V-8, Buffalo, N.Y., 1 Jul 1963 (u) Lockheed Missiles & Space Company, Preliminary Data Release for the Tran-

sonic Wind Tunnel Tests of the Saturn-Apollo 5% Model, by J. P. Reding, LMSC/802367 (TM 53-40-122), Sunnyvale, Calif., Nov 1962 (U)

----- , Preliminary Data Release for the Supersonic Wind Tunnel Tests of the

Saturn-Apollo 5% Model, by J. P. Reding, LMSC/802393 (TM 53-40-123),

Sunnyvale, Calif., Dec 1962 (U)

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M-37-65-2

17. NASA Marshall Space Flight Center, Bending Vibrations, First Stage Saturn IB, Vehicle 201, by George F. McDonough, Memo No. R-AERO-DD-14-65, Hunts- ville, Ala. , 19 Jan 1965 (U)

9 SA 201 Launch Vehicle Reference Trajectow, by J. W. Credn 18.

and W. M. GilES: TM)(-5.?242, H1l&gy:uea -Ala; , 1s !?+'Til 1965 (c.1

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M-37-65-2

Appendix A

DOCUMENTATION OF SA-201 LUMPED LOADS

The a = 0' , lumped load representation used in computing lhe SA-201 damping is documented in this ApLDendix, Figure A-1 r e l a t ~ e the hmped back tc &e g e r e r d fi-231 force &tzib-utiGrl. ZG*, 'leal iiid-uced lump& ar.e pi"ii& in Figs. A-1

through A-4, and their centers of pressure appear in Fig. A-5. Figure A-6 presents

the local and induced axial force moments on the command module and interstage

flares, and Fig. A-7 shows the velocity ratios for each of the separated regions.

A-1


M-37-65-2 8 v, Z

VI k 0 JJ 0 Q) 3 Q) u k 0 Lc

a Q)

4 4 w 0

c 0 a d JJ

4 I 4

b;, *rl k

A-2 1 1 LOCKHEED MISSILES & SPACE COMPANY

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Id I 1 I 1 I I 8

i .a

0.8 - 0.6 d

2 s Z U

E

0" 0.2

c a L &

Lu

Y 0 LL

2 5 0 c Z

4.2

-0.4

0.8

8 I

1 .o 1.2 1.4

k C H NUMBER 1.6 1.8 2.0

F i g . A-2 SA-201 Local and Forebody-Dependent Command Nodule Loads at 01 =O

I A-3

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M-37-65-2 1

Z- V W 1.2

0.8

0.4

0

-0.4

-0.8 0.8 1 .o 1.2 1.4 1.6

MACH NUMBER

F i g . A - 3 SA-201 Local Normal Force Derivatives at a! =O

A-4


1.8 2.0

1 8 II

8 1 1

1 1 1 1 1

8 ~1 ,I I II 0 I 8 8 8 8 8 1 1 II S 1 il 8

M-37-65-2

4.0

3.6

3.2

2.8

2.4

2 .o

t

0.4

0

-0.4

0.8 1 .o 1.2 1.4 1.6

MACH NUMBER

F i g . A - 3 SA-201 Local Normal Force Derivatives at a =O 1 (cont.)

A-5


1.8 2.0

0.4

0

v Z U 0

e -0.4

1.2

0.E

0.4

0

-0.4

-0.8

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0.8 1 .o 1.2 1.4 1.6 1.8 2.0 MACH NUMBER

Fig. '4-4 SA-201 Induced N o r m a l Force Derivatives at Q! =O

A-G


I I I 1 I 1 8 I 8 I u 1 8 I 1 8 I 8 8

8

8 8 8

0 t 0 hl

M-37-65-2 .

0 0 0 t f QD

t s: 0 9 t

13131H3A

Fig. A-5 SA-201 Lumped Load Centers of Pressure at * =O

A- 7

1 1 I 8 I 8 I

M-37-65-2

0

-0.04

-0.08

-0.12 0

-0.04

-0.08

-0.12 0.8 1 .o 1.2 1.4 1.6 1.8 2 .o

M4CH NUMBER

Fig. A-5 SA-201 Local and Induced Comand Module and Flare Axial Force Moment Derivatives at cy =O

A-9


0.8 1 .o

M-37-65-2

.2 1.4

MACH NUMBER

.6 1.8 2.0

Fig. 21-7 :';X-231 Separa ted-Flow Velocity Xatios at Q! =O

A-10


t'

THE AEROELASTIC CHARACTERISTICS OF THE SATURN-1B

SA-202 LAUNCH VEHICLE

(Addendum to LMSC Report M-3'7-65-2)

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k&MBKHEED MlSSiLES & SPACE COMPANY ?

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ADDENDUM

Analysis of the Saturn IB SA-202 Launch Vehicle

The results of the SA-202 damping analysis a re presented herein as an addendum to

LMSC report M-37-65-2.

structural characteristics of the Saturn IB vehicle between the flight vehicles SA-201

and SA-202, both the aerodynamic characteristics, presented in Appendix A, and the

structural characteristics documented in Ref. 17 and 18 for SA-201 vehicle apply as

well to the SA-202 vehicle. The launch trajectory data, secured from Ref. 19, has

been used in the calculation of the damping characteristics presented (in percent of

critical) in Fig. 1 of this addendum. It is observed from the quasi-steady method

that perturbations in launch trajectory will affect only the relative magnitude of the

damping and will not change the sign. This is confirmed by the results in Fig. 1-ADD

which predict positive damping for the SA-202 which is characteristically similar to the

SA-201.

atmospheric ascent.

Since there have been no changes in the configuration or the

It is concluded that the SA-202 vehicle will be dynamically stable throughout


c *

1.2

0.8

M-37-65-2

Q = 00 o! = 4 O ----

-.- a = 8 O - *\ h

a G 8 t

I! !=

Y

Y

5 (3 Z

4 a n

0

1ST BENDING MODE

1 I I I I

O l I I I I I

0.8

O S 8 t

* -

2ND BENDING MODE

3RD BENDING MODE

0.8 1 .o 1.2 1.4 1.6

MACH NUMBER

1.8 2.0

*

Fig. 1-ADD SA-202 Aerodynamic Damping


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M -37 -65-2

17. NASA Marshall Space Flight Center, Bending Vibrations, First Stage Saturn IB, Vehicle 201, by George F. McDonough, Memo No. R-AERO-DD-14-65, Hunts- ville, Ala. , 19 ;Tnn 1965 (U)

19. Marshall Space Flight Center/Manned Spacecraft Center, Joint MSFC/MSC SA-202/ AFRM 011 Reference Trajectory, Document No. 65-FMP-1, Huntsville, Ala. / Houston, Texas, 12 April 1965 (C)

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