Lecture #6 Normal stresses in thin-walled beam
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Transcript of Lecture #6 Normal stresses in thin-walled beam
Lecture #6Normal stressesin thin-walled beam
FOREWORD
2
The calculation of stresses in the wing is generally a statically indeterminate problem, involving three basic mechanical equations: equilibrium, compatibility, constitutive.
BASIC EQUATIONS OF SOLID MECHANICS
3
Equilibriumequations
Constitutiveequations
Compatibilityequations
This is not only the sum offorces or moments, but appliesfor elementary volume as well
Physical law, expressesthe relation between
stress and strain
Solid body shouldremain continuous
while being deformed
WAYS TO FIND NORMAL STRESSES IN THE WING
4
There are two major possible ways:
1. General energy-based methods for statically indeterminate problems (effective only for some specific problems). E.g.: Papkovich theorem (will study later).
2. Beam bending theory, accordingly modified to take account of the physical law.
WAYS TO SOLVE A SOLID MECHANICS PROBLEM
5
Displacements are set as unknowns
Strains are derived
Stresses are derived
Compatibility equations
Constitutive equations
Equilibrium equations are
solved
Equilibrium equations
Stresses are set as
unknowns
Strains are derived
Constitutive equations
Equilibrium equations
Compatibility equations are
solved
Compatibility equations
BASIC EQUATIONS IN BEAM THEORY
6
Equilibriumequations
Constitutiveequations
Compatibilityequations
Internal force factors are equal to appropriate integrals of moments
Taken into account using the reduction coefficients (a.k.a.
effectiveness factors)
Hypotesis of planar cross sections
LIMITATIONS OF BEAM THEORY
7
Beam theory gives unsatisfactory results in following cases:1. Low aspect ratio of the wing. 2. Zone of sweptback angle change. 3. Cut-outs or any other irregularities.
NORMAL STRESSES IN THIN-WALLED BEAMS
8
The distribution of normal stresses obeys the hypothesis of planar cross sections:
,w x y a b x c y
For the case of uniform linear material, it comes to be (for a right coordinate triad):
, yz xz
y x
MN Mx y x y
A I I
CROSS SECTION DISCRETIZATION
9
(CE – conservative estimation, OE – optimistic estimation)
The discretization of real cross section is usually used to possess the calculations of moments of inertia and other geometrical properties:
- small but complex elements like stringers are substituted by point areas positioned at stringer center of gravity (CE) or at the skin surface (OE);
- skins are substituted by center lines (CE);
- complex center line is substituted by polygonal curve;
- portions of skins are substituted by point areas (CE).
CROSS SECTION DISCRETIZATION
10
The problem is to find the moment of inertia.Dimensions:a = 60 mm; h = 22 mm; 1 = 4 mm; 2 = 6 mm;H = 120 mm.
CROSS SECTION DISCRETIZATION – variant #1
11
One option is to substitute the real cross section by center lines with appropriate thick-nesses – usually used in FEA.
Ix, cm4 Iy, cm4
Exact 975 2478
Discrete 1000 2494
Error,% +2.5 +0.6
CROSS SECTION DISCRETIZATION – variant #2
12
Another option is to use concentrated areas instead of stiffeners and webs – very good discretization.
Ix, cm4 Iy, cm4
Exact 975 2478
Discrete 972 2477
Error,% -0.3 -0.0
CROSS SECTION DISCRETIZATION – variant #3
13
Finally, all thin members could be substituted by point areas – ideal for manual calculations.
Ix, cm4 Iy, cm4
Exact 975 2478
Discrete 972 2419
Error,% -0.3 -2.4
CROSS SECTION DISCRETIZATION – variant #4
14
If point areas are positioned at the skin surface, the moment of inertia is overestimatedwhich is not recommended.
Ix, cm4 Iy, cm4
Exact 975 2478
Discrete 1092 2419
Error,% +12 -2.4
WAYS TO TAKE THE ACCOUNT OF PHYSICAL LAW
15
There are many possible ways, some of them are:
1. Method of sequential loading.
2. Method of variable secant modulus.
3. Method of reduction coefficients (a.k.a. effectiveness factors).
The last one is widely used since it is convenient for cross sections with multiple materials, and to study a post-buckling behavior.
METHOD OF REDUCTION COEFFICIENTS
16
The reduction coefficient is the ratio between the real stress in the member and the fictitious stress obeying the Hook law :
,
ii
i f
, ,i f f i fE
The reduction coefficient is introduced to maintain the condition that fictitious strain is equal to real one:
,i i f
METHOD OF REDUCTION COEFFICIENTS
17
The method of reduction coefficient is iterative one. At the first iteration, we set the initial reduction coefficient as the ratio between Young moduli:
Then we calculate fictitious geometrical properties:
,
ii
i f
EE
,i f i iA A
METHOD OF REDUCTION COEFFICIENTS
18
Next we calculate the fictitious stress and find the real stress, forming a new iteration of reduction coefficient:
The process stops when values of reduction coefficients are converged for all points in the section.
,
ii
i f
METHOD OF REDUCTION COEFFICIENTS
19
Calculation of red.coef.
Fictitious geom. properties
Fictitious and real stresses
Initial value is the ratio between Young moduli
Area and axial moments of inertia are calculated using fictitious areas of members
New reduction coefficients
Resultant real stresses
The process is stopped upon convergence of red.coefficients
Real stresses are derived from material physical law or
compression diagram for panel
WHERE TO FIND MORE INFORMATION?
20
Megson. An Introduction to Aircraft Structural Analysis. 2010Chapter 15 – beam bending theory;Chapter 19 - discretization of the cross section.
Method of effectiveness factors (reduction coefficients) is explained inBruhn. Airplane Design HandbookChapter A19.11
… Internet is boundless …
TOPIC OF THE NEXT LECTURE
21
Shear stresses in thin-walled beam
All materials of our course are availableat department website k102.khai.edu
1. Go to the page “Библиотека”2. Press “Structural Mechanics (lecturer Vakulenko S.V.)”