Application of finite elements in aerospace structures

Application of finite elements in aerospace structures

Solve by using the Galerkin method for the displacement in the given tapered spar beam used to model an aircraft wing. Geometry:
Material:
Aluminum alloy 7075-T6.
Loading condition:
Load is a line pressure acted on the upper flange downward. The pointwise magnitudes are given in the table below.
60 mm
200 mm
4200 mm
30 mm
1.5 mm
t=2 mm
Distance from the support (mm)
Load (N)
0
1100
250
1220
500
1380
800
1520
1250
1640
1550
1490
1900
1370
2200
1280
2600
1210
3000
990
3250
870
3600
650
3950
410
4200
120
Solution condition:
(1)Consider the body as one-dimensional body with the governing equations assimple bending analysis.
(2)Use the loading condition as a distributed load. The loading function in termsof the axial coordinates can be derived by a proper curve fitting analysis.
(3)Use at least two basis functions. (Using three basis functions is preferable.)
(4)Basis functions can be chosen as polynomial (or trigonometric) terms.
(5)Use at least one field area (two or more will be preferable).
Verification:
(1)By Euler-Bernoulli beam theory analysis.
(2)Using beam finite element analysis in ANSYS Workbench software.
Results to be presented:
(1)Formulation of the problem.
(2)Comparing deflection function by the three methods.
(3)Discussion on the accuracy of the approaches.