FreeCASE - Free(dom) Computational AeroServoElasticity
Last update:
January 15. 2016 14:05:15

Wing-like structure

In this section we present the numerical results of Code_Aster solver for a structural test problem, such as the static analysis of a wing-like structure.

Problem definition

  • Domain:
    • Rectangular homogeneous wing-like structure
    • # of skin panels Np = 7
    • # of L-shaped stringers NsL = 3
    • # of T-shaped stringers  NsT = 4
    • # of ribs Nr = 4
  • Material:
    • Alluminium
    • Density rho = 2800 kg/m^3
    • Young's modulus E = 7.1e10 Pa
    • Poisson's coefficient nu = 0.3125
  • Boundary conditions:
    • Fixed translations and rotations at the root section z = 0 m
  • Loads:
    • Nodal force F1 = F2 = F3 = 13200 N applied in z = 400 - 800 - 1200 mm
    • Nodal force F4 = 6600 N applied in z = 1600 mm


Figure: Problem definition.

FEM discretization

  • Space discretization:
    • Mixed mesh of POU_D_E Euler-Bernoulli 1D beam elements and DKT 2D square plate elements created in Salomé pre/post-processing platform
    • # of SEG2 elements Ne = 224
    • # of QUAD4 elements Ne = 1440
    • # of COOR_3D nodes Nn = 1414


Figure: Computational grid.

Numerical results

  • Comparison with MSC.Nastran solver (with RBE3 element distributed loads)
  • Single iteration CPUtime = 3.73 s on ASUS M6000 notebook PC with Intel Pentium M 2.0 GHz CPU, 1 Gbyte RAM, 2 Mbyte L2 cache


Figure: Static solution.

Download

  • WingStructure.tar.gz test problem folder. Uncompress this archive in the $HOME folder and execute ~/Aster/ASTK/ASTK_SERV/bin/as_run ./WingStructure.export from terminal to start the simulation. Download.


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