
Winglike structureIn this section we present the numerical results of Code_Aster
solver for a structural test problem, such as the static analysis of a winglike structure.
Problem definition Domain:
 Rectangular homogeneous winglike structure
 # of skin panels Np = 7
 # of Lshaped stringers NsL = 3
 # of Tshaped 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 EulerBernoulli 1D beam elements and DKT 2D square plate elements created in Salomé pre/postprocessing 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.

