Stochastic Finite Element and Satellite Structure Design - Finite Element Analysis for Satellite Structures - page 243

4 Solar panels

Satellite case

4 Heat shields

Fig. 5.1 Layout of the satellite under study [ 11 ]

Fig. 5.2 3-D model of primary satellite structure [ 11 ]

Table 5.1 Mechanical and thermal material properties
Mechanical material
properties

Modulus of elasticity, E = 69 (10 6 ) kg.mm/s 2 /mm 2 Density, q = 2.71

(10 -6 ) kg.mm/s 2 /mm 2

Thermal conductivity, K = 117 W/m. o C
Coefficient of thermal expansion, a = 24.7 9 10 -6

Thermal material
properties K -1

covariance of t y , thickness mean in the z-dir (t z ), covariance of t z , distribution type
(Normla (0) or Lognormal (1)), and beam rotation angle around its center.

- Real_Constants(1,1:7) = [5 0.05 10 0.05 1 1 0];
- Real_Constants(2,1:7) = [7 0.05 14 0.05 1 1 0];