Satellite Configuration Design - Finite Element Analysis for Satellite Structures - page 45

Table 2.4 (continued)

Centroidal mass moment of inertia (kg.m 2 ) Component Mass(kg) Coordinates (mm)

x y z I 0x I 0y I 0z

S-band dipole antenna w/b 0.15 -415 -285 -50 0.0001 0.0001 0.0001

GPS electronic module 1.1 56 -350 846 0.009 0.022 0.014

GPS antenna with bracket -1 0.17 439 -225 -45 0.0001 0.0001 0.0001

GPS antenna with bracket -2 0.17 394 -240 1075 0.0001 0.0001 0.0001

On-board computer -1 3.7 294 0 847 0.074 0.029 0.046

On-board computer -2 3.7 332 0 847 0.074 0.029 0.046

On-board computer -3 3.7 370 0 847 0.074 0.029 0.046

Telemetry Module 2.8 340.5 144 130 0.016 0.012 0.008

Battery cell module 16.5 -340 0 169 0.354 0.122 0.278

Power-conditioning unit 3.6 -307 0 626 0.071 0.029 0.044

Cells leveling unit 1.9 -360 0 628 0.038 0.015 0.023

Cabling 15 - - - - - -

Solar panel-1 (+Y) Stowed 2 0 414 512 0.172 0.313 0.141

Deployed 0 950 -34 0.172 0.141 0.313

Solar panel-1 (-Y) Stowed 2 0 -414 512 0.172 0.313 0.141

Deployed 0 -950 -34 0.172 0.141 0.313

Solar panel-2 (+X) Stowed 1.4 529 0 516 0.173 0.124 0.049

Deployed 1066 0 -31 0.049 0.124 0.173

Solar panel-2 (-X) Stowed 1.4 -529 0 516 0.173 0.124 0.049

Deployed -1066 0 -31 0.049 0.124 0.173

Heat shield-1 (+Y) 1 0 397 518 0.082 0.172 0.090

Heat shield-1 (-Y) 1 0 -397 518 0.082 0.172 0.090

Heat shield-2 (+X) 0.8 512 0 518 0.103 0.063 0.040

Heat shield-2 (-X) 0.8 -512 0 518 0.103 0.063 0.040

Insulation, coatings, sensors 1.5 - - - - - -