Satellite Structural Design - Finite Element Analysis for Satellite Structures - page 52

4 Locking &
releasing devices

4 Solar panels

SATELLITE
“ Small Sat ”

4 Rotation
mechanisms

4 Heat shields

3On-boarddigital
computing complex

Battery cell module

Power-conditioning
unit

X-band electronic
module

SATELLITE CASE
SUBASSEMBLY

2 S-band electronic
module

Cells leveling unit

GPS electronic
module

Cable harness

Upper Frame
Subassembly

Lower Frame
Subassembly

Base Plate
Subassembly

Basis Unit Block
Subassembly

Mounting Plate
Subassembly

Multi-band earth
imager

Telemetry module Star sensor Payload CDH unit

S-band dipole
antenna

2 MBEI signal
processing units

Magnetometer 4 Reaction wheels

GPS receiver
antenna

2 S-band conical
antennae

4Gyros 4 Interface units

2 Separation
transducers

GPS receiver
antenna

3 Magnetorquers

X-band antenna

Fig. 3.1 Satellite technological breakdown scheme

manufacture and has relatively good workability. Mechanical properties of
semi-finished work pieces made of alloy AMg6 according to the standards are
given in Table 3.1 .
Studs for fastening the structural modules together can be fabricated from bars
made of titanium alloy VT-16. Titanium alloy VT-16 is used to manufacture
fasteners operating within a temperature range from -120 to +300 C. Titanium
alloy is also selected because of its very low creep deformation, which minimizes
loss of stud tightness during the satellite's service life. Mechanical properties of
semi-finished work pieces made of titanium alloy VT-16 are given in Table 3.1 .