On the basis of analysis of the deployment motion of satellite solar array,
a whole satellite model was established by UG and was imported to MSC.
ADAMS. Then, the deployment of solar array was simulated in ADAMS. A
jointing structure consisting of revolute joints, torsion springs and closed
cable loops was built in ADAMS/View. Moreover, the impacting process was
simulated by contact functions, the closed cable loops was simulated by
couplers, and the dynamics characteristic was emulated in ADAMS/Solver.
After analysis on the simulation, the relations between deployment angles
of linker and solar panels with time were obtained, and the movement of
satellite′ attitude influenced by deployment motion was calculated. Analysis
results indicate that the deployment process of solar array is 15 s. The
deployment motion is stabilization and smoothness, and has a little effect
on satellite attitude. These results reported here show that designed solar
array is reasonable.