The structure design of small satellite full-physical simulation system

The article presents a kind of small satellite disturbing loads full-physical simulation system which is used to deeply research and validate the control algorithms of orbit and attitude of small satellite under the effect of spacial disturbances. The system uses methods of air floating and hanging for gravity compensation of the five DOF air floating platform on which flexible solar wings have been installed. The main parts of the system have been designed and analyzed in the text. Finally, the feasibility of the system has been illustrated by the simulation that result from the combination of ANSYS and ADAMS softwares. The system proposed in this paper make it available that the satellite with flexible attachment as a whole be used for experiments under spacial disturbances on the ground, it is of great significance to suppress the vibration of flexible attachment and strengthen the stability of the position of satellite under spacial disturbances.