Study On Solar Array Wing Of Spacecraft With Deployment By Step

With the growing development of Chinese spacecraft technology, theconventional solar wing technology is mature, but unable to meet future technologyneeds. Based on the better of the spacecraft orbit attitude control and reduction of solarpressure disturbance torque, need to design the solar wing with T-shaped layout anddeployment by step, the research is of great significance to meet technology trends.In this paper, according to the feature of deployment configuration and solar arraywing specifications, two program was proposed and the comparison was carried out,finally determine the final program. Detail design of solar panels,yoke,deploymentmechanism and hold-down mechanism was finished, and completed the final overallprogram design and PRO/E digital model.In order to verify the correctness of the design,established the kinematics anddynamics simulation model,completed the simulation analysis of the kinematics anddynamics, modal characteristics and intensity, the results show that the design schemeis reasonable and achieves the research objectives.