Design and Verification of Solar Array Deployment Scheme Based on a Novel Biaxial Drive Assembly

Comparing with traditional solar-synchronous orbit satellite, the angle between orbital plane and solar vector of the inclined-orbit satellite varies over a much wider range, up to ±90°. In order to constantly align with solar vector, one of important means is to replace single-axis solar array drive assembly with biaxial solar array drive assembly (BSADA). However, BSADA may result in interference between solar array and satellite body, and is vulnerable to reaction force of solar array deployment. To solve this problem, this paper introduces a novel BSADA, increasing the distance between two axes (named axis A and axis B) by an extension rod, and designs solar array deployment scheme in the satellite injection phase, in which, other than traditional spring-damping device, axis B far away from the satellite is used to deploy the solar array to reduce reaction force. Relevant analysis, simulations and experimental results show that this scheme can effectively avoid solar array’s potential interference to satellite structure, and keep the reactional impact allowable during solar array deployment, which can meet the requirements of inclined orbit satellite to track the direction of solar vector.