所属单位：航天学院
发表刊物：J Syst Eng Electron
摘要：A retrieval control strategy for failed satellite, which is connected to a servicing spacecraft by a tether, is studied. The Lagrange analytical mechanics based dynamics modeling for the system composed of a servicing spacecraft, a tether and a failed satellite, is presented under the earth center inertia coordinate system, then model simplification is conducted under the assumption that the failed satellite's mass is far smaller than the servicing spacecraft's, meanwhile the tether's length is far smaller than the size of the servicing spacecraft's orbit. Analysis shows that the retrieval process is intrinsically unstable as the Coriolis force functions is a negative damping. A retrieval strategy based on only the tether's tension is designed, resulting in the fastest retrieval speed. In the proposed strategy, firstly, the tether's swing angle amplitude is adjusted to 45° by deploying/retrieving the tether; then the tether swings freely with fixed length until it reaches negative maximum angle -45°; finally, the tether is retrieved by the pre-assigned exponential law. For simplicity, only the coplanar situation, that the tether swings in the plane of the servicing spacecraft's orbit, is studied. Numerical simulation verifies the effectiveness of the strategy proposed. © 1990-2011 Beijing Institute of Aerospace Information.
ISSN号：1671-1793
是否译文：否
发表时间：2019-08-01
合写作者：洪军停
通讯作者：韩艳铧
发表时间：2019-08-01