The invention discloses a control method for eliminating in-plane swing of a tethered satellite. The method comprises the following steps: constructing a two-body tethered satellite system dynamic model based on a Lagrange method; based on a two-body tethered satellite system dynamic model, according to a system stability hypothesis, obtaining a tether stable recovery rate; and calculating tether tension based on the tether stable recovery rate and a neurodynamics control method. According to the control method, electric energy is completely used, the tether recovery speed can be directly regulated and controlled, the control efficiency is high, real-time and simple effects are achieved, and the tether tension can be effectively limited. The control method for eliminating in-plane swing of the tethered satellite can be widely applied to the field of satellite control.
本发明公开了一种消除绳系卫星面内摆动的控制方法,该方法包括:基于拉格朗日方法构建两体绳系卫星系统动力学模型;基于两体绳系卫星系统动力学模型,根据系统稳定性假设得到系绳稳定回收速率;基于系绳稳定回收速率和神经动力学控制方法,计算绳系张力。本发明的控制方法完全使用电能,可直接对系绳回收速度进行调控,控制效率高,实时简单,并可对系绳张力进行有效限制。本发明作为一种消除绳系卫星面内摆动的控制方法,可广泛应用于卫星控制领域。
Control method for eliminating in-plane swing of tethered satellite
一种消除绳系卫星面内摆动的控制方法
2023-04-25
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
Tethered satellite control mechanism
NTRS | 1983
|Precision tethered satellite attitude control
NTRS | 1990
|Precision Tethered Satellite Attitude Control
NTIS | 1990
|NTRS | 1986
|