基于滑模观测器的充液航天器姿态控制  

Attitude Control of Spacecraft with Fuel Slosh Based on Sliding Mode Observer

作　　者：史星宇[1] 齐瑞云[1] 

机构地区：[1]南京航空航天大学自动化学院,南京210016

出　　处：《航天控制》2015年第4期11-16,23,共7页Aerospace Control

基　　金：国家自然科学基金资助项目(61374116)

摘　　要：针对一类充液航天器系统,提出了一种滑模观测器的设计方法,有效的估计了液体燃油晃动角。首先,采用Lyapunov稳定性原理,设计了控制律,该控制律能够快速抑制充液航天器液体燃料晃动、稳定航天器的姿态。然后,考虑实际中液体燃油晃动角不可测的情况,设计了滑模观测器,该观测器通过对航天器姿态角、速度等状态的测量,使晃动估计角在一定误差范围内逼近真实值。最后用晃动估计角替换控制律中的晃动角,验证了估计角对航天器姿态的稳定效果。仿真结果表明,估计值能够在一定的误差范围内,快速跟踪真实值,验证了该滑模观测器的有效性。Regarding a class of spacecraft with fuel slosh, a sliding mode observer design is proposed to es- timate the angle of fuel slosh effectively. Firstly, a control law is developed by using the principle of Lya- punov stability, and the controller can both control the motion of the spacecraft and suppress the fuel slosh effectually. Then, according to the measurement difficulty of angle of fuel slosh in practice, the sliding mode observer is designed, which can provide estimate of the angle of fuel slosh close to the real value within a certain error range based on the measurements of velocity and altitude. Finally, the effectiveness of the es- timated angle is verified by the controller. The simulation results show that the estimates can track the real value fast and also demonstrate the effectiveness of the sliding mode observer.

关 键 词：液体燃料晃动 单摆模型 LYAPUNOV函数 滑模观测器 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]