挠性卫星自适应姿态跟踪控制

Adaptive Attitude Tracking Control of Flexible Satellite

具有较强变轨或姿态机动能力的卫星,在轨运行过程中其质量特性随着液体燃料的消耗而不断变化,卫星的惯量特性也随之变化,使卫星质量参数呈现不确知的特性。如何在惯量矩阵未知情况下实现挠性卫星的姿态跟踪控制是研究的重点。考虑目标姿态角速度可以时变的一般情形,设计了基于误差四元数的自适应姿态跟踪控制律,给出了稳定性证明。数学仿真结果表明该控制律能够在卫星转动惯量未知情况下,保证卫星本体姿态和跟踪目标姿态。

For the satellite with rapid orbit or attitude maneuver ability, its inertia changes greatly with the fuel consumed in orbit, and consequently the mass parameters appear to be uncertain. For the flexible satellite with inertial matrix unknown, the attitude tracking control problem was solved. Considering the target angle rate changing, an adaptive attitude tracking control law was designed based on the error quaternion, and the corresponding close system stability was also proved. The numerical simulation results show the effectiveness of the proposed adaptive control strategy for the satellites with inertia unknown.