摘要
以一种能够自适应变化的伪转动惯量,基于Lyapunov稳定定理,推导出一种模型独立的航天器自适应姿态跟踪控制律。理论和数值仿真结果表明,与一般情况下需确知模型参数确定性部分的滑模姿态控制律相比,该控制律能够在不依赖于模型参数确定性部分的情况下良好地实现姿态跟踪,并对模型误差的不确定性和外干扰力矩具有一定的鲁棒性。
By use of a kind of pseudo-inertia of mass which can adjust itself adaptively, based on the Lyapunov stability theorem, a model-independent adaptive attitude tracking control law is derived. Simulation results show that, compared with the traditional sliding-mode attitude controller which depend on the definite part of inertia of mass, the proposed control law can realize attitude tracking under the condition of unknown inertia of mass and it has good robustness to system uncertain error parameters as well as disturbances.
出处
《航天控制》
CSCD
北大核心
2006年第6期31-35,共5页
Aerospace Control
