摘要
对于攻击地面固定目标的飞行器,提出一种非线性制导律和控制方法。制导和控制一体化的设计方法充分考虑了制导和控制回路的不确定性和未建模动态。对于系统的非匹配不确定的特点,设计了特殊的终端滑模切换面和相应的控制策略,使得系统在有限时间内收敛到终端滑模面。分析表明滑模控制器保证了闭环系统的稳定性。数学仿真验证了此方法的有效性。
A nonlinear guidance law and control strategy is proposed for aircraft applying to attack the ground fixed targets. Uncertainties and unmodelled dynamics are taking into consideration in this integrated approach to guidance and control. For the systems with unmatched uncertainties, terminal sliding mode manifold and control methodologies are proposed. The system states are guaranteed to reach the sliding mode manifold in finite time. It is shown that the stability of the closed-loop system is guaranteed by analysis. Simulation results are included to illustrate the effectiveness of the proposed sliding mode controller.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2005年第1期13-18,共6页
Journal of Astronautics
关键词
飞行器
制导
非匹配不确定
滑模
Aircraft
Guidance
Unmatched uncertainties
Sliding mode
