摘要
针对基于线性滑模面的最优末制导律存在的视线角误差和角速率误差渐近收敛、鲁棒性较弱等不足,提出一种基于非奇异终端滑模(nonsingular terminal sliding mode,NTSM)的最优滑模末制导律。算法基于改进的非线性滑模面以解决普通Terminal滑模因参数选择不当出现的奇异问题,实现误差矢量的有限时间收敛。飞行器在该末制导律导引下,视线角误差及角速度误差快速收敛,从而保证飞行器具有较高的命中精度并满足约束条件要求。仿真结果表明该制导律的适用性及较强鲁棒性。
A new optimal guidance law based on nonsingular terminal sliding mode was proposed for the deficiency existing in the traditional optimal guidance law based on linear sliding mode such as poor robustness,asymptotic convergence of line-of-sight angle error and its rate.Singularity in the traditional terminal sliding mode caused by parameter＇s improper chose is avoided by the improved nonlinear sliding mode and the finite-time convergence of error vector is achieved.Controlled by guidance law,the rate of line-of-sight angle can converge quickly,ensuring higher guidance precision.Simulation results show that the guidance law proposed is effective and robust.
出处
《弹箭与制导学报》
CSCD
北大核心
2012年第1期69-72,88,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
最优制导律
非奇异终端滑模
有限时间收敛
强鲁棒性
optimal guidance law
nonsingular terminal sliding mode
finite-time convergence
strong robustness
