摘要
针对一类建模过程中考虑不确定项的大气层内拦截弹,提出一种设计简单、高鲁棒性的拦截末段制导律。根据平面内拦截弹-目标的相对运动方程,引入拦截弹的一阶动力学模型,将系统建模误差和目标未知信息看作不确定项,建立下三角型非线性系统方程。应用自适应动态面控制方法设计新型制导律,解决系统输入与不确定项的非匹配问题,避免制导律中调整参数多、微分膨胀现象,且制导律阶数低,有利于工程化实现。稳定性分析说明控制器参数的合理选择满足系统稳定性要求。仿真结果说明该制导律具有缩短拦截时间、提高系统鲁棒性的特点。
A terminal guidance law of simple design and high robustness is presented for the endoatmosh- peric interceptor considering the uncertainties in modeling. Firstly, considering the relative movement e- quations of interceptor and target in the plane and the one-order dynamic model of interceptor, the model errors and target unknown information were treated as uncertainties. And thus the lower triangular form nonlinear system model was established. Then the adaptive dynamic surface control was used to design the new guidance law. The non- matched problem between system inputs and uncertainties was solved. The large number of adjusted parameters and differentiation explosion were overcome. And the order of the guidance law was lower. Therefore, it was beneficial to engineering realization. The Lyapunov analy- sis proved that the reasonable selection of controller parameters satisfies the requirement of system stabili- ty. The simulation results show that the proposed guidance law shortens intercepting time and improves system robustness.
出处
《电机与控制学报》
EI
CSCD
北大核心
2013年第2期84-89,共6页
Electric Machines and Control
基金
航天支撑基金项目
关键词
不确定项
自适应动态面控制
制导律
鲁棒性
拦截弹
uncertainties
adaptive dynamic surface control
guidance law
robustness
interceptor
