摘要
针对现代战机近距空战导引过程,建立了战机与目标的相对运动模型。应用滑模变结构控制理论,以拦截时间、视线角速率和指令加速度变化率为性能指标,推导出一种增广比例加滑模变结构的新型复合导引律,给出了其设计机理,并在理论上对变参数进行了优化设计。仿真结果表明,该导引律结构简单,能有效克服目标机动,在具有较强鲁棒性的同时,其导引性能较传统的PPN有较大提高,具有工程可实现性和有效性。
In accordance with the guidance procedure for close-in air combat of a modem fighter, this paper deals with a mathematic model of the relative motion between a fighter and a target. Used the control theory of slid- ing mode, a new combined guidance （CG） law combining the augmented proportional navigation （APN） and slid- ing mode guidance law, was proposed with the time of interception, line-of-sight （LOS） angle velocity and rate of acceleration commands as performance indexes, the design mechanism was explained and the variable parameters were optimized. The simulation results show that the CG has the advantages of simple structure, greater robustness and easy to engineering realization.
出处
《飞行力学》
CSCD
北大核心
2012年第3期228-232,共5页
Flight Dynamics
关键词
现代战机
增广比例导引
滑模变结构导引
复合导引
modem fighter
augmented proportional navigation
sliding mode variable structure guidance
combined guidance
