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针对有界控制导弹采用鸭舵或尾舵单一控制形式存在的劣势,基于双边优化微分对策理论,推导了一种有界双重控制导弹微分对策制导律。该制导律不仅将鸭舵与尾舵两组舵面的控制有效融合在一起,而且实现了有界控制命令最优的分配设计。分析了该微分对策制导律的对策空间,并从弹目机动性能比和控制系统时间常数比之间的关系,给出了鞍点解的存在条件。考虑非完全信息情形,完成了目标加速度滤波器和拦截性能衡量指标的设计。采用Monte Carlo法进行了制导性能的仿真验证,结果表明:所设计的有界双重控制导弹制导律与采用单一的鸭舵控制或尾舵控制的导弹相比不仅机动性要求较低,且具有较高的命中概率。
Aiming at the disadvantage of the bounded control missile adopting the single control form of rudder or tail rudder, based on the theory of bilateral optimal differential strategy, a bounded derivative guidance law of bounded dual control missile is derived. The guidance law not only integrates the control of the rudder surfaces of the rudder and tail rudder, but also achieves the optimal distribution design of the bounded control commands. The countermeasure space of the guidance law of the differential game is analyzed, and the existence condition of saddle point solution is given from the relationship between the ratio of maneuvering performance and the time constant ratio of control system. Considering the case of incomplete information, the design of the target acceleration filter and the interception performance measure is completed. The Monte Carlo method is used to simulate the guidance performance. The results show that the bounded dual-control missile guidance law not only has lower maneuverability requirements but also has better performance than the one with single-rudder control or tail-rudder control High hit probability.