摘要
为了提高导弹的杀伤力,对攻击角度提出了一定的要求,而导弹以最小的飞行时间来完成带攻击角度约束的制导律,可减少被导弹防御系统发现概率而提高生存概率。采用Bang-Bang控制原理给出控制量受限情况下攻击角度约束的时间最优的控制律,并给出两种求解控制区间的几何方法:解析几何法和微分几何法。仿真结果验证了控制律的性能。
Impact angle control is required to enhance the terminal effectiveness of missile systems. Moreover, the missile systems are allowed to have only low altitude and minimum flight time to reduce the probability of detection by sensors of missile defense systems and thus to increase the survivability. In this paper, a time-optimal control law based on the Bang-Bang theory is suggested in the case of constrained missile maneuverability and given impact angle, and two method of solution for the control law ： the principles of Euclidean geometry and differential geometry. Performance of the proposed control law is tested by a simulation study.
出处
《飞行力学》
CSCD
北大核心
2010年第2期46-50,共5页
Flight Dynamics
基金
国家自然科学基金资助(60674090)
