CAJ | 학술논문

针对导弹飞行末端弹着角度变化特点,采用最优控制理论,探索控制导弹末端弹着角度的方法.研究了三维空间下的弹着角度可控制导律.对俯冲平面和水平平面,分别运用最优控制理论中的极大值原理及求解Riccati方程的方法给出了两种形式的制导律.通过对两个平面及多枚导弹不同条件下的飞行数据仿真,可以看出这种制导律应用于控制导弹以期望的弹着角度攻击目标时的有效性和可行性.
침대도탄비행말단탄착각도변화특점,채용최우공제이론,탐색공제도탄말단탄착각도적방법.연구료삼유공간하적탄착각도가공제도률.대부충평면화수평평면,분별운용최우공제이론중적겁대치원리급구해Riccati방정적방법급출료량충형식적제도률.통과대량개평면급다매도탄불동조건하적비행수거방진,가이간출저충제도률응용우공제도탄이기망적탄착각도공격목표시적유효성화가행성.
According to the change of impact angle at the flight terminal of missile.This paper introduces an optimal control theory to find the way to control the impact angle.The impact-angle-control guidance law in threedimensional space is studied.Using the maximum principle and method of solving the Riccati equation of optimal control theory helps to give two kinds of impact angle control guidance law refered to diving plane and horizontal plane.The simulation of several engagement situations proves its validity and feasibility,which demonstrates that the new guidance law can be used to hit a target at a desirable impact angle.