一种考虑机动能力的交会角约束弹道设计方法

A Method of Trajectory Design with Constrained Intercept Angle Considering Missile Maneuvering Ability

一般导引弹道的设计都是以导弹可用过载远远满足需用过载为前提,但是防空导弹受其尺寸和燃料的限制,在攻击空袭目标时,不仅要考虑其脱靶量,还要权衡其拦截能力进行综合考虑。首先建立了二维交战模型,并通过最优控制理论推导了一种考虑交会角与过载约束的导引方式;然后通过最小二乘法拟合可用过载边界曲线,设计一种时变权系数;最后对导引弹道进行仿真,验证导引方式的可行性。

The design of leading trajectory is generally on condition that the missile maneuvering ability can far satisfy to the need,but the air-defense missile is subjected to restriction of its size and fuel,while attacking a air attack target,not only need to consider the miss distance,but also need to consider the ability to intercept. This text built up planar engagement geometry firstly,and deduced a method of guidance with the consideration of intercept angle and available payload by optimum control theories;Then draw up the boundary curve of available payload by least square fit,and give a time-varying gain value; Finally emulate the leading trajectory to prove the feasibility of the method.