考虑导引头视场角和落角约束的制导方法

针对空地武器采用最优弹道成型制导律进行大落角攻击时易造成导引头跟踪误差角大于其视场角而丢失目标的问题,提出一种满足导弹导引头视场角约束和落角约束的制导方法.基于线性化模型和小角假设,得到了导引头跟踪误差角的解析表达式,分析了影响导引头跟踪误差角的因素及最大跟踪误差角的取值范围.在此基础上,针对不同空地武器提出了通过改变末制导初始弹目视线角或放松落角约束的方式满足导引头视场角约束的制导方法,并给出了初始弹目视线角的取值原则及最大允许落角的计算方法.通过仿真校验,证明了导引头跟踪误差角的解析解的正确性及制导方法的可行性. 

A Guidance Method on Seeker's Field of View and Impact Angle Constraint

A guidance method was proposed, considering seeker field of view constraints and impact angle constraint, for the reason that the seeker look angle of air to ground weapon may overstep the field of view and lose the target when it follows the optimal trajectory shaping guidance law to achieve large impact angle. An analytic expression of seeker look angle was deduced based on the assumption of linearization model and small angle. The factors that influence seeker look angle and the range of maximum seeker look angle were analyzed. On this basis, the guidance method satisfied the seeker field of view constraints through changing the initial line of sight angle or relaxed impact angle constraints was put forward for different air to ground weapons. The select principle of initial line of sight value and the maximum impact angle calculation method were also presented. Numerical simulations verified the effectiveness of the seeker look angle theoretical expressions and the proposed guidance method.