基于终端落角和加速度约束的末制导律设计

Design of terminal guidance law based on terminal impact angle and acceleration constraints

为了提高导弹末制导的打击精度和毁伤程度,设计了基于剩余时间多项式的满足终端落角约束和终端加速度为0的制导律。经过反馈线性化将弹目方程变成线性形式,通过满足具体的终端约束求解了制导律的系数,得到满足各种约束的易于工程实现的新制导律。利用闭环轨迹解给出了一种有效求解弯曲弹道剩余时间的方法。最后通过弹道仿真和对比试验验证了该制导律的可行性。与现有文献相比,该制导律不仅满足高精度制导的需要,而且对末端迎角控制和早期弹道修正具有较大优势。

In order to study the problem of improving the precision guidance and damage degree of missile in the homing engagement,the guidance law as a polynomial function of time-to-go was designed,which meet the requirements of the terminal impact angle and terminal acceleration constraints.The system equations turn to linear form after feedback linearization,and determine the coefficients of the guidance command to satisfy the specified terminal constraints,get a new guidance law which facilitates project implementation and meets a variety of constraints.Using the closed form trajectory solution,we get a perfect method of calculating the time-to-go of curved trajectory.The feasibility of the guidance law is verified by trajectory simulation and comparison test.The verified results show that the guidance law with multiple constraints meets the requirements for precision guidance under multi-constraint conditions,and has more advantages for terminal AOA and trajectory correction in early phase.