脉冲力末端修正追踪制导律稳定性分析

Stability analysis of pursuit guidance law using impulse force control

脉冲力控制的离散性和弹体动力学的连续性使得脉冲力控制制导控制系统成为难于分析的混杂控制系统。鉴于此,建立了脉冲力控制弹体和制导回路动力学模型,通过将脉冲力控制制导系统等价为幅值式脉冲调制(amplitude pulse frequency modulator,APF-M)系统,解决了脉冲力控制制导回路的变周期离散化建模问题。进一步利用滑模理论分析了制导回路的稳定性,得出脉冲冲量、喷管点火等待时间及重力对制导回路稳定性的影响。提出了偏置阈值法进行重力补偿,并对脉冲力控制制导回路进行了仿真分析。仿真结果验证了偏置阈值法重力补偿的有效性,并得出加大脉冲冲量,减小喷管点火等待时间能有效减缓失调角发散的结论。

The impulse force control guidance system belongs to the complex hybrid control system due to the discreteness of impulse force control and the continuity of missile dynamics. A dynamics model of impulse force control missile is established. And, varying period discrete modeling of the impulse force control guidance loop is completed by finding the equivalence between the impulse force control guidance system and the ampli rude pulse frequency modulator （APF-M） control system. Then, the impact of pulse jet impulse, pulse jet igni- tion waiting time and gravity on the guidance loop is obtained via analyzing the guidance loop stability using the sliding-mode control theory. Moreover, a bias threshold gravity compensation method is proposed and then sim- ulated. The simulation results verify the gravity compensation method, and demonstrate the conclusion that increase pulse jet impulse and decrease pulse jet ignition waiting time can slow down the speed of boresight error divergence.