带末端角约束的跃升俯冲攻击控制律设计

Climb-dive Attack Control Law Design with Terminal Angular Constraint

飞行器在末段进行跃升俯冲攻击,可以增加突防能力,发挥其攻击效能。为解决飞行器在末段机动飞行过程中气动参数变化剧烈、各通道间严重耦合、对控制器鲁棒性要求较高的问题,设计了一种基于反演法的跃升俯冲攻击控制律。设计过程中,非线性控制律由反演法回推得出,通过引入一阶滤波器,避免了设计过程中对某些非线性信号的微分,降低了控制律的复杂性。并且利用Lyapunov稳定性理论证明了系统误差指数收敛。在考虑未知不确定性的情况下,对某飞行器进行了3种不同跃升俯冲攻击方案仿真,结果表明该控制律能很好地跟踪控制指令,实现飞行器的跃升俯冲攻击,飞行弹道平滑,鲁棒性好。

The aerodynamic parameters undergo great changes and all the channels couple seriously during its terminal time. To fulfill the high robustness requirements of a flight control system, a climb-dive attack control law based on backstepping is designed. By introducing a first order filter in the course of design, the problem caused by differentiations of the virtual, control law is solved and the complexity of control law is reduced. The tracking error is proved to converge exponentiary by the Lyapunov stability theorem. The three climb-dive attack schemes simula- l：ions for the vehicle with unknown uncertainty show that the control law is satisfied with climb-dive attack and has smooth trajectory and good robustness.