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针对再入飞行器初始再入段的发动机反作用控制系统(RCS)控制精度问题,提出了一种新型发动机控制方法。首先,将飞行器模型分为慢回路和快回路分别进行控制器设计,采用非线性干扰观测器(DOB)来获取不确定项的估计值,并使用反演法及滑模控制方法设计了飞行器的慢回路和快回路控制律;其次,采用线性规划方法来获取最优RCS指令分配方案;在此基础上,对传统PWPF调制器进行改进,提出了积分补偿型PWPF调制器(IPWPF),采用描述函数法证明了该IPWPF的调制稳定性;最后,通过仿真验证了该方法相比于传统的控制方法具有较高的控制精度。
Aiming at the control accuracy of engine reaction control system (RCS) at the initial reentry stage of reentry vehicle, a new engine control method is proposed. First, the model of the aircraft is divided into a slow loop and a fast loop, respectively, and the controller design is adopted. The non-linear disturbance observer (DOB) is used to obtain the estimation of the uncertainty. The inversion and sliding mode control are used to design the aircraft’s Slow loop and fast loop control law. Secondly, the linear programming method is used to obtain the optimal RCS instruction distribution scheme. On this basis, the traditional PWPF modulator is improved. An integral compensation PWPF modulator (IPWPF) is proposed, The function method proves the modulation stability of the IPWPF. Finally, the simulation results show that the proposed method has higher control precision than the traditional control method.