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针对高超声速飞行器倾侧转弯过程中俯仰、偏航和滚动通道间的强烈耦合,提出一种耦合控制策略。针对高超声速飞行器快时变、非线性和强不确定性的控制问题,基于解析形式的非线性最优预测控制方法,采用分层设计思想设计了飞行器姿态控制系统,可较好满足高超声速飞行器的快速性要求;在分析了倾侧转弯飞行控制过程的主要影响因素及其影响规律的基础上,提出一种“降低攻角—快速滚转—拉起攻角”的耦合控制策略。对该控制策略对于高超声速飞行器的适用性进行了仿真分析,结果表明:所提耦合控制策略有效降低了偏航通道的控制需求,降低了倾侧转弯控制过程的失控风险,提高了控制系统的可靠性。
Aiming at the strong coupling between pitch, yaw and roll path in hypersonic vehicle roll-over, a coupled control strategy is proposed. Aiming at the control problems of hypersonic vehicle with time-varying, nonlinear and strong uncertainty, based on analytic form of nonlinear optimal predictive control method, a stratified design method is adopted to design the attitude control system of aircraft, which can better meet the requirements of hypersonic vehicle Based on the analysis of the main influencing factors and the law of influence on the control process of the tilting flight, a coupling control strategy of “reducing the angle of attack - rapid roll - pulling attack angle” is proposed. The applicability of this control strategy to hypersonic vehicle is simulated. The results show that the proposed coupled control strategy can effectively reduce the control requirements of yaw channel, reduce the risk of out of control and improve the reliability of the control system Sex.