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在具有控制和轨迹约束的再入制导中,提出了一种新的基于多模型预测再入飞行器纵向制导方法。首先对再入飞行器的纵向运动方程沿着标准轨道线性化,基于分段仿射约束系统建模理论逼近原非线性系统,并采用线性矩阵不等式(LMIs)优化技术离线将保证闭环系统稳定的终端二次代价项求出;然后,在每个制导周期内,基于多模型预测在线求解构造好的有限时域优化目标,从而获得控制量的增量,并把第一个控制增量分量与标准轨道的控制量叠加后形成全量控制,用于实际再入轨道的制导,而在下一个制导周期基于新的状态参数重复上面的优化过程。数字仿真结果证实了所提方法的有效性。
In reentry guidance with control and trajectory constraints, a new longitudinal guidance method based on multi-model predictive reentry vehicle is proposed. First, the longitudinal motion equations of reentry vehicle are linearized along the standard orbit, and the original nonlinear system is approximated by the modeling theory of piecewise affine constraints, and the linear matrix inequality (LMIs) optimization technique is used to off-line the terminal to ensure the stability of the closed-loop system Then, in each guidance cycle, a finite time-domain optimization target constructed on the basis of the multi-model prediction online solution is obtained, so as to obtain the increment of the control amount, and the first control increment component is compared with the standard The amount of control of the trajectory is superposed to form a full amount of control for the actual reentry orbit guidance and the above optimization procedure is repeated for the next guidance period based on the new state parameters. Numerical simulation results confirm the effectiveness of the proposed method.