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基于θ-D次优控制方法设计了一种满足落角约束的三维末制导律。对于采用倾斜转弯(BTT)控制方式的高超声速滑翔飞行器,其俯仰、偏航通道存在强耦合关系,基于双通道解耦的制导律设计方法不再适用。针对这一问题,首先建立了飞行器和目标的三维相对运动方程,通过重新定义状态变量,基于θ-D方法设计了一种带落角约束的三维末制导律。所设计的制导律不需要进行通道解耦,制导精度高,计算量小。仿真结果表明了该制导律的可行性和良好性能。
Based on the θ-D suboptimal control method, a three-dimensional terminal guidance law satisfying the falling angle constraint was designed. For hypersonic gliding aircraft with Tilt Bend (BTT) control method, the pitch and yaw channels are strongly coupled, and the guidance method based on dual channel decoupling is no longer suitable. To solve this problem, the three-dimensional relative motion equations of the aircraft and the target are first established. By re-defining the state variables, a three-dimensional terminal guidance law with a corner constraint is designed based on θ-D method. The designed guidance law does not require channel decoupling, high guidance accuracy and small calculation. The simulation results show the feasibility and good performance of the guidance law.