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高超声速飞行器的再入过程十分复杂,已知初始状态推断落点区域对飞行器再入航迹规划具有重要意义。本文提出一种基于动力学规划求解高超声速飞行器落点区域的方法。该方法在满足再入轨迹的各种约束条件前提下,在能量-阻力空间里描绘出标称阻力边界曲线,通过反馈线性法对其进行跟踪得到实际可用的上下边界,再经插值计算得到符合约束条件的阻力方案。纵向轨迹采用反馈线性法跟踪得到,而横向控制则通过不同时刻的侧向机动实现。选取阻力最大和最小点作为再入落点区域的最上和最下端,将倾侧角恒为正的点和恒为负的点作为最左和最右端点,由此组成了再入落点区域的边界。该方法通过了计算机仿真可行性验证,得到了精确的落点区域。
The reentry process of the hypersonic vehicle is very complicated. It is of great significance to deduce the landing area in the initial state for the reentry trajectory planning of the aircraft. This paper presents a method based on dynamic programming for solving the landing area of hypersonic vehicles. Under the premise of satisfying various constraints of reentry trajectory, this method draws the nominal resistance boundary curve in the energy-resistance space and traces it by the feedback linear method to get the upper and lower boundaries that are actually available, Constraints of the resistance program. The longitudinal trajectory is tracked by the feedback linear method, while the lateral control is achieved by lateral maneuvers at different moments. Select the maximum and minimum drag points as the reload entry point of the region at the top and bottom of the corner will be constant for a positive point and constant negative for the left and right endpoint as the extreme point, boundary. The method passes the verification of computer simulation feasibility and gets the accurate landing area.