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火箭基组合循环(RBCC)的发动机推力与飞行轨迹相互影响,导致飞行器轨迹设计与发动机性能分析存在耦合作用。对RBCC飞行器爬升段的轨迹设计方法进行研究,提出了基于马赫数-动压参考曲线的轨迹设计方法。对非均匀有理B样条(NURBS)曲线进行了定义补充,以用于描述具有任意形状的马赫数-动压参考曲线,并对参考曲线的各控制参数选取方法进行了研究;建立了基于二分法求解迎角并实现轨迹方程求解的算法流程。利用提出的轨迹设计方法对空中载机发射的RBCC飞行器进行了爬升段轨迹设计与分析,计算结果表明:(1)马赫数-动压参考曲线法考虑了发动机性能与飞行轨迹的耦合作用,能够适用于RBCC飞行器爬升段的轨迹设计;(2)引射模态低速段(Ma<2.0)消耗的推进剂质量超过爬升段的50%以上,是发动机性能优化的关键;(3)引射模态推进剂流量最大值与最小值之比达到了6.3;(4)当飞行马赫数达到1.7后引射模态下的来流空气冲压作用超过了一次火箭的引射作用,在保证空气捕获方面占主导地位。
The influence of rocket-based combined cycle (RBCC) engine thrust and flight path interaction has resulted in the coupling between trajectory design of aircraft and engine performance analysis. The trajectory design method of RBCC aircraft climb section is studied, and the trajectory design method based on Mach-number and dynamic pressure reference curve is proposed. The non-uniform NURBS curve is supplemented to describe Mach-reference curve with arbitrary shape, and the selection of each control parameter of the reference curve is studied. Based on the dichotomy Solving the angle of attack and solving the trajectory equation algorithm flow. The trajectory design method is used to design and analyze the climb trajectory of RBCC aircraft launched by airborne aircraft. The calculation results show that: (1) The Mach-number dynamic reference curve method considers the coupling between engine performance and flight path, Which is suitable for trajectory design of RBCC aircraft climbing section. (2) The mass of propellant consumed in low velocity section of launch mode (Ma <2.0) exceeds 50% of the climbing section, which is the key to engine performance optimization. (3) State propellant flow rate reached the maximum and minimum ratio of 6.3; (4) When the flight Mach number 1.7 after injection mode of the incoming air punching effect exceeds a rocket launch role in ensuring air capture Dominant.