航空学报 > 2010, Vol. 31 Issue (7): 1331-1337

RBCC飞行器爬升段轨迹设计方法

吕翔, 何国强, 刘佩进   

  1. 西北工业大学 燃烧、流动和热结构国家级重点实验室
  • 收稿日期:2009-07-10 修回日期:2010-03-16 出版日期:2010-07-25 发布日期:2010-07-25
  • 通讯作者: 吕翔

Ascent Trajectory Design Method for RBCC-powered Vehicle

Lu Xiang, He Guoqiang, Liu Peijin   

  1. National Key Laboratory of Combustion, Flow and Thermo-structure, Northwestern Polytechnical University
  • Received:2009-07-10 Revised:2010-03-16 Online:2010-07-25 Published:2010-07-25
  • Contact: Lu Xiang

摘要:

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。

关键词: 高超声速飞行器, 火箭基组合循环, 飞行轨迹, 控制规律, 非均匀有理B样条

Abstract:

Intense effects between rocket based combined cycle (RBCC) engine performance and vehicle flight trajectory cause the coupling between trajectory design and engine performance analysis. Ascent trajectory design method of RBCC-powered vehicle is studied and the Mach number-dynamic pressure reference curve method is propounded. Complement to non-uniform rational B-spline (NURBS) curve is made to define arbitrary dynamic pressure reference curve, with the selecting principles studied for the control variables of reference curve. Solving procedure for trajectory simulation is investigated with the binary-search method for angle of attack. Trajectory design and analysis for air-launching RBCC-powered vehicle are conducted with the proposed method. The results show that (1) Mach number-dynamic pressure reference curve method is suitable for ascent trajectory design of RBCC-powered vehicle, because it considers the coupling between engine performance and flight trajectory. (2) More than 50% of propellant consumption is produced at low Mach number stage (Ma<2.0) of ejector mode, dominating the performance optimization of RBCC engine. (3) Propellant mass flow rate in ejector mode reaches 6.3 between the maximum and the minimum. (4) Ram effect of the incoming air exceeds the pure ejection effect of primary rocket and becomes the dominant for air intaking in ejector mode with the flight Mach number over 1.7.

Key words: hypersonic vehicle, rocket based combined cycle, flight trajectory, control law, non-uniform rational B-spline

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