航空学报 > 2014, Vol. 35 Issue (5): 1284-1291   doi: 10.7527/S1000-6893.2013.0389

RBCC-RKT两级入轨飞行器飞行轨迹优化方法

阮建刚, 何国强, 吕翔   

  1. 西北工业大学 燃烧、流动和热结构国家级重点实验室, 陕西 西安 710072
  • 收稿日期:2013-07-12 修回日期:2013-09-13 出版日期:2014-05-25 发布日期:2013-11-01
  • 通讯作者: 何国强,Tel.:029-88494163 E-mail:gqhe@nwpu.edu.cn E-mail:gqhe@nwpu.edu.cn
  • 作者简介:阮建刚男,博士研究生。主要研究方向:航空宇航推进理论与工程。Tel:029-88492417E-mail:fortran2009@mail.nwpu.edu.cn;何国强男,博士,教授,博士生导师。主要研究方向:航空宇航推进理论与工程。Tel:029-88494163E-mail:gqhe@nwpu.edu.cn;吕翔男,博士,副教授。主要研究方向:航空宇航推进理论与工程。Tel:029-88492417E-mail:lvxiang@nwpu.edu.cn

Trajectory Optimization Method in Two-stage-to-orbit RBCC-RKT Launch Vehicle

RUAN Jian'gang, HE Guoqiang, LYU Xiang   

  1. National Key Laboratory of Combustion, Flow and Thermo-structures, Northwestern Polytechnical University, Xi'an 710072, China
  • Received:2013-07-12 Revised:2013-09-13 Online:2014-05-25 Published:2013-11-01

摘要:

针对火箭基组合循环(RBCC)发动机比冲和推进剂质量流量随飞行条件改变而不断变化的特点,提出了通过增广拉格朗日遗传算法优化飞行器飞行轨迹的方法,在飞行器气动参数和发动机比冲已知、最大飞行动压给定等条件下,进行了火箭基组合循环发动机-液体火箭(RKT)发动机推进的水平起飞两级入轨(TSTO)飞行器飞行轨迹优化计算。研究结果表明:在飞行俯仰角和发动机推进剂质量流量变化范围已知的情况下,利用该方法能够在较好满足给定约束条件的情况下,优化得到飞行俯仰角和发动机流量随时间的变化关系,为飞行轨迹初步设计提供参考。

关键词: 两级入轨, 水平起飞, 火箭基组合循环, 发动机, 轨迹优化, 增广拉格朗日遗传算法

Abstract:

In view of the fact that the specific impulse and propellant mass flow rate of a rocket based combined cycle (RBCC) engine change constantly with flight conditions, a method based on augmented Lagrangian genetic algorithm for optimizing the trajectory of a RBCC-RKT two-stage-to-orbit (TSTO) horizontal takeoff launch vehicle is established when the aircraft aerodynamic parameters, the engine specific impulse and the maximum flying dynamic pressure are the constant values. The result shows that employed the method and given the range of flight program angle and propellant mass flow rate between a min and a max, the constraints can be satisfied and the history of flight program angle and propellant mass flow rate are optimized to provide a reference for the scheme demonstration and preliminary concept design of the vehicle.

Key words: two-stage-to-orbit, horizontal takeoff, rocket based combined cycle, engine, trajectory optimization, augmented Lagrangian genetic algorithm

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