宇航学报

宇航学报 ›› 2018, Vol. 39 ›› Issue (1): 17-26.doi: 10.3873/j.issn.1000-1328.2018.01.003

• 飞行器设计与力学 • 上一篇    下一篇

TBCC飞行器发动机尺寸选型及爬升策略设计

李乐, 姜光泰, 褚显应, 王健   

  1. 北京机电工程研究所，北京 100074
  • 收稿日期:2017-06-08 修回日期:2017-11-02 出版日期:2018-01-15 发布日期:2018-01-25

Research on TBCC Engine Size Selection and Ascent Strategy of Combined Cycle Aircraft

LI Yue, JIANG Guang tai, CHU Xian ying, WANG Jian   

  1. Beijing Institute of Mechanical and Electrical Engineering, Beijing 100074, China
  • Received:2017-06-08 Revised:2017-11-02 Online:2018-01-15 Published:2018-01-25

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摘要：

针对临近空间高速飞行器爬升航迹问题，提出了一种涡轮冲压组合发动机尺寸选型的依据和一种固体火箭助推器辅助加速的爬升策略。以本文设计的一型临近空间高速飞行器为原型，基于hp自适应Radau伪谱法开展爬升航迹优化研究，将最优控制问题转化为非线性规划问题，以爬升消耗燃料质量最小为目标，利用序列二次规划算法求解最优航迹。在此基础上，分析了涡轮冲压组合发动机尺寸选型和采用固体火箭助推器加速爬升策略对爬升航迹和巡航航程的影响。结果表明，选取合理的发动机尺寸和助推器辅助爬升策略，均可有效减少飞行器爬升消耗燃料质量，提升巡航航程。

关键词: 临近空间高速飞行器, TBCC动力系统尺寸选型, 爬升段策略, Radau伪谱法

Abstract:

In this paper, a new high speed near space flight vehicle is introduced, based on which the impact of TBCC (turbine based combined cycle) engine matching project and the ascent strategy on the range are discussed. The optimization of the trajectory is transcribed to a nonlinear programming (NLP) problem by the hp-adaptive Radau pseudospectral method. To obtain the ascent trajectory with minimal propellant consumption, the resulting NLP problem is solved by SQP (sequential quadratic programming) algorithm. Based on the analysis, an evaluation criterion of TBCC engine matching project and an ascent strategy with boosters are produced.

Key words: High speed near space flight vehicle, TBCC engine size selection, Ascent strategy, Radau pseudospectral method

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