航空学报 > 2014, Vol. 35 Issue (6): 1651-1664   doi: 10.7527/S1000-6893.2013.0457

面向跟踪的吸气式高超声速飞行器动力学建模

李海宁, 雷虎民, 翟岱亮, 邵雷, 李炯   

  1. 空军工程大学 防空反导学院, 陕西 西安 710051
  • 收稿日期:2013-09-03 修回日期:2013-11-04 出版日期:2014-06-25 发布日期:2014-06-20
  • 通讯作者: 雷虎民,Tel.:029-84789196 E-mail:hmlei@163.com E-mail:hmlei@163.com
  • 作者简介:李海宁男,博士研究生。主要研究方向:机动目标跟踪,非线性估计。 E-mail:lhn_0403@163.com;雷虎民男,博士,教授,博士生导师。主要研究方向:飞行器导航、制导与控制。Tel:029-84789196 E-mail:hmlei@163.com;翟岱亮男,博士研究生。主要研究方向:多目标跟踪,非线性估计。 E-mail:quietzdl@126.com;邵雷男,博士,讲师。主要研究方向:飞行器导航、制导与控制,多模自适应控制。 E-mail:shaoleijing@126.com;李炯男,博士,讲师。主要研究方向:飞行器导航、制导与控制,多模复合制导。 E-mail:gracefulool@163.com
  • 基金资助:

    航空科学基金(20130196004)

Tracking Oriented Dynamics Modeling of Airbreathing Hypersonic Vehicles

LI Haining, LEI Humin, ZHAI Dailiang, SHAO Lei, LI Jiong   

  1. College of Air and Missile Defense, Air Force Engineering University, Xi'an 710051, China
  • Received:2013-09-03 Revised:2013-11-04 Online:2014-06-25 Published:2014-06-20
  • Supported by:

    Aeronautical Science Foundation of China(20130196004)

摘要:

根据吸气式高超声速目标的动力学特性,对传统动压加速度模型的局限性做了分析。在重力转弯模型框架中,基于超燃冲压发动机的推力产生机理以及高超声速流场的斜激波方程和普朗特梅叶方程,提出了描述目标切向加速度的推广模型和目标法向加速度的斜激波、非解析混合模型。随后,基于高超声速流场工程近似算法对吸气式高超声速目标的模式特征进行分析,并设计了均匀模型集。对攻角、滚转角以及发动机状态发生突变的高超声速机动目标跟踪问题进行了仿真研究。结果表明,新的模型集能够较好地适应目标突然加速和转弯机动,有效跟踪助推跳跃机动的吸气式高超声速目标。

关键词: 高超声速飞行器, 机动目标跟踪, 动力学模型, 多模型方法, 斜激波方程

Abstract:

The disadvantages of traditional acceleration model based on dynamic pressure are analyzed according to dynamic characteristics of airbreathing hypersonic targets. In the framework of gravity turn modeling structure, a generalized model for tangent acceleration along with a mixed model consisting of oblique shock and a non-analytical models for normal acceleration is proposed according to thrust generating mechanism of scramjet engine as well as the oblique shock equation and Prandtl-Meyer equation of hypersonic flow field. Then, the mode space corresponding to these new models is analyzed with approximate calculation methods for hypersonic flow and a uniformly distributed model set is designed. A tracking scenario of hypersonic target maneuvering with instant change of angle of attack, roll angle and engine state is simulated. Simulation results demonstrate the efficiency of the new model set for tracking hypersonic targets with instant acceleration and turn.

Key words: hypersonic vehicles, maneuvering target tracking, dynamic model, multi-model approach, oblique shock equation

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