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。
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 PrandtI-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.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2014年第6期1651-1664,共14页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金(20130196004)~~
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
hypersonic vehicles
maneuvering target tracking
dynamic model
multi-model approach
oblique shock equation
