摘要
为了真实的反映高超声速飞行器机体、发动机间的耦合特性,首先建立了超燃冲压发动机预压缩面、进气道、燃烧室、尾喷管、外喷管的数学模型,推导了以敏感度方程表示的机体对发动机的耦合模型和发动机对机体的耦合模型,然后建立了飞行器点火飞行段的数学模型,并进行了简单的校核,最后基于变结构控制理论设计了一种简单的开环+闭环的控制系统。模型的简单校核及控制系统仿真表明建立的模型定性上符合高超声速点火飞行段的飞行特性,设计的控制器在存在干扰、噪声、拉偏时能够快速收敛,且鲁棒性强。
The main challenge of the modeling of air-breathing hypersonic vehicle was that the propulsion system and airframe were so highly coupled that it was hard to be separated. The model of scramjet was derived by one-dimensional aero/thermo analysis of flow; the sensitivities were set up with the linearizing of model. We got the coupling model from scramjet to airframe by the analysis of external nozzle with two-dimensional dilatation wave theory. The whole model of the hypersonic vehicle with the engine operated was established and a simple control base on variable structure control was designed. The simple model checking and simulation showes that the model meet the characteristics of hypersonic flight ; the controller can get a fast convergence and can resist the disturbance, perturbation and noise during the flight.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第5期1509-1514,共6页
Journal of Astronautics
基金
国家863计划航天支撑基金(2008-HT-XGD)
关键词
高超声速飞行器
耦合模型
变结构控制
Hypersonic vehicle
The coupling model
Variable structure control
作者简介
孟中杰（1982-），男，博士生，研究方向为飞行器制导与控制。通信地址：陕西省西安市友谊西路127号西北工业大学航天学院（710072）电话：（029）88460366—802 E-mail：zhongjiemeng@hotmail．com
