高超声速巡航飞行器推进系统建模与仿真  

Modeling and Simulation of Propulsion System for Hypersonic Cruise Vehicle

作　　者：邢永刚[1] 唐硕[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《计算机仿真》2011年第11期54-58,共5页Computer Simulation

摘　　要：关于飞行器控制优化设计问题,在高超声速巡航飞行器概念研究中涉及多学科设计优化。为了开发出快速预测推进系统性能的超燃冲压发动机模型是非常必要的。在飞行器机身-发动机一体化和Cowl–to-tail气动-推进界面划分的基础上,分别建立了进气道内压段、隔离段、燃烧室、尾喷管模型以及发动机总体性能模型。应用一维流分析方法进行了高超声速巡航飞行器推进系统性能分析。最后以某类高超声速巡航飞行器为研究对象,进行了飞行器推进系统性能仿真。仿真结果表明建立的推进系统模型和使用的一维流分析方法用在飞行器概念研究阶段是可行、有效的,为优化飞行器推进稳定性控制提供参考。To reduce computational cost in process of multidisciplinary design optimization for hypersonic cruise vehicle concept,it is very necessary to develop the scramjet engine model to rapidly predict the propulsion system performance.Based on the airframe integration with scramjet engine and cowl-to-tail aero-propulsion interface separation,the internal compression of inlet,isolator,combustion and nozzle as well as overall engine performance have been modeled,respectively.One-dimensional flow method was utilized to analyze the performance of propulsion system.Then a qusi-waverider hypersonic cruise vehicle was used to simulate the performance of propulsion system.The results of simulation reveal the models of propulsion system and analysis method are feasible and efficient in conceptual development of hypersonic cruise vehicle.

关 键 词：超燃冲压发动机 高超声速巡航飞行器 建模 仿真 推进系统 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]