多变量调节固冲发动机动力学建模及仿真  

Dynamic modeling and simulation of multivariableadjustable ducted rocket

作　　者：邵明玉[1] 王志刚[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2015年第6期782-788,共7页Journal of Solid Rocket Technology

摘　　要：分别建立了多变量调节固冲发动机各部件的性能/平衡模型、动力学模型以及扰动传播模型,并综合为多变量调节固冲发动机动力学模型。在此基础上,对飞行条件扰动以及进气道/燃气发生器/喷管调节时,发动机的响应特性进行了仿真分析,并分析了扰动的传播过程及不同扰动传播过程处理方法对发动机响应的影响。结果表明,进气道调节不会改变推力和补燃室压强的稳态值,燃气流量调节对推力有较大影响,喷管调节对补燃室压强有较大影响。The equilibrium model, dynamic model of each component of muhivariable-adjustable ducted rocket and the disturb- ance propagation model were built, and synthesized into the dynamic model of muhivariable adjustable ducted rocket. Based on this model,the response of ducted rocket to the flight condition disturbance and inlet/gas-generator/nozzle adjustment was simulated and analyzed.The effects of disturbance propagation dynamic process and its treatment method on ducted rocket were also studied.The re- suits show that, the steady-state value of thrust and combustor pressure won＇t be changed due to inlet adjustment,while the gas gen- erator adjustment and nozzle adjustment have great influence on thrust and combustor pressure respectively.

关 键 词：固冲发动机 多变量调节 动力学建模 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]