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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2015年第6期782-788,共7页
Journal of Solid Rocket Technology
关键词
固冲发动机
多变量调节
动力学建模
ducted rocket
muhivariable-adjustment
dynamic modeling
