喉栓式变推力固体火箭发动机压强控制模型分析  

Analysis of fluid dynamic control model for pintle controlled solid rocket motor

作　　者：成沉 鲍福廷[1] 刘旸[1] 许昊[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》2013年第6期748-752,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(51005179)

摘　　要：针对喉栓式变推力固体火箭发动机气动控制过程,用控制工程的方法将喉面-压强响应系统近似为一阶线性系统,建立了系统传递函数。用传递函数中决定响应速度的时间常数对影响压强响应的因素进行了分析,得到了发动机设计参数对压强响应的影响规律。考虑线性化带来的误差,对传递函数进行了线性修正,用修正后的传递函数对采用开环控制的发动机系统压强响应进行求解,得到了压强响应曲线的近似解析解及理论响应时间,并分析了压强响应速度相对于喉栓作动速度的延迟。该求解办法可指导试验设计并提供快速有效的工程估算方法。To study the control process of the pinfle controlled solid rocket motor,the response system between throat area and pressure was approximated to a first order linear control system, and the transfer function was established to analyze the pressure re- sponse rate.Then the influencing factors on the pressure response were analyzed by the transfer function.Considering the error of the linearization,the transfer function was modified to solve the pressure response of the open-loop rocket system.Then the approximate analytical solution of the pressure response and the response time was obtained.At last, the delay between the pressure response rate and the pintle moving velocity was discussed.The method can be used for guiding the experiment design, and providing rapid and valid engineering estimation.

关 键 词：喉栓 固体火箭发动机 压强响应 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]