摘要
为了在液体火箭发动机试验过程中缩短低温气动阀的响应时间,减少非线性求解阀门动态响应的计算量,提升试验过程中的安全性与可靠性,根据低温气动阀的工作原理,构建阀门的动态响应非线性传递模型,并在此基础上,通过引入变步长系数与定义遗忘因子,在四阶龙格-库塔法基础上,构建了一种动态递推龙格-库塔法的非线性动力学求解方法,并提出响应速度的改进方案。最后通过实例的验证与仿真,为提升低温气动阀响应速度提供了一种方法指导,为提高液体火箭发动机试验技术提供了支持。
To shorten the dynamic responding time of cryogenic pneumatic valve, reduce the cal-culated amount of nonlinear solution for valve dynamic response, and improve the reliability and se-curity of cryogenic pneumatic valve, a dynamic responding non-linear transferring model of cryogenic valve were built in accordance with the operating principle of cryogenic pneumatic valve. Afterwards, based on four-stage Runge-Kutta algorithm, a nonlinear dynamics solution method for the dynamic recursive Runge-Kutta algorithm was constructed by means of the introduction of variable step length coefficient and definition oblivion factor. A scheme to improve the response speed is proposed. This method was demonstrated and validated by a sample. Consequently, this method has offered guidance for reducing dynamic responding time of cryogenic pneumatic valve, and provided a support for im-proving the ability to rationally and exactly evaluate the performance of liquid rocket engine.
出处
《火箭推进》
CAS
2013年第6期23-28,共6页
Journal of Rocket Propulsion
关键词
非线性分析方法
低温气动阀
动态响应
龙格-库塔法
nonlinear analysis method： cryogenic pneumatic valve
dynamic responding
Runge-Kutta algorithm
