In order to solve the contradiction between the opening and closing time of the high speed on/off valve for space propulsion systems of the liquid rocket engine, a pneumatic pilot-operated high speed on/off valve is proposed and multiobjective optimization for the opening and closing time of the valve is carried out in this paper. Based on the analysis of the working mechanism of the valve, the mathematical models for the pilot valve and the main valves are established respectively. The Plackett-Burman design is used to select the optimization variables which influence the performance of the response time significantly. The central composite design is used to obtain the sample points and establish second-order response surface models of the response time. The NSGA-II is used to obtain the Pareto front of the optimization objectives. The optimized opening and closing time can be reduced by 17.7% and 37.4% respectively. A prototype based on the optimized parameters is manufactured and tested to verify the accuracy of the multiobjective optimization results. The test results verify the validity of the optimization approach for the proposed valve in this paper.

中文翻译：

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气动先导式高速开关阀响应时间的多目标优化研究

为解决液体火箭发动机空间推进系统高速开关阀的开启和关闭时间之间的矛盾，提出了一种气动先导式高速开关阀，并对其进行多目标优化。阀门的关闭时间在本文中进行。在分析阀门工作机理的基础上，分别建立了先导阀和主阀的数学模型。Plackett-Burman设计用于选择优化变量，这些优化变量会显着影响响应时间的性能。中央复合设计用于获取采样点并建立响应时间的二阶响应表面模型。NSGA-II用于获得优化目标的Pareto前沿。优化的打开和关闭时间可以分别减少17.7％和37.4％。制造并测试了基于优化参数的原型，以验证多目标优化结果的准确性。测试结果验证了本文提出的阀门优化方法的有效性。