现有的机载导弹弹射系统主要采用热气弹射和冷气弹射两种动力源，这两种弹射方式每次弹射后都需要及时维护更换，本课题组早期提出一种气液混合式弹射动力系统，弹射效果良好，基本免维护，但也存在分离角速度不可调的不足之处，为此提出了一种分离式气液混合弹射动力系统，采用双流量阀控制双多级液压缸的结构，有利于速度和角速度的控制。在对动力系统工作过程分析的基础上，应用流体动力学理论建立其数学模型；并在MATLAB平台上应用四阶龙格库塔算法编制仿真程序，对分离速度、角速度与阀口开度之间的关系进行理论分析；最后建立实验装置进行验证，实验结果证明方案可行。
Abstract
Heat air ejection and cool air ejection are mainly used in modern airborne missile launch systems,which need maintenance and replacement after each ejection. A novel gas-hydraulic hybrid ejection system was proposed,whose ejection effect ion was good and maintenance or replacement was free. But the angular velocity of the separation cannot be adjusted. Therefore,a separate gag-hydraulic hybrid ejection system was developed based on early systems,whose two flow valves were used to control two hydraulic cylinder with two stages to control the velocity and angular velocity of the load. Based on the analysis of the operation process of the dynamic principle of the system,a mathematical model was built using the fluid dynamics theory; and the fourth-order Runge Kutta algorithm simulation program was designed in Matlab platform. The relationships among the separation velocity,angular velocity and the valve port opening were obtained from the theoretical analysis. Finally an experimental system was established to verify the analysis results. The experimental results show that the scheme is feasible.
关键词
弹射 /
气液混合 /
分离式
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Key words
ejection
/
gas-hydraulic hybrid /
separate
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