| 摘要: |
| 本文分析了一种机构型火箭牵制缓释机构的运动学过程，利用牛顿-欧拉方程对机构的缓释阶段进行了动力学建模，针对动力学模型中的弹性元件，提出了一种逼近-校正法对其进行分析。设计了一种基于此机构的结构参数，将此结构参数代入到模型中，对所建立的动力学模型进行了Matlab数值仿真和多体动力学仿真，得到了目标缓释力下的气缸力时序曲线，验证了其正确性。并且将动力学模型计算结果与去除惯性力的静力学模型计算结果进行了对比，分析了机构惯性力的影响，为此类机构缓释阶段的控制奠定了基础。最后进行了相关实验分析。 |
| 关键词: 牵制缓放机构；缓释放；牛顿-欧拉方程；动力学模型；数值仿真；多体动力学仿真 |
| 基金项目: |
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| Dynamic Modeling and Analysis of A Mechanism-type Holding Release Device |
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Chen Qingbin1, Han Xianguo2, Li Meng3, Ju Long4
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1. Beijing Institute of Mechanical and Electrical Engineering, Beijing 100074;2. School of Mechanical Engineering and Automation, Beihang University, Beijing 100089;3. School of Automation Science and Electrical Engineering, Beihang University, Beijing 100089;4. Landspace Technology Co., Ltd., Beijing 100176
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| Abstract: |
| The kinematical process of the rocket drag release mechanism was analyzed, and the mechanism’s release stage was modeled using Newton Euler equations. An approximation correction method was proposed for analyzing the elastic elements in the dynamic model. A structural parameter based on this mechanism was designed and incorporated into the model. Based on Matlab, numerical simulation and multibody dynamics simulation were performed on the established dynamic model, and the cylinder force timing curve under the target release force was obtained, verifying its correctness. The dynamic model calculation results were compared with the static model calculation results that removed the inertial force, and the impact of the inertial force on the mechanism was analyzed, laying a foundation for the slow release control of the rocket drag release mechanism. Then relevant experimental analysis was conducted. |
| Key words: diversion of release agencies；slow release；Newton Euler equations；kinetic models；numerical simulation；multi body dynamics simulation |
