载荷—火箭分离导向机构参数设计及动力学分析

针对载荷—火箭分离中易碰撞以及载荷部姿态的问题，以多体系统动力学理论为基础，在ADAMS中建立了针对一种新型分离导向机构的载荷—火箭分离虚拟样机模型，分别就分离导向机构支柱刚度、高度、滚轮与载荷部之间预载对分离结果的影响进行了计算分析。结果表明：刚度与高度的取值越大，分离过程中的分离最小间隙就越大，越有利于火箭与载荷部的成功分离；预载主要影响载荷部的姿态。基于此结果，设计了一套分离导向机构的匹配参数，并结合姿态控制律，利用ADAMS与Simulink软件包进行联合仿真，校验了这套设计参数可以保证火箭与载荷部的正常分离，姿控系统可以纠正载荷部的姿态偏差。本文采用的研究方法以及所获得的结论对采用该形式分离导向装置的载荷—火箭分离问题具有普适性。

Design and Dynamics Analysis of Separation Guiding Mechanism’s Parameters of Payload Rocket

Separation guiding mechanism is a new way to guarantee the successful separation between a payload and a rocket. In this article, A dynamics model is built for a new form of separation guiding mechanism to analyze the influence of parameters, including the strut’s stiffness, height and preload on the guiding mechanism, by considering the payload’s attitude and the minimum clearance between the rocket and the payload. The calculational results show that large value of stiffness and height is beneficial to the successful separation, while preload mainly influences the payload’s attitude. Based on the results, a group of parameters are designed. Besides, through a Co simulation of ADAMS with SIMULINK, a closed loop control system is proved that it could remedy the deviation which the payload already has before the separation and caused by the separation guiding mechanism deviation before the separation. For the separation problem of such a mechanism as this form, the research method used in this article and the results have general application.