基于ADAMS的火箭分离机构动力学分析及仿真  

Dynamic analysis and simulation of the rocket separation mechanism based on ADAMS

作　　者：陈力[1] 张明[1] 颜驿濛 朱冠宁 Chen Li;Zhang Ming;Yan Yimeng;Zhu Guanning(Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology ofFlight Vehicle, Nanjing University of Aeronautics & Astronautics, Jiangsu Nanjing, 210016, China)

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点科学实验室,江苏南京210016

出　　处：《机械设计与制造工程》2020年第7期7-11,共5页Machine Design and Manufacturing Engineering

摘　　要：以多体系统动力学为理论基础,在动力学分析软件ADAMS中建立了火箭整流罩分离模型,对该分离机构模型进行动力学仿真计算与分析,得到了分离机构的动力学仿真计算结果。对整流罩和箭体分离过程中的速度和角速度进行分析,比较各个载荷随时间的变化情况,结果表明分离火箭推力对分离机构在分离过程中速度和姿态的变化影响最大。Based on the theory of multi-body system dynamics,a fairing of rocket separation model is established in ADAMS.The dynamic simulation calculation and analysis of the separation mechanism model are carried out and the dynamic simulation result parameters of the separation mechanism are obtained.The velocity and angular velocity of the fairing and the arrow body during the separation are analyzed.Comparing the variation of each load over time,the results show that the separation rocket thrust has the greatest influence on the velocity and attitude of the separation mechanism.

关 键 词：火箭 整流罩 分离机构 动力学仿真 ADAMS 

分 类 号：V226[航空宇航科学与技术—飞行器设计]