摘要
为研究卫星分离姿态的影响因素,运用动力学理论和虚拟样机技术,推导卫星姿态动力学,对比理论计算值与ADAMS仿真结果,验证模型的正确性。运用ADAMS虚拟样机技术进行多星分离释放仿真,改变弹簧刚度系数与弹簧初始压缩量,对比理论计算值,分析不同因素对卫星分离后运动状态的影响;采用不同的分离释放方案,分析星间最小距离,验证卫星分离的安全性与可靠性。
In order to study the influence factors of satellite separation attitude,the dynamic theory and virtual prototype technology are used to derive the satellite attitude dynamics,and the correctness of the model is verified by comparing the theoretical calculation value with the ADAMS simulation results.The multi-satellite separation and release simulation are carried out by ADAMS virtual prototype technology:change the spring stiffness coefficient and the initial compression of the spring,compare the theoretical calculation values,and analyze the different factors on the satellite separation about the impact of the post-motion state.Different separation and release schemes are applied to analyze the minimum distance between satellites and verify the safety and reliability of satellite separation.
作者
陈金宝
霍伟航
陈传志
崔继云
江安澜
CHEN Jinbao;HUO Weihang;CHEN Chuanzhi;CUI Jiyun;JIANG Anlan(Academy of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;Key Laboratory of Deep Space Star Catalog Detection Mechanism Technology of Ministry of Industry and Information Technology,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China)
出处
《机械制造与自动化》
2023年第2期7-10,共4页
Machine Building & Automation
基金
国家自然科学基金项目(52075242)
江苏省自然科学基金项目(BK20180437)。
关键词
一箭多星
虚拟样机仿真
姿态动力学
分离安全性
multi-satellite launching
virtual prototype simulation
attitude dynamics
separation safety
