摘要
针对卫星-卫星、卫星与大型部组件、功能模块与结构平台的在轨自动连接与分离的需求,基于通用化、标准化的接口设计理念,阐述了一种低功耗、小质量、小包络尺寸的柔性杆式弱撞击自动对接机构,在机构设计上采用柔性杆实现软连接,刚性周边杆实现纠偏和刚性锁紧,阻尼装置吸收对接碰撞能量的设计方案。采用Adams软件对机构的动力学过程进行了仿真建模,多工况动力学仿真试验表明所设计的柔性杆式弱撞击对接机构可在0.25 m/s弱撞击速度范围,20 mm横向对接容差以及±5°角度容差范围内实现可靠对接。并对柔性杆和刚性杆对仿真过程的差异进行了对比,结果表明,刚性与柔性的计算结果无明显差异。
Recent years autonomous on⁃orbit docking and separation has been highlighted with two satellites,one satellite and its large assemblies or functional modules.Based on interface design philosophy of universalization and standardization,this paper presents a kind of soft⁃rod low impact docking mechanism,characterized by low power consumption,low mass and small overall dimensions.The mechanism takes the soft central rod as the soft connection,three peripheral rigid rods as automatic alignment and rigidization,and a damping device as the impact energy absorber.A high fidelity docking mechanism is modeled in ADAMS software.Multi⁃conditional autonomous docking contact and impact procedure is analyzed.It proves that the current design is capable of reliable docking with impact velocity less than 0.25 meter per second,horizontal offset up to 20 millimeters and angular deviation up to 5 degrees.It also reveals that there is no significant difference between the rigid rod model and the flexible rod model.
作者
王文龙
朱汪
满剑锋
Wang Wenlong;Zhu Wang;Man Jianfeng(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2018年第S01期49-55,共7页
Journal of Northwestern Polytechnical University
关键词
航天器
交会对接
对接机构
动力学
spacecraft
rendezvous and docking
docking mechanism
dynamics
