大型构件伸展与锁(压)紧释放技术  

Deployment and Hold-down and Release Mechanism of Large Space Component

作　　者：于登云[1] 孙京[1] 马兴瑞[2] 

机构地区：[1]中国空间技术研究院,北京100094 [2]航天科技集团公司,北京100037

出　　处：《航天器工程》2007年第1期23-27,共5页Spacecraft Engineering

摘　　要：介绍了大型构件伸展与锁(压)紧释放机构的国内外发展概况及主要分类形式。从动力源的选择和力(矩)裕度分析、传动副的选择与润滑、间隙非线性关节的建模与分析、改善结构的阻尼特性四个方面论述了伸展机构的关键技术。讨论了支撑与紧固点的选择、压紧点的选择、锁(压)紧与释放形式的选择和实现、锁(压)紧预载设计及加载和测量方法等四项锁紧释放机构的关键技术,展望了伸展与锁紧释放机构的前景。The sort of deployment mechanism, hold-down and release mechanism, and their general situation are summarized in this paper. There are four key technologies of deployment mechanism being analyzed, such as choosing power and analyzing the force （torque） margin, choosing the transmission and lubrication method, modeling and analyzing of the clearance nonlinear joint, improving the structural damp characteristic. Afterward other four key technologies of hold-down and release mechanism are discussed, such as choosing the supporting and fixing points, selecting the hold-down points, selecting and realizing the methods of the hold-down and release, designing the pre-load and the method of loading and measurement. In the end, the development direction of the Chinese spacecraft deployment mechanism and hold-down and release mechanism has been expected.

关 键 词：航天器 伸展机构 锁(压)紧释放机构 

分 类 号：V423[航空宇航科学与技术—飞行器设计]