摘要
为了揭示间隙对航天器可展结构动力学性能的影响 ,基于间隙铰的接触变形模式 ,建立了含间隙的可展结构动力学模型。对含间隙的典型可展结构动力学进行了仿真分析 ,仿真结果表明间隙对可展结构展开过程动力学性能影响较大。在展开起始阶段 ,间隙铰关节有较大的接触力 ;由于间隙的影响 ,产生持续的脉冲式碰撞接触力 ;随着间隙增大 ,碰撞力幅值有增大的趋势 ,碰撞次数减少。摩擦可能激起系统振动 ,增加系统动力学非线性 ;同时 。
Based on contact deformation mode of clearance′s joints, dynamic equations of the deployable structures with clearances is developed to find out the influences on dynamic performances of the structure for spacecraft. Dynamics of a typical deployable structure with a clearance is simulated, and the simulation results show that dynamic performances of the structure are greatly influenced by the clearance during deploying. At beginning, there are bigger contact forces, and then come into being impulse impact forces continuously. As dimensions of the clearance increase, amplitudes of impact forces are trend to increase and times of impacts decrease. Frictions could result in non linear dynamic response, but at the same time, they could have effects on suppressing dynamic disturbances for the deployable structure.
出处
《导弹与航天运载技术》
北大核心
2002年第6期42-46,共5页
Missiles and Space Vehicles
基金
国家航天 86 3高技术项目 ( 86 3-2 -2 -4 -2 )
国家自然科学基金 ( 5 990 5 0 1 6 )资助
