卫星筒式偏心在轨分离动力学分析  

Dynamics analysis of the constrained and centroid biased on-orbit satellite separation

作　　者：蒋超[1] 王兆魁[1] 范丽[2] 张育林[1] 

机构地区：[1]清华大学航天航空学院,北京100084 [2]装备指挥技术学院科研部,北京101416

出　　处：《飞行力学》2010年第1期76-79,共4页Flight Dynamics

摘　　要：偏心安装的子卫星在轨分离是一类特殊的卫星在轨分离问题。为了给分离地面试验和分离系统设计提供依据,在惯性参考系中分析了筒式偏心在轨分离问题的运动特性。以刚体运动学原理和动力学动量定理、角动量定理及能量定理为依据,建立了分离过程的动力学模型。运用数值求解方法,给出了不同初始条件下的模型求解算例,并对求解结果进行了比较和分析。分析结果表明,分离弹簧物性参数是影响分离速度的主要因素;卫星相对安装位置是影响分离角速度的主要因素。The constrained and centroid biased on-orbit satellite separation, which a sub-satellite fits in with a centroid offset, is a special kind of on-orbit satellite separation problems. In order to provide references for the ground separation tests and the separation system design, characteristics of the constrained and centroid biased on- orbit satellite separation were analyzed in inertial reference frame. By using kinematics principles of a rigid body, as well as momentum theorem, angular momentum theorem and kinetic energy theorem of dynamics, the dynamic model of the separating motion was formulated. Then, using the numerical solution, model solution examples with different initial conditions were offered; also solution results were compared and analyzed. It shows that the main factor of separation velocity is affected by physical parameters of the separation spring, the original fixing distance between two satellites is the main factor which affects the separation angular velocity.

关 键 词：分离 分布式航天器 动力学分析 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]