皮卫星星箭分离机构运动系统设计

Kinematic System Design of the Pico-Satellite Separation Mechanism

为实现"皮星一号A"卫星无干涉分离,达到分离初始姿态要求,对皮卫星星箭分离机构运动系统进行了分析设计。首先,根据皮卫星与凸轮限位机构间的受力情况和能量守恒定理确定了凸轮轮廓尺寸和分离弹簧结构参数,在此基础上建立了星箭分离过程动力学模型,通过对动力学模型的数值计算确定满足无干涉分离条件的舱门扭簧弹性系数。星箭分离过程的仿真计算和试验校验了"皮星一号A"星箭分离机构可实现无干涉分离,皮卫星初始速度、角速率均满足所提出的各项初始分离姿态要求。

In order to realize the interference-free separation of the ＇ ZDPS-1 A＇ satellite from the rocket, and to meet the demand of initial attitude of separation, a novel pico-satellite separation mechanism kinematic system is designed and developed. Firstly, according to the force between the satellite and the cam mechanism and energy conservation principle, the size of the cam contour and structure parameters of the separation spring are designed. And then, on the basis of above results, the dynamics model of separation process is established. Finally, through numerical calculation of the dynamics model, elasticity coefficient of the torsional spring is determined to meet the requirement of non-interference separation. Simulation results and verification experiments show that the ＇ZDPS-1A＇ satellite can separate successfully form the rocket without any interference. Furthermore, the initial velocity and angular rates of the satellite completely satisfies designed technical indexes.