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本文讨论了非自旋稳定卫星用的以螺旋压缩弹簧作为分离冲量的分离系统。按分离弹簧、卫星安装对接面、未级安装对接面和夹紧/解锁机构4个组成部分,阐述系统设计及其工作。详细介绍了用于数字计算机设计研究的刚体分离数学模型的建立。分析的重要参数包括各弹簧的特性及配置、卫星与未级的重心、质量、惯性特性及其偏移、卫星与未级之间的轴线不重合度及偏差、残余的初始角速度、末级残余推力。可以看出,分离弹簧的精确匹配有助于减少分离误差,用双摆试验对理论分析作了试验验证。这些试验采用了卫星、末级动力学相拟模型和全尺寸的分离装置飞行件。此外,还对轨道地球物理台(OGO)、卫星与船帆星座(VeLa)卫星的分离系统地面试验和轨道飞行测量结果作了介绍,说明系统的精度与理论分析的相关性。
In this paper, a separation system using helical compression springs as separation impulses for non-spin-stable satellites is discussed. According to the separation of spring, satellite mount docking surface, not installed on the mating surface and clamping / unlocking mechanism of the four components, elaborated on the system design and its work. The establishment of mathematical model of rigid body separation for digital computer design is introduced in detail. The important parameters analyzed include the characteristics and configuration of each spring, the center of gravity and mass of the satellites, the inertial characteristics and their offsets, the misalignments and deviations of the axis between satellites and the unscented, the residual initial angular velocities, the final residuals thrust. It can be seen that the precise matching of the separation springs helps to reduce the separation error, and the double-pendulum test is used to verify the theoretical analysis. These experiments used satellites, final-phase kinetic modeling and full-size separation device flight pieces. In addition, the ground test and orbital flight measurement results of the separation system of Orbital Earth Observatory (OGO), Satellite and Sailing Constellation (VeLa) satellites are also introduced. The correlation between system accuracy and theoretical analysis is also illustrated.