文档介绍：摘要
伴随着中国航天技术的开发,航天器交会对接技术的发展迫在眉睫。航天器的交会对接应用技术研究过程中,验证控制系统方案设计,提高可靠性的飞船在轨道上,失去对飞机的控制,降低风险的正确性,半实物仿真测试系统是必要的。飞船在空间环境有两大特点:失重和真空,地面模拟试验设备,因此考虑引入空气轴承表中的半实物仿真系统(即气浮台)是重力加速度的影响下。气浮机由压缩空气形成的空气轴承和轴承之间的间隙膜,使所悬挂的空气轴承表抵消重力的影响,并实现近似的相对运动的摩擦条件下,模拟外层空间飞船干扰例句力学环境。由于飞船控制系统,气浮试验台可以模拟零重力条件下,航天器姿态动力学与控制系统研究的理想平台,在地面条件下在轨道上的航天器的姿态运动的物理模拟的核心部件。
为了研究多体卫星地面实物仿真测试方法,根据动量矩定理,文章建立了动力学理论刚体转动配件及三轴气浮台中心直接和级联情况下的动态模型和依据灵活的动力理论气浮台平台创建一个三度的自由度力学模型。根据动力学方程的旋转部分的质量特性的精确建模可以被分析和计算部件旋转的空气轴承表中对身体的运动特性。在这个过程中的姿态变化的气浮平台的质心变化的公式和所需的重量,基于空间飞行器的姿态动力学理论的空气轴承表平台失去平衡的时刻取得的公式推导出一个沉重的作用。平台重量变形有限元方法结构不平衡的点,探索结构上的不平衡力矩的方向刚度参数的参数值组合的概念提出的零平衡点的平台结构的不平衡力矩平台结构参数影响大小的关系,即灵敏度之间的平衡和不平衡力矩的平台的结构刚性。
关键词:气浮台;缓冲装置;转动附件;力矩陀螺;不平衡度
Abstract
Along with the development of China's space technology, spacecraft rendezvous and docking technology development is imminent. and docking related technologies are getting more and plex. In the course of the study, the rendezvous and docking technology validation fluid control system thecorrectness, to improve the simulation system test is the spacecraft in orbit in order to reduce the risk of aircraft control, physical simulation of the system test is necessary. Space environment has two main characteristics: weight loss and vacuum. Flotation units formed pressed air gap between the air bearing and the bearing film, so that the suspension of the air bearing table to counteract the effects of gravity, and to achieve the approximation of the relative movement of the friction conditions, the analog outer space spacecraft interferencetorque mechanical environment. As the spacecraft control system, the the flotation test stand can simulate zero gravity conditions, the ideal platform for Spacecraft Attitude Dynamics and Control System, the ponent of the physical simulation of the conditions on the ground in orbit spacecraft attitude motion.
Accordin to the thery on the spacecraft attitude ics the formual for the platform structure mass-center displaysment and for the c