遥感卫星在轨微振动测量数据分析

介绍某遥感卫星的在轨微振动测量方案,并从背景噪声、扰动源特征、星体结构传递特征三个方面对测量数据进行分析。由测试数据发现,控制力矩陀螺（CMG）和动量轮引起的局部扰动较大,而传递至有效载荷处的扰动主要由CMG和双轴天线引起。星体结构对微振动有良好的衰减作用,有效载荷安装面的响应相对于振源得到了大幅衰减。     

光学遥感卫星微振动抑制方法及关键技术

针对光学遥感卫星面临的微振动对成像质量影响的问题,对微振动抑制设计方法和关键技术进行了论述。首先对动量轮、控制力矩陀螺、扫摆机构等主要扰动源的机理和特征进行分析,然后从传递路径设计、微振动源抑制、降低有效载荷敏感性三个方面介绍了微振动抑制方法,最后结合遥感卫星的研制过程给出了微振动抑制设计的实例。     

Design and experiments of an active isolator for satellite micro-vibration

In this paper, a soft active isolator（SAI） derived from a voice coil motor is studied to determine its abilities as a micro-vibration isolation device for sensitive satellite payloads. Firstly,the two most important parts of the SAI, the mechanical unit and the low-noise driver, are designed and manufactured. Then, a rigid-flexible coupling dynamic model of the SAI is built, and a dynamic analysis is conducted. Furthermore, a controller with a sky-hook damper is designed. Finally,results from the performance tests of the mechanical/electronic parts and the isolation experiments are presented. The SAI attenuations are found to be more than 20 d B above 5 Hz, and the control effect is stable.     

双状态非线性隔振器参数设计与试验研究

为有效抑制在轨微振动对有效载荷指向精度的影响,并改善其发射段动力学环境,设计了一种双状态非线性隔振器,利用发射与在轨状态载荷条件的差异,使其在两个阶段有不同的隔振频率。分析了各设计参数对发射段动态响应以及在轨隔振性能的影响,提出了隔振器参数设计方法。试制了隔振器样件,进行了静力学测试,并按照发射和在轨两种状态的力学环境进行了动力学试验,测试了隔振器在两种状态下的传递率。试验结果表明,隔振器在发射段准静态载荷作用下可避免出现大变形,并显著改善星载设备的动力学环境。在轨时可有效隔离微振动,将5Hz以上频段受到的扰动幅度下降92%以上。     

便携式微振动可视化测量仪的设计与实现

针对微振动难以察觉、振动测量中接触式的电测法需要布置大量传感器、非接触式的光测法测量速度慢且价格昂贵的问题,设计了基于视觉的便携式微振动可视化测量仪。提出了基于盲源分离的灰度平均测量算法以提取振动信号,结合视频放大算法实现微振动可视化,并基于嵌入式开发平台将测量系统集成为便携式仪器。在试验中,良好的可视化效果和准确的测量结果验证了所提方法的有效性,可为振动测量中存在的问题提供新的解决思路。     

Recent advances in precision measurement & pointing control of spacecraft

There exists an increasing need for precision measurement & pointing control and extreme motion stability for current and future space systems, e.g., Ultra-Performance Spacecraft (UPS). Some notable technologies of realizing Ultra-Pointing (UP) ability have been developed particularly for Ultra-accuracy Ultra-stability Ultra-agility (3U) spacecraft over recent decades. Usually, Multilevel Compound Pointing Control Techniques (MCPCTs) are deployed in aerospace engineering, especially in astronomical observation satellites and Earth observation satellites. Modern controllers and/or algorithms, which are a key factor of MCPCTs for 3U spacecraft, especially the jitter phenomena that commonly exist in a UPS Pointing Control System (PCS), have also been effectively used in some UP spacecraft for a number of years. Micro-vibration suppression approaches, however, are often proposed to deal with low-level mechanical vibration or disturbance in the microgravity environment that is common for UPS. This latter approach potentially is one of the most practical UP techniques for 3U tasks. Some emerging advanced Disturbance-Free Payload (DFP) satellites that exploit the benefits of non-contact actuators have also been reported in the literature. This represents an interesting and highly promising approach for solving some challenging problems in the area. This paper serves as a state-of-the-art review of UP technologies and/or methods which have been developed, mainly over the last decade, specifically for or potentially could be used for 3U spacecraft pointing control. The problems discussed in this paper are of reference significance to UPS and millisecond optical sensors, which are involved in Gaofeng Project, deep space exploration, manned space flight, and gravitational wave detection.