星上控制力矩陀螺群隔振平台的动力学特性

张尧; 黄庭轩; 徐世杰

星上控制力矩陀螺群隔振平台的动力学特性

北京航空航天大学宇航学院, 北京 100191

基金项目: 中国航天科技集团公司航天科技创新基金和国家自然科学基金资助项目(10902003)

详细信息

中图分类号: V 412.4
计量
- 文章访问数: 3359
- HTML全文浏览量: 144
- PDF下载量: 609
- 被引次数: 0
出版历程
- 收稿日期: 2010-08-24
- 网络出版日期: 2012-01-30

Dynamic characteristic of vibration isolation platform of control moment gyroscopes on satellites

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 为能够给星上有效载荷提供一种超静环境,提出一种星上控制力矩陀螺群(CMGs,Control Moment Gyroscopes)的隔振方案,并对所使用的隔振平台的动力学特性进行研究分析.首先介绍了不同参数模型的隔振元件工作原理和参数特性;其次利用牛顿-欧拉法对含有隔振平台和CMGs的卫星进行动力学建模;最后通过频域和时域的方法分析并对比了各个参数模型下的隔振平台力衰减特性以及对星体姿态稳定度的改善程度.结果表明:两参数加调谐质量阻尼器模型下的隔振平台对共振峰值有一定的衰减作用,三参数模型下的隔振平台在力衰减和对姿态稳定度的改善程度上要明显优于其他2种模型.
- 控制力矩陀螺群 /
- 两参数模型 /
- 调谐质量阻尼器 /
- 三参数模型 /
- 隔振平台
Abstract: An isolation scheme for control moment gyroscopes (CMGs) was put forward and used on satellite which can provide an ultra quiet environment for the optical payloads, and dynamic characteristic of the vibration isolation platform for CMGs was analyzed in detail. The theories of the vibration isolators of different parameter models and the reason of choosing certain parameters were studied. A whole-satellite dynamic model with vibration isolation platform and CMGs was constructed by Newton-Euler method. The force transfer rates of different parameter models were compared by using frequency domain method. The ameliorative degrees of vibration isolation device with the two-parameter and three-parameter model to the satellite attitude stabilization were compared by using time domain method. The simulation results show that the vibration isolation platform with two-parameter adding tuned mass damper model can attenuate the resonance amplification peak to a certain extent, and the vibration isolation platform with three-parameter model had the best performance in the three models.
- control moment gyroscopes /
- two-parameter model /
- tuned mass damper /
- three-parameter model /
- vibration isolation platform

HTML全文

参考文献(1)

[1] John P H.Control moment gyro with vibration isolation:United States,5820078 .1998-10-13 [2] Smith D W,Davis T S.Methods and apparatus for tuned axial damping in rotating machinery with floating dearing cartridge:United States,0268735 .2005-12-08 [3] Davis L P,Hyde T T.Moment control unit for spacecraft attitude control:United States,6340137 .2002-01-22 [4] Agrawal B.Jitter control for imaging spacecraft //The 4th Recent Advances in Space Technologies International Conference.Istanbul,Turkey:IEEE Conferences,2009:615-620 [5] 关新,王全武,郑钢铁.飞轮拟主动隔振方法 [J].宇航学报, 2010,31(7):1870-1876 Guan Xin,Wang Quanwu,Zheng Gangtie.A pseudo-active vibration isolation method for reaction wheels [J].Journal of Astronautics,2010,31(7):1870-1876(in Chinese) [6] 金磊.使用角动量交换装置的航天器姿态动力学与控制问题研究 .北京:北京航空航天大学宇航学院,2008 Jin Lei.Study on attitude dynamics and control of spacecraft using angular momentum exchange devices .Beijing:School of Astronautics,Beijing University of Aeronautics and Astronautics,2008(in Chinese) [7] Dasgupta B,Mruthyunjaya T S.A Newton-Euler formulation for the inverse dynamics of the Stewart platform manipulator [J].Mechanism and Machine Theory,1998,33(8):1135-1152 [8] 张军,徐世杰.柔性航天器IPACS建模与动力学分析 [J].北京航空航天大学学报,2006,32(4):377-381 Zhang Jun,Xu Shijie.IPACS modeling and dynamical analysis of a flexible spacecraft [J].Journal of Beijing University of Aeronautics and Astronautics,2006,32(4):377-381(in Chinese) [9] 汤亮,贾英宏,徐世杰.使用单框架控制力矩陀螺的空间站姿态控制系统建模与仿真 [J].宇航学报,2003,24(2):126-131 Tang Liang,Jia Yinghong,Xu Shijie.Modeling and simulation of attitude control for space station with SGCMG systems [J].Journal of Astronautics,2003,24(2):126-131(in Chinese)

施引文献

资源附件(0)

访问统计