星载飞轮双状态隔离用变刚度摩擦阻尼器

刘国勇; 侯永涛; 刘海平; 赵鹏鹏; 朱冬梅

doi:10.37188/OPE.20202807.1539

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星载飞轮双状态隔离用变刚度摩擦阻尼器

微纳技术与精密机械 | 更新时间：2020-08-13

- 星载飞轮双状态隔离用变刚度摩擦阻尼器
- Variable stiffness friction damper for dual-state isolation of flywheel on satellite
- 光学精密工程 2020年28卷第7期页码：1539-1545
- 作者机构：
  
  1.北京科技大学机械工程学院, 北京 100083
  2.中国兵器工业第二○八研究所, 北京 102202
- 作者简介：
  
  [ "刘国勇(1969-), 男, 湖北宜城人, 副教授, 博士, 1992年于湖北工业大学获得学士学位, 2007年于北京科技大学获得博士学位, 主要从事复合结构减隔振研究与开发、多物理场耦合建模与优化的研究。E-mail:gy_liu666@ustb.edu.cn" ]
  [ "侯永涛(1993-), 男, 河北承德人, 助理工程师, 硕士, 2017年于天津工业大学获得学士学位, 2020年于北京科技大学获得硕士学位, 主要从事产品结构设计、减振降噪方面的研究。E-mail:mechanical_hyt@163.com" ]
  [ "刘海平(1982-), 男, 山西吕梁人, 博士, 副教授, 2004年、2007年于中国矿业大学分别获得学士、硕士学位, 2011年于上海交通大学获得博士学位, 主要从事新型减振降噪技术开发方面的研究。E-mail:liuhaiping@ustb.edu.cn" ]
- 基金信息：
  
  国家自然科学基金资助项目(51405014);国家留学基金委资助项目(201806465019)
- DOI：10.37188/OPE.20202807.1539
  中图分类号： O322;TH113.1;X966
- 收稿日期：2019-12-20，
  
  修回日期：2020-03-04，
  
  录用日期：2020-3-4，
  
  纸质出版日期：2020-07-15
- 稿件说明：
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刘国勇, 侯永涛, 刘海平, 等. 星载飞轮双状态隔离用变刚度摩擦阻尼器[J]. 光学精密工程, 2020,28(7):1539-1545.

Guo-yong LIU, Yong-tao HOU, Hai-ping LIU, et al. Variable stiffness friction damper for dual-state isolation of flywheel on satellite[J]. Optics and precision engineering, 2020, 28(7): 1539-1545.
刘国勇, 侯永涛, 刘海平, 等. 星载飞轮双状态隔离用变刚度摩擦阻尼器[J]. 光学精密工程, 2020,28(7):1539-1545. DOI： 10.37188/OPE.20202807.1539.

Guo-yong LIU, Yong-tao HOU, Hai-ping LIU, et al. Variable stiffness friction damper for dual-state isolation of flywheel on satellite[J]. Optics and precision engineering, 2020, 28(7): 1539-1545. DOI： 10.37188/OPE.20202807.1539.

摘要

为了有效抑制星载飞轮在轨姿态调整过程中输出的微振动，并改善发射过程中的动力学环境，提出一种变刚度摩擦阻尼器。根据星载飞轮在轨工作阶段和主动发射阶段的实际载荷条件，采用谐波平衡法得到频域力/绝对位移传递率曲线，并通过实验方法对所得传递率曲线进行了验证。实验结果表明：变刚度摩擦阻尼器在谐振频率处能够提供较大阻尼，将放大系数控制在较小范围内，实测结果和理论解吻合较好。研究结果表明：在轨工作阶段小载荷作用下，变刚度摩擦阻尼器能有效抑制飞轮输出微振动，在保证高频段隔振性能的同时，力传递率峰值约为6.5；在主动发射阶段大载荷作用下，绝对位移传递率峰值约为2.3。由此可见，变刚度摩擦阻尼器能同时兼顾飞轮在不同工作阶段载荷条件变化的影响，显著抑制其动态响应。

Abstract

In this study

a variable stiffness friction damper was proposed that effectively suppresses micro-vibration output during the orbit attitude adjustment of the spaceborne flywheel and improves dynamic environment during launch. Depending on the actual load conditions of the spaceborne flywheel in orbit and active launching phases

the harmonic balance method was used to obtain the frequency domain force/absolute displacement transmissibility curve. The transmissibility curve was verified via experimental methods. The experimental results show that the variable stiffness friction damper can provide greater damping at the resonance frequency and control the amplification factor to a smaller range. The measured results agree well with the theoretical solution. The research results show that under the effect of small load on-orbit phase

the variable stiffness friction damper can effectively suppress the micro-vibration of the flywheel output. On ensuring high frequency vibration isolation performance

the peak value of the force transmissibility is approximately 6.5. Under heavy load during the launching phase

the peak value of the absolute displacement transmissibility is approximately 2.3. Notably

the variable stiffness friction damper can simultaneously consider the influence of the change of the flywheel load conditions in different working phases

and significantly inhibit its dynamic response.

关键词

Keywords

references

魏展基.卫星飞轮微振动隔离方法与技术研究[D].长沙: 国防科学技术大学, 2012.

WEI ZH J. Research on the Microvibration Isolation Method and Technology for Flywheel of Satellite [D]. Changsha: National University of Defe nse Technology, 2012. (in Chinese)

徐鹏 , 黄长宁 , 王涌天 , 等 . 卫星振动对成像质量影响的仿真分析 . 宇航学报 , 2003 . 24 ( 3 ): 259 - 263 . DOI: 10.3321/j.issn:1000-1328.2003.03.008 http://doi.org/10.3321/j.issn:1000-1328.2003.03.008 .

P XU , CH N HUANG , Y T WANG , 等 . Simulation analysis of the influence of satellite vibration on image quality . Journal of Astronautics , 2003 . 24 ( 3 ): 259 - 263 . DOI: 10.3321/j.issn:1000-1328.2003.03.008 http://doi.org/10.3321/j.issn:1000-1328.2003.03.008 .

Q LUO , D LI , W ZHOU , 等 . Dynamic modelling and observation of micro-vibrations generated by a single gimbal control moment gyro . Journal of Sound and Vibration , 2013 . 332 ( 19 ): 4496 - 4516 . DOI: 10.1016/j.jsv.2013.03.034 http://doi.org/10.1016/j.jsv.2013.03.034 .

W ZHOU , D LI , Q LUO , 等 . Analysis and testing of micro-vibrations produced by momentum wheel assemblies . Chinese Journal of Aeronautics , 2012 . 25 ( 4 ): 640 - 649 . DOI: 10.1016/S1000-9361(11)60430-5 http://doi.org/10.1016/S1000-9361(11)60430-5 .

J FIRTH , J BLACK . Vibration interaction in a multiple flywheel system . Journal of Sound and Vibration , 2012 . 331 ( 7 ): 1701 - 1714 . DOI: 10.1016/j.jsv.2011.11.028 http://doi.org/10.1016/j.jsv.2011.11.028 .

S S NARAYAN , P S NAIR , A GHOSAL . Dynamic interaction of rotating momentum wheels with spacecraft elements . Journal of Sound and Vibration , 2008 . 315 ( 4-5 ): 970 - 984 . DOI: 10.1016/j.jsv.2008.02.020 http://doi.org/10.1016/j.jsv.2008.02.020 .

刘海平 , 王耀兵 , 史文华 . 非线性能量阱对飞轮扰振特性的抑制 . 宇航学报 , 2017 . 38 ( 5 ): 490 - 496 . http://d.old.wanfangdata.com.cn/Periodical/yhxb201705007 http://d.old.wanfangdata.com.cn/Periodical/yhxb201705007 .

H P LIU , Y B WANG , W H SHI . Vibration suppression for a flywheel based on nonlinear energy sink . Journal of Astronautics , 2017 . 38 ( 5 ): 490 - 496 . http://d.old.wanfangdata.com.cn/Periodical/yhxb201705007 http://d.old.wanfangdata.com.cn/Periodical/yhxb201705007 .

C YANG , D LI , L CHENG . Dynamic vibration absorbers for vibration control within a frequency band . Journal of Sound and Vibration , 2011 . 330 ( 8 ): 1582 - 1598 . DOI: 10.1016/j.jsv.2010.10.018 http://doi.org/10.1016/j.jsv.2010.10.018 .

虞自飞 , 周徐斌 , 申军烽 , 等 . 卫星飞轮隔振与吸振联合减振系统设计 . 光学精密工程 , 2014 . 22 ( 4 ): 897 - 903 . DOI: 10.3788/OPE.20142204.0897 http://doi.org/10.3788/OPE.20142204.0897 .

Z F YU , X B ZHOU , J F SHEN , 等 . Design of joint vibration reduction system combined isolation and absorbtion for flywheel . Opt. Precision Eng. , 2014 . 22 ( 4 ): 897 - 903 . DOI: 10.3788/OPE.20142204.0897 http://doi.org/10.3788/OPE.20142204.0897 .

OH C S, LEE W, BANG H. Passive jitter isolation for reaction wheel of satellites[C].2006 SICE-ICASE International Joint Conference. IEEE, 2006: 3891-3895.

PENDERGAST K J, SCHAUWECKER C J. Use of a passive reaction wheel jitter isolation system to meet the advanced X-ray astrophysics facility imaging performance requirements[C]. Space Telescopes and Instruments V. International Society for Optics and Photonics, 1998, 3356: 1078-1095.

刘兴天 , 孔祥森 , 申军烽 , 等 . 卫星遥感器微振动隔离用液体阻尼隔振器 . 光学精密工程 , 2017 . 25 ( 9 ): 2448 - 2453 . DOI: 10.3788/OPE.20172509.2448 http://doi.org/10.3788/OPE.20172509.2448 .

X T LIU , X S KONG , J F SHEN , 等 . Vibration isolator with relaxation type damping for micro-vibration isolation from satellite remote sensors . Opt. Precision Eng. , 2017 . 25 ( 9 ): 2448 - 2453 . DOI: 10.3788/OPE.20172509.2448 http://doi.org/10.3788/OPE.20172509.2448 .

李太平.航天器微振动及其抑制技术研究[D].哈尔滨: 哈尔滨工业大学, 2013.

LI T P. Research on Micro Vibration and Its Isolation of Spacecraft[D]. Harbin: Harbin Institute of Technology , 2013. (in Chinese)

王光远 , 关新 , 陈祥 , 等 . 双状态非线性隔振器参数设计与试验研究 . 宇航学报 , 2011 . 32 ( 1 ): 7 - 14 . DOI: 10.3873/j.issn.1000-1328.2011.01.002 http://doi.org/10.3873/j.issn.1000-1328.2011.01.002 .

G Y WANG , X GUAN , X CHEN , 等 . Parameter design and experimental study of a two state nonlinear isolator . Journal of Astronautics , 2011 . 32 ( 1 ): 7 - 14 . DOI: 10.3873/j.issn.1000-1328.2011.01.002 http://doi.org/10.3873/j.issn.1000-1328.2011.01.002 .

彭凌云.向心式摩擦阻尼器的理论分析与应用研究[D].北京: 北京工业大学, 2004.

PENG L Y. Theoretical Analysis and Application Research on Energy Dissipating Restraint [D]. Beijing: Beijing University of Technology, 2004. (in Chinese)

李澈.摩擦阻尼器的研制与应用[D].北京: 中国建筑科学研究院, 2011.

LI CH. Friction Damper Development and Application [D]. Beijing: China Academy of Building Research, 2011. (in Chinese).

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