并联式承载减振一体的整星隔振研究

潘忠文; 邢建伟; 王檑; 陈珅艳

doi:10.6052/0459-1879-18-285

并联式承载减振一体的整星隔振研究

* 北京宇航系统工程研究所,北京 100076
?? 北京航空航天大学宇航学院,北京 100191

基金项目: 国家自然科学基金资助项目(11672016)

详细信息

作者简介:
2) 潘忠文,研究员,主要研究方向：载荷与力学环境.E-mail： zhwpan@sina.com

中图分类号: TB535 ⁺.1
计量
- 文章访问数: 2169
- HTML全文浏览量: 472
- PDF下载量: 186
出版历程
- 收稿日期: 2018-08-30
- 刊出日期: 2019-03-17

RESEARCH ON WHOLE-SPACECRAFT VIBRATION ISOLATION BASED ON PARALLEL LOAD-BEARING AND DAMPING SYSTEM

* Beijing Institute of Space System Engineering, Beijing 100076, China
?? School of Astronautics, Beihang University, Beijing 100191, China

摘要

摘要: 整星隔振是一种改善卫星振动环境的有效措施,传统整星隔振方案主要通过在卫星与火箭之间插入柔性、高阻尼结构.该方案因串联柔性元件,在实现减振的同时,也导致卫星分支(卫星、卫星支架、过渡支架)及整个运载火箭的模态频率大幅降低和卫星振动位移的显著增大.前者严重影响运载火箭飞行特别是末级飞行的稳定性;后者则会大幅减小卫星与整流罩的动态间隙,严重时可能导致卫星与整流罩碰撞.为了解决串联式整星隔振存在的问题,本文提出了一种在原主承力(过渡支架)结构中并联阻尼元件的整星隔振方案,该方案不改变卫星分支结构形式、连接关系,不影响卫星分支主承力结构的强度和刚度.根据柔性航天器的特点,建立了多自由度系统动力学模型,通过仿真分析研究了不同阻尼特性对系统共振频率附近传递特性的影响,得到了增大阻尼可有效改善系统各阶共振频率附近的振动传递特性.根据某运载火箭的外激励特点、过渡支架结构形式、卫星减振需求,设计的一种黏性阻尼器及其安装支架,通过在过渡支架均匀分布8个减振单元,构建了并联式承载减振一体的整星隔振方案,有限元分析和试验结果表明,该方案与无减振状态相比,卫星分支频率变化小于±5％,共振频率处传递特性改善30％~40％.
- 并联式 /
- 减振 /
- 整星 /
- 黏滞阻尼器
Abstract: Whole-satellite vibration isolation is an effective measure to improve the satellite vibration environment. Traditional Whole-Satellite vibration isolation schemes mainly insert flexible and high-damping structures between satellite and rocket. Due to the series of flexible components, the scheme achieves vibration reduction, and also causes a significant decrease in the modal frequencies of satellite branches (satellite, satellite brackets, transition brackets) and the entire launch vehicle with a remarkably increase in satellite vibration displacement. The former seriously affects the flight stability of launch vehicle, especially the stability of final stage, while the latter greatly reduces the dynamic clearance between satellite and fairing, which may lead to collision between satellite and fairing in severe cases. In order to solve the problem of series whole-satellite vibration isolation, this paper presents a whole-satellite vibration isolation scheme with parallel dampers in the original main bearing structure (transition support). This scheme does not change the form and connection relationship of satellite branch structure, and does not affect the strength and stiffness of satellite branch main bearing structure. According to the characteristics of flexible spacecraft, a multi-degree-of-freedom system dynamics model is established. The effects of different damping characteristics on the transmission characteristics near the resonance frequencies of the system are analyzed by simulation. It is concluded that increasing damping can effectively improve the vibration transmission characteristics near the resonance frequencies of the system. A viscous damper and its mounting bracket are designed according to the external excitation characteristics of a launch vehicle, the structural form of transition support and vibration reduction requirement of satellite. By evenly distributing eight vibration reduction units in the transition support, a whole satellite vibration isolation scheme with Parallel bearing and vibration reduction is constructed. Finite element analysis and experimental results show that the variation of satellite branch frequencies is less than 5％ and the transmission characteristics at resonance frequencies are improved by 30％~40％ compared with the non-vibration state.
- parallel mode /
- vibration attenuation /
- whole-satellite /
- viscous damper

HTML全文

参考文献(1)

[1]	马兴瑞, 韩增尧, 邹元杰等. 航天器力学环境分析与试验条件设计进展. 宇航学报, 2012,33(1):1-12
[1]	( Ma Xingrui, Han Zengyao, Zou Yuanjie , et al. Review and assessment of spacecraft mechanical environment analysis and specification determination. Journal of Astronautics, 2012,33(1):1-12 (in Chinese))
[2]	马兴瑞, 韩增尧 . 卫星与运载火箭力学环境分析方法及试验技术.北京: 科学出版社, 2014: 7-9
[2]	( Ma Xingrui, Han Zengyao. Mechanical Environment Analysis Method and Test Technology of Satellite and Launch Vehicle. Beijing: Science Press, 2014: 7-9(in Chinese))
[3]	王小军, 于子文, 张兵等. 国内外运载火箭POGO抑制技术研究进展. 中国科学:技术科学, 2014,44(5):492-503
[3]	( Wang Xiaojun, Yu Ziwen, Zhang Bing , et al. Research progress of POGO suppression technology for launch vehicles at home and abroad. Science China, 2014,44(5):492-503(in Chinese))
[4]	王庆伟, 谭述君, 吴志刚等. 大型液体火箭姿控与跷振大回路耦合动力学建模与分析. 力学学报, 2015,47(5):789-798
[4]	( Wang Qingwei, Tan Shujun, Wu Zhigang , et al. Dynamic modeling and analysis of large-loop coupled by attitudecontroland pogo for large liquid rockets. Chinese Journal of Theoretica and Applied Mechanics, 2015,47(5):789-798 (in Chinese))
[5]	曹登庆, 白坤朝, 丁虎等. 大型柔性航天器动力学与振动控制研究进展. 力学学报, 2018,48(6):1019-1032
[5]	( Cao Dengqing, Bai Kunchao, Deng Hu , et al. Advances in dynamics and vibration Control of large-scale flexible spacecraft. Chinese Journal of Theoretica and Applied Mechanics, 2018,48(6):1019-1032 (in Chinese))
[6]	黄文虎, 曹登庆, 韩增尧 . 航天器动力学与控制的研究进展与展望. 力学进展, 2012,42(4):367-394
[6]	( Huang Wenhu, Cao Dengqing, Han Zengrao . Advances and trends in dynamics and control spacscraft. Advances in Mechanics, 2012,42(4):367-394 (in Chinese))
[7]	张军, 谌勇, 骆剑等. 整星隔振技术的研究现状与发展. 航空学报, 2006,26(2):179-183
[7]	( Zhang Jun, Chen Yong, Luo Jian , et al. Review of the whole-spacecraft isolation techniques. Acta Aeronauticaet Astronautica Sinica, 2006,26(2):179-183 (in Chinese))
[8]	Johnson CD, Wilke P . Protecting satellite from the dynamics of the launch environment. CSA Papers, 2003: 1-14
[9]	Denoyer KK, Johnson CD . Recent achievements in vibration isolation systems for space launch and on-orbit application//52nd International Astronautical Congress, Toulouse, France, 2001, IAF-01-I.2.01
[10]	Johson CD, Wilke PS, Darling KR . Multi-axis whole-spacecraft vibration isolation for small launch vehicles//SPIE Conference on Smart Structures and Materials, Newport Beach, 2001,4331:153-161
[11]	Chen Y, Fang B, Yang TZ , et al. Study of whole-spacecraft vibration isolators based on reliability method. Chinese Journal of Aeronautics, 2009,22(2):153-159
[12]	陈阳, 方勃, 曲秀全 . 新型整星隔振器隔振性能分析. 宇航学报, 2007,28(4):986-990
[12]	( Chen Yang, Fang Bo, Qu Xiuquan . Performance analysis of the new whole-spacecraft isolation. Journal of Astronautics, 2007,28(4):986-990 (in Chinese))
[13]	周杰, 方勃, 王日新 . 正交各向异性层合圆板的非轴对称弯曲. 宇航学报, 2007,28(4):819-823, 864
[13]	( Zhou Jie, Fang Bo, Wang Rixin . Nonaxisymmetrical bending of orthotropic laminated circular plate. Journal of Astronautics, 2007,28(4):819-823, 864 (in Chinese))
[14]	Liu LK, Zheng GT, Huang WH . Octo-strut vibration isolation platform and its application to whole spacecraft vibration isolation. Journal of Sound and Vibration, 2006,289(4-5):726-744
[15]	刘丽坤, 郑钢铁, 黄文虎 . 整星被动多杆隔振平台研究. 应用力学学报, 2005,22(3):329-335
[15]	( Liu Likun, Zheng Gangtie, Huang Wenhu . Multi-strut platform for passive whole-spacecraft vibration isolation. Chinese Journal of Applied Mechanics, 2005,22(3):329-335(in Chinese))
[16]	Liu LK, Zheng GT, Huang WH . Study of liquid viscosity dampers in octo-strut platform for whole-spacecraft vibration isolation. Acta Astronautica, 2006,58(10):515-522
[17]	Liu LK, Liang L, Zheng GT , et al. Dynamic design of octostrut platform for launch stage whole-spacecraft vibration isolation. Journal of Spacecraft and Rockets, 2005,42(4):654-662
[18]	Wang XL, Yang QJ, Zheng GT . Dynamic analysis and decoupling control of octo-pneumatic actuator vibration isolation platform. Chinese Journal of Mechanical Engineering, 2009,22(1):116-123
[19]	王晓雷, 杨庆俊, 郑钢铁 . 整星主动隔振平台研究. 宇航学报, 2007,28(2):438-441
[19]	( Wang Xiaolei, Yang Qingjun, Zheng Gangtie . Study of whole-statellite active vibration isolation platform. Journal of Astronautics, 2007,28(2):438-441(in Chinese))
[20]	Ruebsamen DT , Evolved launch vibration evolved launch vibration isolation system (ELVIS) demonstration unittest results. The S/C and L/V Dynamics Environments Workshop, the Aerospace Corporation, June, 2003
[21]	涂奉臣 . 基于磁流变阻尼器的整星半主动隔振技术研究.[博士论文]. 哈尔滨: 哈尔滨工业大学, 2010
[21]	( Tu Fengchen . Semi-active whole-spacecraft cibration isolation technology using magnetorheological damper. [PhD Thesis]. Harbin: Harbin Institute of Technology, 2010 (in Chinese))
[22]	黄曦, 余淼 . 磁流变液阻尼器动态响应及其影响因素分析. 功能材料, 2006,37(5):808-813
[22]	( Huang Xi, Yu Miao . Analysis of dynamic response time of MR damper and its influential factors. Functional Materials, 2006,37(5):808-813 (in Chinese))
[23]	杨建伟 . 汽车半主动磁流变悬架的自适应双模糊控制方法. 振动与冲击, 2010,29(4):46-51
[23]	( Yang Jianwei . Adaptive dual fuzzy control method for automotive semi-active suspension with magnetorheological damper. Journal of Vibration and Shock, 2010,29(4):46-51(in Chinese))
[24]	Dong XM . Human simulated intelligent control and its application in magneto-rheological suspension. Control Theory & Applications, 2010,27(2):249-256
[25]	Cheok KAC, Hu HX, Loh NK . Discrete-time frequency-shaping parameteric LQ control with application to active seat suspension control. IEEE Transactions on Industrial Electronics, 1998,36(3):383-390
[26]	王檑, 潘忠文, 廉永正等. 磁流变Stewart隔振平台$H\infty$半主动控制研究. 宇航总体技术, 2018,2(1):41-48
[26]	( Wang Lei, Pan Zhongwen, Lian Yongzheng , et al. Research on H$\infty$ semi-active control of magnetorheological stewart vibration isolaton platform. Astronautical Systems Engineering Technology, 2018,2(1):41-48 (in Chinese))
[27]	Du HJ, Zou ZZ, Huang WH . Vibration suppression analysis for supporter with constrained layer damping. Journal of Harbin Institute of Technology, 2004(2):231-236
[28]	杜华军, 于百胜, 郑钢铁等. 蜂窝锥壳卫星适配器约束阻尼层振动抑制分析. 应用力学学报, 2003,20(3):5-9
[28]	( Du Huajun, Yu Baisheng, Zheng Gangtie , et al. Vibration suppression of a conical honeycomb satellite adapter subjected to constrained layer damping. Chinese Journal of Applied Mechanics, 2003,20(3):5-9 (in Chinese))
[29]	杜华军, 陈恩鹏 . 航天结构的约束阻尼振动抑制优选方案研究. 航天控制, 2004,22(5):8-11
[29]	( Du Huajun, Chen Enpeng . An optimized scheme for aerospace structure vibration suppression with constrained layer damping. Aerospace Control, 2004,22(5):8-11(in Chinese))
[30]	徐卫秀, 王江, 邵英翠等. 卫星支架附加约束阻尼减振设计与分析. 导弹与航天运载技术, 2015,5:91-95
[30]	( Xu Weixun, Wang Jiang, Shao Yingcui , et al. Vibration damping design and analysis of additional constrained damping layer for satellite adapter. Missilesand Space Vehicles, 2015,5:91-95 (in Chinese))
[31]	梁鲁, 刘明辉, 张静等. 附加约束阻尼层对星箭系统动特性的影响分析. 应用力学学报, 2007,24(4):669-673
[31]	( Liang Lu, Liu Minghui, Zhang Jing , et al. Transverse dynamic characteristic of spacecraft vibration isolation platform. Chinese Journal of Applied Mechanics, 2007,24(4):669-673(in Chinese))
[32]	王聪, 牟全臣, 姜兴谓等. 一类约束阻尼结构动力学建模及其应用.强度与环境, 2001(1):20-25
[32]	( Wang Cong, Mou Quanchen, Jiang Xingwei , et al. Modeling and application for a kind of constrained damping structure. Structure & Environment Engineering, 2001(1):20-25(in Chinese))
[33]	张家雄, 张华山, 曹晓瑞等. 航天器仪器安装板附加约束阻尼层设计与振动抑制验证. 航天器环境工程, 2016,33(5):540-544
[33]	( Zhang Jiaxiong, Zhang Huashan, Cao Xiaorui , et al. Constrained damping layer design and vibration suppression verification for vehicle instrument installation board. Spacecraft Environment Engineering, 2016,33(5):540-544 (in Chinese))
[34]	邢誉峰, 李敏 . 工程振动基础(第2版). 北京: 北京航空航天大学出版社, 2011: 43-45
[34]	( Xing Yufeng, Li Min . Engineering Vibration Foundation (2nd Edition). Beijing: Beihang University Press, 2011: 43-45(in Chinese))

施引文献(19)

期刊类型引用(10)

1.	王辰，王文熙，陈政清，张宏剑，吴会强. 重复使用运载火箭机构电涡流阻尼技术应用及思考. 宇航材料工艺. 2024(02): 43-53 . 百度学术
2.	王正东，卡主草，胡林欢，燕群，延浩，高洁，田野，李勇. 基于声阻抗匹配理论的弹性吸收体研究. 航空工程进展. 2024(05): 79-85 . 百度学术
3.	东巳宙，白照广，白云鹤，杨新峰，单悌磊，王玉帅，常静. 卫星对接环减振装置设计与验证. 宇航学报. 2023(01): 143-154 . 百度学术
4.	匡格平，胡兆财，谢金鑫，姜广利，彭飞. 飞行器蒙皮桁条结构减振优化设计方法研究. 强度与环境. 2023(03): 45-52 . 百度学术
5.	李佳霖，赵剑，孙直，郭杏林，郭旭. 基于移动可变形组件法(MMC)的运载火箭传力机架结构的轻量化设计. 力学学报. 2022(01): 244-251 . 本站查看
6.	范大蔚，佟佳慧. 一种基于环境预报数据的阵风建模方法. 系统仿真学报. 2020(12): 2409-2414 . 百度学术
7.	李加瑞，于子平，郭江川，韩星凯，张昭. 火箭被动减振结构——C型弹簧的设计. 弹箭与制导学报. 2020(06): 26-29 . 百度学术
8.	肖春生，范大蔚，林建军. 大气紊流对飞行器飞行和命中率影响研究. 战术导弹技术. 2020(06): 127-131 . 百度学术
14.	骆海涛，王浩楠，于长帅，刘广明. 某无人机激光雷达隔振设计与试验测试. 振动.测试与诊断. 2021(06): 1143-1147+1238-1239 . 百度学术
18.	陈春，高雪，滕汉东. 气动准零非线性隔振器的刚度特性与参数调控. 振动.测试与诊断. 2020(03): 513-518+626 . 百度学术