柔性接头迟滞阻尼特性识别

郑开发; 王超; 郝文强; 任军学; 刘宇; 杨敬贤

doi:10.13224/j.cnki.jasp.2017.02.029

柔性接头迟滞阻尼特性识别

doi: 10.13224/j.cnki.jasp.2017.02.029

1.
北京航空航天大学宇航学院,北京 100191
2.
中国航天科工集团公司北京机械设备研究所,北京,1000851
3.
中国航天科技集团公司上海新力动力设备研究所,上海 200125

基金项目: 上海航天科技创新基金(SAST201258)

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出版历程
- 收稿日期: 2015-05-21
- 刊出日期: 2017-02-28

Identification of flexible joint hysteresis damping characteristics

摘要

摘要: 为实现对柔性接头系统的建模和动力学分析,对柔性接头的迟滞阻尼特性识别方法进行了研究.测试了一系列不同摆角和不同频率条件下柔性接头的动态特性参数,基于变刚度变阻尼法对不同频率下的刚度系数和阻尼系数进行了参数识别,获得了刚度系数和阻尼系数跟摆动频率之间的关系,建立了柔性接头动力学模型.应用该模型分析计算了柔性接头低速频率特性,并与试验结果进行了对比分析.结果表明：建立的模型可以很好地描述柔性接头的低频特性,随摆动频率的增加,恢复力矩略有增加；在振幅较小时,弹性力矩随摆角呈线性,随着摆动振幅的增加,弹性力矩的非线性逐渐增强.
- 柔性接头 /
- 迟滞阻尼 /
- 参数识别 /
- 动力学建模 /
- 动态特性
Abstract: In order to model and analyze the dynamics of flexible joint, the method of identifying flexible joint hysteresis damping characteristics was studied. The dynamic characteristics of flexible joint at different amplitudes and frequencies were tested. The elastic force and damping force at different frequency parameters were identified based on the method of variable stiffness and damping. Therefore the relationships between the frequency and stiffness coefficient and damping coefficient were discovered, and a nonlinear dynamic model of flexible joint was established. The calculated dynamic properties of the amplitude dependence for the joint with the proposed model were compared with experiment. Result shows that a good agreement is obtained and the torque increase a little with the increase of the frequency. Elastic moment is linear with the pendulum angle in the small amplitude, and it gradually becomes nonlinear with the increase of the amplitude.
- flexible joint /
- hysteretic damping /
- parameter identification /
- dynamic modeling /
- dynamic characteristics

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参考文献(15)

[1]	Shimon S,Shlomo P,Arie P,et al.Development of a highperformance flexible joint for thrust vector control［R］.AIAA 95-3017,1995.
[2]	林培基,高峰.推力矢量对防空导弹作战效能的影响［J］.飞航导弹,2009(1):56-57,64. LIN Peiji,GAO Feng,Effect of thrust vector on operational efficiency of air defense missile［J］.Aerodynamic Missile Journal,2009(1):56-57,64.(in Chinese)
[3]	吉礼超,宋贵宝.防空导弹控制方法的研究现状及展望［J］.战术导弹技术,2009(3):54-59. JI Lichao,SONG Guibao.Current study status and future prospect of control mode of a irdefense missile［J］.Tactical Missile Technology,2009(3):54-59.(in Chinese)
[4]	Wassom S R,Faupell L C,Perley T,et al.Integrated aerofin/thrust vector control for tactical missiles［J］.Journal of Propulsion and Power,1991,7(3):374-381.
[5]	Caveny L H,Geisler R L,Ellis R A,et al.Solid rocket enabling technologies and milestones in the United States［J］.Journal of Propulsion and Power,2003,19(6):1038-1066.
[6]	Olsen K E,Walsh J J,Thomas E L.Navy terrier LEAP thirdstage propulsion［R］.Monterey,CA:AIAA Missile Sciences Conference,1994.
[7]	Uhrig G,Roussille C.Design drivers and technologies for solid propulsion of interceptors［R］.Arcachon,France:The 1st Association Aeronautique et Astronautique de France International Conference on Missile Defense,2003.
[8]	陈乃立,童忠钫.非线性迟滞系统的参数分离识别［J］.振动与冲击,1994,52(4):7-14. CHEN Naili,TONG Zhongfang.Separably indentifying the parameters of nonlinear hysteretic system［J］.Journal of Vibration and Shock,1994,52(4):7-14.(in Chinese)
[9]	龚宪生,唐一科.一类迟滞非线性振动系统建模新方法［J］.机械工程学报,1999,35(4):11-14. GONG Xiansheng,TANG Yike.New method for modeling of a norlinear vibration system with hysteresis characteristics［J］.Chinese Journal of Mechanical Engineering,1999,35(4):11-14.(in Chinese)
[10]	赵荣国,徐有钜,陈忠富,等.一个新的非线性迟滞隔振系统动力学模型［J］.机械工程学报,2004,40(2):185-188. ZHAO Rongguo,XU Youju,CHEN Zhongfu,et al.New dynamic model for nonlinear hysteresis vibration isolation system［J］.China Academy of Engineering,2004,40(2):185-188.(in Chinese)
[11]	GiNegrete N,Vinolas J,Kari L,et al.A simplified methodology to predict the dynamic stiffness of carbonblack filled rubber isolators using a finite element code［J］.Journal of Sound and Vibration,2006,296:757-776.
[12]	Mordini A,Strauss A.An innovative earthquake isolation system using fiber reinforced rubber bearings［J］.Engineering Structures,2008,30（2）:2739-2751.
[13]	张晓光,刘宇,任军学,等.小型柔性接头推力矢量性能试验研究［J］.航空动力学报,2012,27(12):2836-2841. ZHANG Xiaoguang,LIU Yu,REN Junxue,et al,Experimental investigation of miniature flexible joint thrust vector characteristics［J］.Journal of Aerospace Power,2012,27(12):2836-2841.(in Chinese)
[14]	王超,任军学,郝文强,等.柔性接头有效摆心漂移特性［J］.航空动力学报,2014,29（12）：2993-2999. WANG Chao,REN Junxue,HAO Wenqiang,et al.Characteristics of effective pivot point excursion for flexible joint［J］.Journal of Aerospace Power,2014,29（12）：2993-2999.(in Chinese)
[15]	陈汝训.固体火箭发动机设计［M］.北京：中国宇航出版社,2005.