ls98wave 发表于 2005-12-2 21:15

[求助]星箭隔振振动主动控制

不知各位是否有相关资料,可以分享一下<br><br>小弟最近需要做相关的论文,可是具体知识了解的不是很多<br><br>大家多帮忙了!谢谢了<br><br>如果可以发到我的邮箱更是不胜感激
[此贴子已经被cdwxg于2006-5-28 0:52:47编辑过]

simon21 发表于 2005-12-5 14:34

回复:(ls98wave)求助:星箭隔振振动主动控制

整星隔振技术的研究现状和发展
<br>Review of the Whole-spacecraft Isolation Techniques
<p>张军  谌勇  骆剑  华宏星 
<p>摘 要:为了减小卫星发射时所承受的环境载荷,降低卫星及其设备的质量控制成本,提高卫星发射的可靠性,所以整星隔振技术得以研究和应用.整星隔振是在不改变卫星原结构前提下,重新设计具有隔振效能的适配器,或者在运载火箭和卫星之间引入隔振装置,隔离从星箭界面传递给卫星的轴向或侧向振动.详细介绍了近十年国外整星隔振技术的研究现状,并展望其今后的发展方向.<BR>关键词:卫星; 整星隔振; 适配器; 隔振器; 轴向/侧向隔振<BR>分类号:V414  文献标识码:A<BR>文章编号:1000-6893(2005)02-0179-05
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<p>作者简介:张军(1976-) 男,重庆北碚人,上海交通大学振动、冲击和噪声国家重点实验室在读博士研究生,研究方向:振动控制和结构设计,Email:zj_zmkm@sjtu.edu.cn,电话:021-54744481-107. <BR>作者简介:谌勇(1977-) 男,重庆巫溪人,上海交通大学振动、冲击和噪声国家重点实验室在读博士研究生,从事结构振动及模态分析理论的研究. <BR>作者简介:华宏星(1955-) 男,上海人,上海交通大学振动、冲击噪声国家重点实验室教授,博士生导师,中国振动工程学会模态分析专业委员会主任,上海市振动工程学会常务理事. <BR>作者单位:张军(上海交通大学,振动、冲击和噪声国家重点实验室,上海,200240) <BR>     谌勇(上海交通大学,振动、冲击和噪声国家重点实验室,上海,200240) <BR>     骆剑(航天部第八研究院,805所,上海,200240) <BR>     华宏星(上海交通大学,振动、冲击和噪声国家重点实验室,上海,200240) <BR>
<P>参考文献:</P>Wilke P S, Alto P, Johnson C D,et al. Payload isolation system for launch vehicles.SPIE Proceedings.1997,3045:20-30.<BR>Bicos A S, Johnson C D. Need for and benefits of launch vibration isolation . SPIE Proceedings. 1997. 3045: 14-19.<BR>Fosness E R,Denoyer K K,Das A, et al. Whole-spacecraft isolation development effects at the USAF Phillips laboratory. 11th AIAA/USU Conference on Small Satellites. 1997.<BR>Toren D, Osterberg S, David A. Load vibration isolation apparatus .United States Patent: 5947240, 1999.<BR>Johnson C D. On the design and testing of a spacecraft launch vibration isolation system (LVIS) .Proceedings of the 38th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference.1997.<BR>Edberg D L, Bartos B, Goodding J, et al. Passive and active launch vibration studies in the LVIS program .SPIE Proceedings. 1998. 3327: 411-422.<BR>Edberg D L,Johnson C D,Davis L P,et al.Development of a launch vibration isolation system.SPIE Procceedings.1998.3045:31-37<BR>Osterberg S,David A.Load isolator apparatus . United States Patent: 5918865, 1999.<BR>Toren D, Osterberg S.David A. Heavy load vibration isolation apparatus . United States Patent: 5803213, 1998.<BR>Hubert,Dominique P M. Device for suspension of a payload in a space launch .United States Patent: 6244541, 1999.<BR>Ruebsamen D T, Evolved launch vibration evolved launch vibration isolation system (ELVIS) demonstration unit test results . The S/C and L/V Dynamics Environments Workshop, the Aerospace Corporation, June, 2003.<BR>Johnson C D, Wilke P S, Grosserode P J.Whole-spacecraft vibration isolation system for the GFO/Taurus mission.SPIE Proceedings.1999.3672:175-185.<BR>Wilke P S,Johnson C D,Grosserode P J,et al.Whole-spacecraft vibration isolation for broadband attenuation.IEEE Aerospace Conference.2000.4117:315-321.<BR>Johnson C D, Wilke P S,Grosserode P J.GFO/Taurus whole-spacecraft vibration isolation system.12th Annual AIAA/USU Conference on Small Satellites.September Logan Utah. 1998.<BR>Johnson C D,Wilke P S,Scottccc,et al. Three-axis, six degree-of-freedom, whole-spacecraft passive vibration isolation system .United States Patent:6290183,2001.<BR>Sciulli D,Denoyer K K,Fosness E R.Program development of whole-spacecraft launch isolation systems at the U.S.Air force research laboratory.50th International Astronautical Congress.Amsterdam,the Netherlands.1999:1-6.<BR>Wilke P S, Johnson C D,Fosness E R.Whole-spacecraft passive launch isolation.Journal of Spacecraft and Rockets,1998,35(5):690-694.<BR>Wilke P S, Johnson C D, Darling K R. Whole-spacecraft vibration isolation flown on the Minotaur launch vehicle . 15th Annual/USU Conference on Small Satellites . Logan,Utah.2001.<BR>Johnson C D, Wilke P S, Darling K R.Multi-axis whole-spacecraft vibration isolation for small launch vehicles.SPIE Proceedings.2001,4331:162-174.<BR>Denoyer K K, Johnson C D. Recent achievements in vibration isolation systems for space launch and on-orbit applications.52nd International Astronautical Congress Toulouse. 2001.4-11.<BR>Edberg D L,Fukushima,Jeffrey D,et al.Passive lateral vibration isolation system for a spacecraft launch vehicle.United States Patent:6012680,2001.<BR>Malya J R,Haskett S A,Wilke P S,et al.EELV secondary payload adapter with whole-spacecraft isolation for primary and secondary payloads.SPIE Proceedings.2000.3989:430-439.<BR>Scott C, Haskett S A.Doggrel,et al.EELV secondary payload adapter(ESPA).SPIE Proceedings.2000,4136:27-35.<BR>Jeremy S,Wegner G P.Evolved expendable launch vehicle secondary payload adapter.15th Annual/USU Conference on Small Satellites.August,Logan,Utah.2001.<BR>Sciulli D, Griffin,Steven F.Whole-spacecraft hybrid isolation system for launch vehicles .United States Patent: 6135390, 2000.<BR>Khorrami F, Rastegar J, Erwin R S. A three degrees-of-freedom adaptive-passive isolator for launch vehicle payloads .SPIE Proceedings. 2000.164-176.<BR>Karahalis G G.Whole spacecraft vibration isolation master's thesis.USA:OH. School of Engineering, 1999.<BR>Karahalis G G, Agnes G S. Preliminary analysis of hybrid launch isolation for spacecraft .SPIE Proceedings.1999.3674:360-370.<BR>Sciulli D, Griffin S F . Hybrids launch isolation system .SPIE Proceedings.1999.3674 : 352-359.<BR>Jarosh J R.Active and adaptive control for payload launch vibration isolation master's thesis.USA:OH. School of Engineering, 2000.<BR>Jarosh J R,Agnes G S, Karahalis G G.Adaptive control for payload launch vibration isolation.SPIE Proceedings.2001.4331: 162-174.<BR>Flint E.Active/passive counter-force vibration control and isolation systems.IEEE Aerospace Conference Proceedings.2000,4:285-298.<BR>Flint E, Anderson E.Multi-degree of freedom parallel actuation system architectures for motion control . AIAA 2001-4750.
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