[求助]星箭隔振振动主动控制

ls98wave

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

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
<p>
<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>[1]Wilke P S, Alto P, Johnson C D,et al. Payload isolation system for launch vehicles[A].SPIE Proceedings[C].1997,3045:20-30.<BR>[2]Bicos A S, Johnson C D. Need for and benefits of launch vibration isolation [A]. SPIE Proceedings[C]. 1997. 3045: 14-19.<BR>[3]Fosness E R,Denoyer K K,Das A, et al. Whole-spacecraft isolation development effects at the USAF Phillips laboratory[A]. 11th AIAA/USU Conference on Small Satellites[C]. 1997.<BR>[4]Toren D, Osterberg S, David A. Load vibration isolation apparatus [P].United States Patent: 5947240, 1999.<BR>[5]Johnson C D. On the design and testing of a spacecraft launch vibration isolation system (LVIS) [A].Proceedings of the 38th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference[C].1997.<BR>[6]Edberg D L, Bartos B, Goodding J, et al. Passive and active launch vibration studies in the LVIS program [A].SPIE Proceedings[C]. 1998. 3327: 411-422.<BR>[7]Edberg D L,Johnson C D,Davis L P,et al.Development of a launch vibration isolation system[A].SPIE Procceedings[C].1998.3045:31-37<BR>[8]Osterberg S,David A.Load isolator apparatus [P]. United States Patent: 5918865, 1999.<BR>[9]Toren D, Osterberg S.David A. Heavy load vibration isolation apparatus [P]. United States Patent: 5803213, 1998.<BR>[10]Hubert,Dominique P M. Device for suspension of a payload in a space launch [P].United States Patent: 6244541, 1999.<BR>[11]Ruebsamen D T, Evolved launch vibration evolved launch vibration isolation system (ELVIS) demonstration unit test results [R]. The S/C and L/V Dynamics Environments Workshop, the Aerospace Corporation, June, 2003.<BR>[12]Johnson C D, Wilke P S, Grosserode P J.Whole-spacecraft vibration isolation system for the GFO/Taurus mission[A].SPIE Proceedings[C].1999.3672:175-185.<BR>[13]Wilke P S,Johnson C D,Grosserode P J,et al.Whole-spacecraft vibration isolation for broadband attenuation[A].IEEE Aerospace Conference[C].2000.4117:315-321.<BR>[14]Johnson C D, Wilke P S,Grosserode P J.GFO/Taurus whole-spacecraft vibration isolation system[A].12th Annual AIAA/USU Conference on Small Satellites[C].September Logan Utah. 1998.<BR>[15]Johnson C D,Wilke P S,Scottccc,et al. Three-axis, six degree-of-freedom, whole-spacecraft passive vibration isolation system [P].United States Patent:6290183,2001.<BR>[16]Sciulli D,Denoyer K K,Fosness E R.Program development of whole-spacecraft launch isolation systems at the U.S.Air force research laboratory[A].50th International Astronautical Congress[C].Amsterdam,the Netherlands.1999:1-6.<BR>[17]Wilke P S, Johnson C D,Fosness E R.Whole-spacecraft passive launch isolation[J].Journal of Spacecraft and Rockets,1998,35(5):690-694.<BR>[18]Wilke P S, Johnson C D, Darling K R. Whole-spacecraft vibration isolation flown on the Minotaur launch vehicle [A]. 15th Annual/USU Conference on Small Satellites [C]. Logan,Utah.2001.<BR>[19]Johnson C D, Wilke P S, Darling K R.Multi-axis whole-spacecraft vibration isolation for small launch vehicles[A].SPIE Proceedings[C].2001,4331:162-174.<BR>[20]Denoyer K K, Johnson C D. Recent achievements in vibration isolation systems for space launch and on-orbit applications[A].52nd International Astronautical Congress Toulouse[C]. 2001.4-11.<BR>[21]Edberg D L,Fukushima,Jeffrey D,et al.Passive lateral vibration isolation system for a spacecraft launch vehicle[P].United States Patent:6012680,2001.<BR>[22]Malya J R,Haskett S A,Wilke P S,et al.EELV secondary payload adapter with whole-spacecraft isolation for primary and secondary payloads[A].SPIE Proceedings[C].2000.3989:430-439.<BR>[23]Scott C, Haskett S A.Doggrel,et al.EELV secondary payload adapter(ESPA)[J].SPIE Proceedings[C].2000,4136:27-35.<BR>[24]Jeremy S,Wegner G P.Evolved expendable launch vehicle secondary payload adapter[A].15th Annual/USU Conference on Small Satellites[C].August,Logan,Utah.2001.<BR>[25]Sciulli D, Griffin,Steven F.Whole-spacecraft hybrid isolation system for launch vehicles [P].United States Patent: 6135390, 2000.<BR>[26]Khorrami F, Rastegar J, Erwin R S. A three degrees-of-freedom adaptive-passive isolator for launch vehicle payloads [A].SPIE Proceedings[C]. 2000.164-176.<BR>[27]Karahalis G G.Whole spacecraft vibration isolation master's thesis[D].USA:OH. School of Engineering, 1999.<BR>[28]Karahalis G G, Agnes G S. Preliminary analysis of hybrid launch isolation for spacecraft [A].SPIE Proceedings[C].1999.3674:360-370.<BR>[29]Sciulli D, Griffin S F . Hybrids launch isolation system [A].SPIE Proceedings[C].1999.3674 : 352-359.<BR>[30]Jarosh J R.Active and adaptive control for payload launch vibration isolation master's thesis[D].USA:OH. School of Engineering, 2000.<BR>[31]Jarosh J R,Agnes G S, Karahalis G G.Adaptive control for payload launch vibration isolation[A].SPIE Proceedings[C].2001.4331: 162-174.<BR>[32]Flint E.Active/passive counter-force vibration control and isolation systems[A].IEEE Aerospace Conference Proceedings[C].2000,4:285-298.<BR>[33]Flint E, Anderson E.Multi-degree of freedom parallel actuation system architectures for motion control [R]. AIAA 2001-4750.
<p>