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星箭适配器(PAF)隔振技术的进展

王跃宇, 冷力强, 李 志, 李 勇

王跃宇, 冷力强, 李 志, 李 勇. 星箭适配器(PAF)隔振技术的进展[J]. 航天器环境工程, 2007, 24(1): 43-46
引用本文: 王跃宇, 冷力强, 李 志, 李 勇. 星箭适配器(PAF)隔振技术的进展[J]. 航天器环境工程, 2007, 24(1): 43-46
WANG Yueyu, LENG Liqiang, LI Zhi, LI Yong. The Recent Development of Vibration Isolation Technique of Payload Attach Fitting[J]. Spacecraft Environment Engineering, 2007, 24(1): 43-46.
Citation: WANG Yueyu, LENG Liqiang, LI Zhi, LI Yong. The Recent Development of Vibration Isolation Technique of Payload Attach Fitting[J]. Spacecraft Environment Engineering, 2007, 24(1): 43-46.

星箭适配器(PAF)隔振技术的进展

The Recent Development of Vibration Isolation Technique of Payload Attach Fitting

  • 摘要: 星箭适配器(PAF)隔振技术是指在不修改卫星原有结构的前提下,设计具有隔振效能的适配器或在适配器与星箭界面之间引入隔振装置,以隔离卫星发射阶段轴向或侧向的振动。该技术可以降低卫星的质量控制成本,提高卫星发射的可靠性。文章对星箭适配器隔振技术国内外研究进展进行了总结和评述,对美国CSA和欧空局EADS的产品做了介绍,并对我国星箭适配器隔振技术的未来发展途径提出了建议。
    Abstract: The vibration isolation technique of payload attach fitting(PAF) refers to inserting isolators or the isolating PAF between the satellite and the launch vehicle to isolate the satellite axial/lateral vibration without any alterations of the existing satellite structure. The use of this vibration isolation technique can reduce the launch-induced dynamic loads and the quality control costs of the satellite, and to improve the satellite reliability during launch. In this paper, the recent development of the researches and engineering applications of the vibration isolation technique of PAF are introduced in detail and some suggestions about future development of this vibration isolation technique in China are proposed.
  • [1] Wilke P S, Johnson C D, Fosness E R. Payload isolation system for launch vehicles[J]. SPIE, 1997, ( 3045): 20~30 [2] 袁家军, 等. 卫星结构设计与分析[M]. 中国宇航出版社 [Yuan Jiajun, et al. Design and analysis of satellite structures[M]. China Astronautic Publishing House] [3] Edberg D L, Johnson C D, Davis L P, Fosness E R. On the development of a launch vibration isolation system[J]. SPIE, 1997, (3045): 31~37 [4] Johnson C D, Wilke P S, Grosserode P J. Whole-spacecraft vibration isolation system for the GFO/Taurus mission[J]. SPIE, 1999, (3672): 175~185 [5] Rittweger A, Beig H, Konstanzer P, Dacal R B. Active payload adaptor for ariane 5[A]. IAC-05-C2-4-02, 56th International Astronautical Congress, Fukuoka, Japan, 2005 [6] Johnson C D, Wilke P S, Darling K R. Multi-axis whole-spacecraft vibration isolation for small launch vehicles[J]. SPIE, 2001, (4331): 162~174 [7] Wilke P S, Johnson C D, Fosness E R. Whole-spacecraft passive launch isolation[J]. J of Spacecraft & Rockets, 1998, 35(5): 690~694 [8] Denoyer K K, Johnson C D. Recent achievements in vibration isolation systems for space launch and on-orbit application[A]. IAC-01-I.2-01, 52nd International Astronautical Congress, Toulouse, France, 2001 [9] Mace B R. Active control of flexible vibrations[J]. J of Sound & Vibration, 1987, 114: 253~270 [10] Meirovitch L, Baruh H, et al. A comparison of control techniques for large flexible systems[J]. J of Guidance, Control & Dynamics, 1983, 6: 302~310 [11] 张军, 谌勇, 张志谊, 华宏星. 一种整星隔振器的研制[J]. 振动与冲击, 2005, 24(5): 35~38 [Zhang Jun, Chen Yong, Zhang Zhiyi, Hua Hongxing. The development of a kind of whole-spacecraft vibration isolation system[J]. Chinese J of Vibration and Shock, 2005, 24(5): 35~38]
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出版历程
  • 收稿日期:  2006-11-20

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