面向小型自主航天器的锥-杆式对接机构锥面构型设计

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英文篇名：Designing of Conical Surface Configuration for the Probe-cone Docking Mechanism Facing to Mini-Spacecraft 作者：韩伟 ; 姜志杰 ; 黄奕勇 ; 陈小前 英文作者：HAN Wei;JIANG Zhijie;HUANG Yiyong;CHEN Xiaoqian;National Innovation Institute of Defense Technology; 关键词：在轨服务 ; 航天器 ; 对接机构 ; ANSYS/LS-DYNA 英文关键词：On-Orbit Servicing(OOS);;Spacecraft;;Docking mechanism;;ANSYS/LS-DYNA 中文刊名：KJKB 英文刊名：Chinese Journal of Space Science 机构：军事科学院国防科技创新研究院; 出版日期：2019-03-15 出版单位：空间科学学报 年：2019 期：v.39 基金：国家自然科学基金项目资助(91216201,11725211) 语种：中文; 页：KJKB201902012 页数：5 CN：02 ISSN：11-1783/V 分类号：88-92

摘要

对接锥是对接机构的重要组成部分,在碰撞过程中首先与主动对接机构相接触.比较小的锥角会造成系统在碰撞过程中发生剧烈振动,而比较大的锥角又会使系统的接触碰撞力增大,甚至造成对接失败.本文针对面向在轨服务的小型航天器上使用的锥-杆式对接机构,提出了新的对接锥型面设计目标;利用有限元分析软件ANSYS/LS-DYNA,仿真分析了对接机构碰撞后的运动学特性;通过研究对接锥的型面设计方法,得到了新型对接锥型面.研究结果表明,新型对接机构的整体性能满足设计目标要求.
        With mankind ceaselessly breaking new ground in the field of space, the growing demands for autonomous on-orbit servicing are putting forward higher requirements to the autonomy, diversity,robustness, reliability and the overall performance of the space rendezvous and docking mechanism.To ensure high success rate and reliability of the spacecraft docking process in space, attentions should be paid on the design, development and test of the docking mechanism. Focusing on the probe-cone docking mechanism utilized on mini-spacecraft for On-Orbit Servicing(OOS), a new design objective of docking cone is presented in this paper. The impact process is simulated using the explicit finite element code, ANSYS/LS-DYNA, and the influence of the docking mechanism on the process is investigated with the kinematical simulation. In addition, on the basis of above simulation analyses, the innovational design technique of docking cone is studied and a new satisfied docking cone is obtained. The results show that the integrated performance of the whole mechanism can meet the capturing requirements of the design objective.

引文

[1] CHEN X Q, YUAN J P, YAO W, et al. On-orbit Service Technology of Spacecraft[M]. Beijing:China Astronaitic Publishing House, 2009(陈小前,袁建平,姚雯,等.航天器在轨服务技术[M].北京:中国宇航出版社,2009)
    [2] HAYS A B, TCHORYK P, PAVLICH J C, et al. Dynamic simulation and validation of a satellite docking system[J].SPIE, 2003, 5088:77-88
    [3] HAYS A B, TCHORYK P, PAVLICH J C. Advancements in design of an autonomous satellite docking system[J].SPIE, 2004, 5419:107-118
    [4] RIVERA D E, MOTAGHEDI P. HAYS A B. Modeling and simulation of the Michigan aerospace autonomous satellite docking system II[J]. SPIE, 2005, 5799:82-91
    [5] STAMM S, MOTAGHEDI P. Orbital express capture system:Concept to reality[J]. SPIE, 2004, 5419:78-91
    [6] ODA M, KIBE K, YAMAGATA F. ETS-VII, space robot in-orbit experiment satellite[C]//Proceedings of IEEE International Conference on Robotics and Automation.Minneapolis Minnesota, 1996:739-744
    [7] IS AO K, MASAAKI M, TORU K, et al. Result of autonomous rendezvous docking experiment of engineering test satellite-VII[J]. J. Spacec. Rock., 2001, 38(1):105-111
    [8] HAN Wei, HUANG Yiyong, ZHANG Xiang, et al. Research and development of an impact testing system for space docking mechanism[J]. Chin. J. Space Sci.,2013,33(5):548-553(韩伟,黄奕勇,张翔,等.空间对接机构碰撞试验系统的开发研究[J].空间科学学报,2013, 33(5):548-553)
    [9] HAN Wei, HUANG Yiyong, ZHANG Xiang, et al.Collision simulation analysis for flexible probe-cone docking mechanism[J]. Aerns.Shanghai, 2012, 29(3):49-53(韩伟,黄奕勇,张翔,等.柔性锥-杆式对接机构碰撞过程仿真研究[J].上海航天,2012, 29(3):49-53)