Optics and Precision Engineering, Volume. 26, Issue 3, 606(2018)

Electromagnet door release mechanism in deploying mechanism for CubeSats

ZHANG Jiao-long* and ZHOU Jun
Author Affiliations
  • [in Chinese]
  • show less
    References(19)

    [1] [1] SHIN Y, YOON S, SEO Y, et al.. Radiation effect for a cubesat in slow transition from the earth to the moon[J]. Advances in Space Research, 2015, 55(7): 1792-1798.

    [2] [2] VENTURINI C, ABRAMOWITZ L, JOHANSEN J, et al.. CubeSat developmental programs-working with the community[C]. AIAA SPACE 2009 Conference and Exposition, Pasadena, American Institute of Aeronautics and Astronautics Inc, 2009.

    [3] [3] FISH C S, SWENSON C M, CROWLEY G, et al.. Design, development, implementation, and on-orbit performance of the dynamic ionosphere cubeSat experiment mission[J]. Space Science Reviews, 2014, 181(1-4): 61-120.

    [4] [4] YUAN J J. Design and Analysis of Satellite Structures[M]. Beijing: China Astronautic Publishing House, 2004. (in Chinese)

    [5] [5] CAO N L, DONG D Y, LI ZH L. Non-pyrotechnic separation devices research based on shape memory alloy[J]. Spacecraft Recovery & Remote Sensing, 2014, 35(5): 9-18. (in Chinese)

    [6] [6] HU X N, WU J, PENG J SH, et al.. Design and experimental research of a large load and low shock release device on shape memory alloy[J]. Science Technology and Engineering, 2016, 30(16) 319-323. (in Chinese)

    [7] [7] NASON I, PUIG-SUARI J. Development of a family of picosatellite deployers based on the cubesat standard[C]. The 2002 IEEE Aerospace Conference, IEEE, 2002: 457-464.

    [8] [8] MIYAMOTO K, UI K, MATUNAGA S, et al.. Tokyo tech separation demonstration TSD as M-V rocket sub-payload for nanosatellite separation mechanism[C]. The 56th International Astronautical Congress, IAF, 2005: 2271-2277.

    [10] [10] TENG L, JIN ZH H. Pico-satellite separation parameter optimization[J]. Journal of Astronautics, 2016, 37(10): 1200-1206. (in Chinese)

    [11] [11] BAI ZH F, GUO L L, CHEN D S. Late-model non-pyrotechnic devices for separation of satellite-launching vehicle[J]. Missile and Space Vehcile, 2009(1): 31-37. (in Chinese)

    [12] [12] Aerospace, CubeSat Deployer, CubtSat Deployer-PSL family[EB/OL]. http://www.astrofein.com/astro-und-feinwerktechnik-adlershof/products/raumfahrt-eng/193/cubsat-deployer-engl/. (2015-01-06).

    [13] [13] SANG X J. The Design and Performance Analysis for Separation System of Small Satellite from Rocket[D]. Changsha: Graduate School of National University of Defense Technology, 2014. (in Chinese)

    [14] [14] JIANG H. The Hold-on Release Device Based on Vortex Coil Spring Winging Self-locking Principle[D]. Harbin: Harbin Institute of Technology, 2016. (in Chinese)

    [17] [17] PENG K R, HE W G. Design of control surface electromagnetic lock-apparatus system based on integration with BLDCM[J]. Micromotors, 2015, 48(5): 95-97. (in Chinese)

    [18] [18] WU SH, PENG CH L, JIAO Z X, et al.. Design and experimental research of the linear bi-directional force solenoid for electro-hydraulic proportional valve[J]. Journal of Mechanical Engineering, 2014, 50(22): 200-206. (in Chinese)

    [19] [19] GONG B. Research on proportional solenoid′s static characteristics[J]. Fluid Power Transmission & Control, 2017(2): 25-32, 35. (in Chinese)

    Tools

    Get Citation

    Copy Citation Text

    ZHANG Jiao-long, ZHOU Jun. Electromagnet door release mechanism in deploying mechanism for CubeSats[J]. Optics and Precision Engineering, 2018, 26(3): 606

    Download Citation

    EndNote(RIS)BibTexPlain Text
    Save article for my favorites
    Paper Information

    Category:

    Received: Sep. 25, 2017

    Accepted: --

    Published Online: Apr. 25, 2018

    The Author Email: Jiao-long ZHANG (zhangjiaolong@nwpu.edu.cn)

    DOI:10.3788/ope.20182603.0606

    Topics