Design of hold-down and release mechanism for solar panel of micro-satellite

Ming XUAN; Dao-wei ZHANG; Song GU; Lin YANG; Long CHENG

doi:10.3788/OPE.20172504.0979

您当前的位置：

首页 >

文章列表页 >

Design of hold-down and release mechanism for solar panel of micro-satellite

Micro/Nano Technology and Fine Mechanics | 更新时间：2020-07-07

- Design of hold-down and release mechanism for solar panel of micro-satellite
- Optics and Precision Engineering Vol. 25, Issue 4, Pages: 979-986(2017)
- 作者机构：
  
  1.中国科学院长春光学精密机械与物理研究所, 吉林长春 130033
  2.中国科学院大学, 北京 100039
  3.长光卫星技术有限公司, 吉林长春 130033
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20172504.0979
  CLC： V423.44
- Received：20 April 2016，
  
  Accepted：15 August 2016，
  
  Published：25 April 2017
- 稿件说明：
移动端阅览
Ming XUAN, Dao-wei ZHANG, Song GU, et al. Design of hold-down and release mechanism for solar panel of micro-satellite[J]. Optics and precision engineering, 2017, 25(4): 979-986.
DOI：

Ming XUAN, Dao-wei ZHANG, Song GU, et al. Design of hold-down and release mechanism for solar panel of micro-satellite[J]. Optics and precision engineering, 2017, 25(4): 979-986. DOI： 10.3788/OPE.20172504.0979.

摘要

为实现某型号微小卫星太阳帆板的压紧释放，研制了一种小型熔线式压紧释放机构。首先，设计了可测量预紧力的压紧机构，得到扭矩与预紧力的2倍关系，给出了预紧力的确定方法。然后，根据绳索特点，设计了具有电阻调节功能的解锁机构，增强了对电源的适应能力，满足了微小卫星快速模块化布局。最后，进行了熔断特性实验与熔断参数设计，得到熔断时间与电流的函数关系，确定了该型号卫星解锁的熔断功率为6.25 W，熔断时间为（6±1）s。开展了实验室环境与真空环境下的可靠性验证实验，结果表明：所设计的压紧释放机构工作可靠，适用于微小卫星展开机构，且具有较好的通用性与扩展性。该项研究对微小卫星太阳帆板压紧释放装置设计和空间展开机构设计具有指导意义。

Abstract

To achieve the hold-down and release for a solar panel of micro-satellites

a small-scale fuse holding-down and release mechanism was developed. Firstly

the hold-down mechanism for measuring pretightening force was designed to acquire the twice relationship between torque and pretightening force and a determination method of pretightening force was given. Then

according to the features of rope

the unlocked mechanism with resistance regulatory function was designed to improve the adaptive capacity of power supply and to meet the requirements of rapid modularization layout of micro-satellites. Finally

a fusing characteristic experiment and the fusing parameters for the mechanism were designed to obtain the function relationship between fusing time and currents. It shows that the unlocked fusing power of this mechanism for micro-satellites is 6.25 W

the fusing time is (6±1) s. The reliability demonstration experiment was also carried out under the environments of laboratory and vacuum. The results show that the hold-down and release mechanism designed is suitable for the unfolding mechanism of micro-satellites

which is reliable work and has better universality and expansibility. It offers a certain guiding significance for design of hold-down and release devices and spatial deployable mechanisms for solar panels of micro-satellites.

关键词

Keywords

references

张雷. 航天器分步展开式太阳翼设计与研究[D]. 上海: 上海交通大学, 2012. http://cdmd.cnki.com.cn/Article/CDMD-10248-1012034938.htm

ZHANG L. Study on solar array wing of spacecraft with deployment by step[D]. Shanghai:Shanghai Jiao Tong University, 2012. (in Chinese)

金光, 谢晓光, 谷松, 等.卫星太阳帆板展开的动力学仿真分析与应用[J].光学精密工程, 2014, 22(3):745-753.

JIN G, XIE X G, GU S, et al.. Dynamic simulation and application of deployable mechanism of satellite solar panels[J]. Opt. Precision Eng., 2014, 22(3):745-753. (in Chinese)

孙家栋.卫星结构设计与分析 (下)[M].北京:中国宇航出版社, 2004.

SUN J D. Design and Analysis of Satellite Structure[M]. Beijing:China Astronautic Publishing House, 2004. (in Chinese)

徐福祥.卫星工程概论[M].北京:中国宇航出版社, 2003.

XU F X. Introduction of Satellite Engineering[M]. Beijing:China Astronautic Publishing House, 2003. (in Chinese)

陈烈民.航天器结构与机构[M].北京:中国科学技术出版社, 2005.

CHEN L M. Spacecraft Structure and Mechanism[M]. Beijing:China Science and Technology Press, 2005. (in Chinese)

王书新, 李景林, 齐光, 等.空间相机用爆炸螺栓防护装置[J].光学精密工程, 2014, 22(12):3318-3323.

WANG S X, LI J X, QI G, et al.. Protecting device for explosive bolt in space camera[J]. Opt. Precision Eng., 2014, 22(12):3318-3323. (in Chinese)

STEWART A C, HAIR J H. Intricacies of using Kevlar cord and thermal Knives in a deployable release system:issues and solutions[C]. Proceedings of the 36th Aerospace Mechanisms Symposium, Glenn Research Center, 2002:243-255.

姜水清, 刘立平.热刀致动的压紧释放装置研制[J].航天器工程, 2005, 14(4):31-34.

JIANG S Q, LIU L P. Development of the hold-down and release mechanism using thermal knife[J].Spacecraft Engineering, 2005, 14(4):31-34.(in Chinese)

任守志, 刘颖, 王举, 等.立方体卫星太阳翼技术综述[J].航天器工程, 2015, 24(2):109:118.

REN S Z, LIU Y, WANG J, et al.. Overview of solar wing for CubeSat[J]. Spacecraft Engineering, 2015, 24(2):109-118. (in Chinese)

THURN A, HUYNH S. A nichrome burn wire release mechanism for CubeSats[C]. Proceedings of the 41st Aerospace Mechanisms Symposium, NASA JPL, 2012.

SENATORE P, KLESH A, ZURBUCHEN T H, et al.. Concept, design, and prototyping of XSAS:A high power extendable solar array for CubeSat applications[C]. Proceedings of the 40th Aerospace Mechanisms Symposium, NASA Kennedy Space Center, 2010.

陈秀宁, 顾大强.机械设计[M].杭州:浙江大学出版社, 2010.

CHEN X N, GU D Q. Machine Design[M]. Hangzhou:Zhejiang University Press, 2010. (in Chinese)

王玉鹏, 王凯, 贾瑞栋, 等.精指向自解锁星载太阳指向器设计与应用[J].光学精密工程, 2016, 24(1):65-72.

WANG Y P, WANG K, JIA R D, et al.. Design and application of accurate pointing and auto-unlocking sun tracker on satellite[J]. Opt. Precision Eng., 2016, 24(1):65-72. (in Chinese)

刘志全.航天器机构的可靠性试验方法[J].中国空间科学技术, 2007, 27(3):39-45.

LIU Z Q, Reliability test methods of spacecraft mechanisms[J]. Chinese Space Science and Technology, 2007, 27(3):39-45. (in Chinese)

刘志全, 陈新华, 孙国鹏.航天器火工机构的可靠性验证试验及评估方法[J].航天器工程, 2008, 17(4):62-66.

LIU Z Q, CHEN X H, SUN G P. Reliability validation tests and evaluation methods for pyrotechnic mechanisms of spacecraft[J]. Spacecraft Engineering, 2008, 17(4):62-66. (in Chinese)

Views

474

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Optimization design and test for bracket of star sensor in micro-satellite

Related Author

LI Lin

WAND Dong

TAN Lu-yang

KONG Lin

YANG Hong-bo

Related Institution

Changchun Institute of Optics, Fine Mechanics and Physics, Chinese Academy of Sciences, Changchun 130033, China

University of Chinese Academy of Sciences

Chang Guang Satellite Technology LTD.,.

AI问答

Address：No.3888 Dong Nanhu Road, Changchun, Jilin, China Postal code：130033
Tel：0431-86176855 Email：gxjmgc@ciomp.ac.cn
Technical support is provided by Beijing Founder electronics co., LTD 吉ICP备11002662号-17 京公网安备11010802024621
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰