微小卫星太阳帆板压紧释放机构的设计

宣明; 张道威; 谷松; 杨林; 程龙

doi:10.3788/OPE.20172504.0979

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微小卫星太阳帆板压紧释放机构的设计

微纳技术与精密机械 | 更新时间：2020-07-07

- 微小卫星太阳帆板压紧释放机构的设计
- Design of hold-down and release mechanism for solar panel of micro-satellite
- 光学精密工程 2017年25卷第4期页码：979-986
- 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：
  
  [ "宣明 (1956-)，男，江苏常州人，研究员，博士生导师，1985年于中国科学院长春光学精密机械与物理研究所获得硕士学位，主要从事MEMS、精密机械方面的研究。E-mail:xuanm@ciomp.ac.cn" ]
  张道威 (1991-), 男, 河南信阳人, 硕士研究生, 2014年于浙江大学获得学士学位, 主要从事卫星展开机构方面的研究。E-mail:877061527@qq.com ZHANG Dao-wei, E-mail:877061527@qq.com
- 基金信息：
  
  国家自然科学基金资助项目(No.41501383)
- DOI：10.3788/OPE.20172504.0979
  中图分类号： V423.44
- 收稿日期：2016-04-20，
  
  录用日期：2016-8-15，
  
  纸质出版日期：2017-04-25
- 稿件说明：
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宣明, 张道威, 谷松, 等. 微小卫星太阳帆板压紧释放机构的设计[J]. 光学精密工程, 2017,25(4):979-986.

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.
宣明, 张道威, 谷松, 等. 微小卫星太阳帆板压紧释放机构的设计[J]. 光学精密工程, 2017,25(4):979-986. DOI： 10.3788/OPE.20172504.0979.

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.

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references

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