The structure of the micro-satellite is exquisite and compact which requires the long whip antenna to be tucked into the specific deployable mechanism. This paper analyses the advantages and disadvantages of commonly used the swing arm deployable mechanism and on this basis we design a kind of rotating disk deployable mechanism. By the mechanics analysis and comparison of this two mechanism, the superiority of the new mechanism on the mechanical and dynamic performance was proved. This design and the conclusion has great significance in futher research.
| Published in | Science Discovery (Volume 4, Issue 6) |
| DOI | 10.11648/j.sd.20160406.18 |
| Page(s) | 393-397 |
| Creative Commons |
This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited. |
| Copyright |
Copyright © The Author(s), 2016. Published by Science Publishing Group |
Whip Antenna, Deployable Mechanism, Rotating Disk, Mechanics Analysis
| [1] | 林来兴，张小琳.迎接“轨道革命”——微小卫星的飞速发展[J].航天器工程，2016,25（2）：97-104。 |
| [2] | Zhigang Xing, Gangtie Zheng. Deploying process modeling and attitude control of a satellite with a large deployable antenna [J]. Chinese Journal of Aeronautics, (2014), 27 (2): 299–312. |
| [3] | 钟世宏，孙巍，张崇耿.新型可折叠翼板展开机构的设计及动力学研究[J].航天制造技术,2013(5)：17-20。 |
| [4] | 王天舒，孔宪仁，王本利.太阳帆板绳索联动同步机构的机理和功能分析[J].宇航学报，2000,21（3）：29-33。 |
| [5] | Bouwmeester J, Gill E K A, Verhoeven C J M. Advancing nanosatellite platforms: the Delfi program[C]. Proceedings of the 59th International Astronautical Congress, Glasgow, Scotland. 2008. |
| [6] | Ubbels W J, et al. Delfi-C3: a student nanosatellite as a test-bed for thin film solar cells and wireless onboard communication [C]. Recent Advances in Space Technologies, 2005. RAST 2005. Proceedings of 2nd International Conference on. IEEE, 2005: 167-172. |
| [7] | Van Breukelen E D, Bonnema A R, Ubbels W J, et al. Delfi-C3: Delft University of Technology’s Nanosatellite [C]. Proceedings of the 4S Symposium: Small Satellites, Systems and Services, Chia Laguna, Italy. 2006. |
| [8] | Ubbels W J, Verhoeven C J M, Hamann R J, et al. First flight results of the Delfi-C3 satellite mission [J]. 2008. |
| [9] | Ubbels W J, Bonnema A R, Rotteveel J, et al. A Miniaturized Nanosatellite VHF/UHF Communications System [J]. 2008. |
| [10] | ISIS-Innovative Solutions In Space. ANTS VHF/UHF Antenna Brochure[EB/OL].http://www.isispace.nl/brochures/ISIS_ANTS_Antenna_Brochure_v.1.5.pdf. |
| [11] | 陈烈民.航天器结构与机构[M].北京：中国科学技术出版社，2005:370-374。 |
| [12] | 胡建峰，肖勇.展开速度对天线展开过程动力学影响分析[J].机械工程师，2016,（5）：53-55。 |
| [13] | 杨会生，张银鹤，柴方茂等.离轴三反空间相机调焦机构设计[J].光学精密工程，2013,21（4）：948-954。 |
| [14] | 张淑杰，李瑞祥，丁同才.盘绕式杆状展开机构的设计与力学分析[J].力学季刊，2006,27（2）：341-347。 |
| [15] | 董吉洪，陈小伟.空间相机主镜展开机构设计方案分析[Z].中国科学院长春光学精密机械与物理研究所。 |
| [16] | 宋顺广，王春洁.航天器附件联动展开机构优化设计[J].北京航空航天大学学报，2013,39（7）：912-916。 |
| [17] | 钟世宏，王占利，孙巍.旋转展开弹簧支架的设计及其动力学研究[J].航天制造技术，2009（5）：22-27。 |
| [18] | 李红信．可展开平面天线机构展开过程分析与实验研究[D]．哈尔滨工业大学，2014.7。 |
| [19] | 张文会．一种天线展开机构[J]．西安：中国空间技术研究院西安分院.“可展开空间结构”学术会议。 |
APA Style
Han Jin, Wang Xinsheng. (2016). Design and Analysis of Micro-Satellite Whip Antenna Rotating Disk Deployable Mechanism. Science Discovery, 4(6), 393-397. https://doi.org/10.11648/j.sd.20160406.18
ACS Style
Han Jin; Wang Xinsheng. Design and Analysis of Micro-Satellite Whip Antenna Rotating Disk Deployable Mechanism. Sci. Discov. 2016, 4(6), 393-397. doi: 10.11648/j.sd.20160406.18
Share This Article
Twitter
Linked In
Facebook
Copy
Download@article{10.11648/j.sd.20160406.18,
author = {Han Jin and Wang Xinsheng},
title = {Design and Analysis of Micro-Satellite Whip Antenna Rotating Disk Deployable Mechanism},
journal = {Science Discovery},
volume = {4},
number = {6},
pages = {393-397},
doi = {10.11648/j.sd.20160406.18},
url = {https://doi.org/10.11648/j.sd.20160406.18},
eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.sd.20160406.18},
abstract = {The structure of the micro-satellite is exquisite and compact which requires the long whip antenna to be tucked into the specific deployable mechanism. This paper analyses the advantages and disadvantages of commonly used the swing arm deployable mechanism and on this basis we design a kind of rotating disk deployable mechanism. By the mechanics analysis and comparison of this two mechanism, the superiority of the new mechanism on the mechanical and dynamic performance was proved. This design and the conclusion has great significance in futher research.},
year = {2016}
}
TY - JOUR T1 - Design and Analysis of Micro-Satellite Whip Antenna Rotating Disk Deployable Mechanism AU - Han Jin AU - Wang Xinsheng Y1 - 2016/12/01 PY - 2016 N1 - https://doi.org/10.11648/j.sd.20160406.18 DO - 10.11648/j.sd.20160406.18 T2 - Science Discovery JF - Science Discovery JO - Science Discovery SP - 393 EP - 397 PB - Science Publishing Group SN - 2331-0650 UR - https://doi.org/10.11648/j.sd.20160406.18 AB - The structure of the micro-satellite is exquisite and compact which requires the long whip antenna to be tucked into the specific deployable mechanism. This paper analyses the advantages and disadvantages of commonly used the swing arm deployable mechanism and on this basis we design a kind of rotating disk deployable mechanism. By the mechanics analysis and comparison of this two mechanism, the superiority of the new mechanism on the mechanical and dynamic performance was proved. This design and the conclusion has great significance in futher research. VL - 4 IS - 6 ER -
Email: