Analysis for structural modal frequency of one rocket with two satellites of GEO satellite for full-electric thruster

WANG Yun-chen; CHEN Chang-ya

doi:10.3788/OPE.20172514.0125

您当前的位置：

首页 >

文章列表页 >

Analysis for structural modal frequency of one rocket with two satellites of GEO satellite for full-electric thruster

更新时间：2020-08-13

- Analysis for structural modal frequency of one rocket with two satellites of GEO satellite for full-electric thruster
- Optics and Precision Engineering Vol. 25, Issue 12z, Pages: 125-133(2017)
- 作者机构：
  
  上海卫星工程研究所上海,200240
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20172514.0125
  CLC： TP391.9
- Received：29 August 2017，
  
  Revised：20 September 2017，
  
  Published：31 December 2017
- 稿件说明：
移动端阅览
王韵臣, 陈昌亚,. 全电推进GEO卫星一箭双星结构模态频率分析[J]. 光学精密工程, 2017,25(12z): 125-133

WANG Yun-chen, CHEN Chang-ya,. Analysis for structural modal frequency of one rocket with two satellites of GEO satellite for full-electric thruster[J]. Editorial Office of Optics and Precision Engineering, 2017,25(12z): 125-133
王韵臣, 陈昌亚,. 全电推进GEO卫星一箭双星结构模态频率分析[J]. 光学精密工程, 2017,25(12z): 125-133 DOI： 10.3788/OPE.20172514.0125.

WANG Yun-chen, CHEN Chang-ya,. Analysis for structural modal frequency of one rocket with two satellites of GEO satellite for full-electric thruster[J]. Editorial Office of Optics and Precision Engineering, 2017,25(12z): 125-133 DOI： 10.3788/OPE.20172514.0125.

摘要

为了节省卫星燃料，增加卫星载重比，延长卫星使用寿命，将化学推进平台改为全电推进平台，并且采用"一箭双星"发射。首先设计出使用电推进时的轨道转移方案，根据卫星发射重量使用双台300 mN的推力器并联工作，从GTO至GEO的转移时间约为6个月，消耗燃料仅需约650 kg。针对目前存在的3种一箭双星发射方式，火箭舱内支撑、自串联和并联，分别设计卫星构型，对其进行模态分析，与之前的化学推进方案相比较。可以得出3种满足火箭发射要求的构型中火箭舱内支撑构型最佳，单星横向基频为20.781 Hz，结构质量比为9.8%，选择该构型进行一箭双星发射。综合分析可知，采用全电推进火箭舱内支撑一箭双星发射方式，可以减少燃料，使结构轻量化与整星轻量化，并能够节约发射成本，具有良好的先进性和经济性。

Abstract

Changing chemical thruster platform to full-electric thruster platform can save satellite fuel

increase bearing ratio of satellite and prolong service life of satellite

and "one rocket with two satellites" launch can be adopted. Firstly

orbit transfer scheme at the time of using electric thruster was designed

with satellite launch weight of 2 700 kg

and parallel operation for two 300 mN thrusters was used. Transfer time from GTO to GEO was about 6 months

and consumption fuel of 650 kg was just needed. Aimed at current existing three kinds of launch modes for one rocket with two satellites

support

self-series and parallel inside rocket tank were provided with modal analysis by designing satellite configuration respectively to compare with previous chemical thruster scheme. It can be obtained that three kinds of configurations for one rocket with two satellites all meet requirements for rocket launch

of which support configuration inside rocket tank is the best with horizontal frequency of 20.781 Hz and structural weight ratio of 9.8% per satellite

and this configuration shall be used to conduct launch of one rocket with two satellites. Comprehensive analysis shows that adopting launch mode for one rocket with two satellites for support inside rocket tank of full-electric thruster is relatively good

which can save more than one hundred million of lunch cost

and its has excellent advancement and economy.

关键词

Keywords

references

杭观荣, 康小录. 电推进在深空探测主推进中的应用及发展趋势[J]. 火箭推进, 2013, 38(4):1-8, 48. HANG G R, KANG X L. Application and development trends of electric propulsion in deep-space primary propulsion[J]. Journal of Rocket Propulsion, 2013, 38(4):1-8, 48. (in Chinese)

张天平, 张雪儿. 空间电推进技术及应用新进展[J]. 真空与低温, 2013, 19(4):187-194. ZHANG T P, ZHANG X E. Electric propulsion progress in technologies and applications[J]. Vacuum & Cryogenics, 2013, 19(4):187-194. (in Chinese)

胡照, 王敏, 袁俊刚. 国外全电推进卫星平台的发展及启示[J]. 航天器环境工程, 2015, 32(5):566-570. HU ZH, WANG M, YUAN J G. A review of the development of all-electric propulsion platform in the world[J]. Spacecraft Environment Engineering, 2015, 32(5):566-570. (in Chinese)

GOPINATH N S, SRINIVASAMUTHY K N. Optimal low thrust orbit transfer from GTO to geosynchronous orbit and station keeping using electric propulsion system[C]. 54th International Astronautical Congress of the International Astronautical Federation, IAF, 2003:2-3.

夏利娟, 金咸定, 汪庠宝. 卫星结构蜂窝夹层板的等效计算[J]. 上海交通大学学报, 2003, 37(7):999-1001. XIA L J, JIN X D, WANG X B. Equivalent analysis of honeycomb sandwich plates for satellite structure[J]. Journal of Shanghai Jiaotong University, 2003, 37(7):999-1001. (in Chinese)

NASA HDBK 7004B-2003 Force limited vibration testing[S]. 2003:24-30.

SHUNMUGAVEL P. Modal effective masses for space vehicles[C]. 36th Structures, Structural Dynamics and Materials Conference, AIAA, 1995:19-25.

WITTING M, KLEIN M. Modal selection by means of effective masses and effective modal forces an application example[C]. Proceedings of Conference on Spacecraft Structures, Materials & Mechanical Testing, ESA Bulletin, 1996:751-759.

马爱军, 周传月, 王旭. Patran和Nastran有限元分析专业教程[M]. 北京:清华大学出版社, 2005:291-297. MA A J, ZHOU CH Y, WANG X. Tutorial of Finite Element Analysis of Patran and Nastran[M]. Beijing:Tsinghua University Press, 2005:291-297. (in Chinese)

Views

279

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Design and research of the double-head ultrasonic consolidation vibration system

Structure design of two-axis fast steering mirror for aviation optoelectronic platform

Structrual design of detector for optical elements with large aperture

Design of six dimensional vibration isolation system for space optical payload

Support structure of primary mirror for small optical remote sensor

Related Author

FENG Sailong

ZOU Lingling

ZHONG Xiangqiang

Quanchao LI

Yefei WANG

Yongsen XU

Fuchao WANG

Songnian TAN

Related Institution

School of Mechanical Engineering， Anhui Polytechnic University

Key Laboratory of Airborne Optical Imaging and Measurement， Chinese Academy of Sciences

University of Chinese Academy of Sciences

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

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

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