纳卫星变轨段质量矩姿态控制系统设计

doi:10.7527/S1000-6893.2016.0306

电子电气工程与控制

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

纳卫星变轨段质量矩姿态控制系统设计

陆正亮, 张翔, 于永军, 莫乾坤, 廖文和

南京理工大学机械工程学院, 南京 210094

收稿日期:2016-09-12 修回日期:2016-11-21 出版日期:2017-06-15 发布日期:2016-11-27
通讯作者: 张翔,E-mail:zhxiang2002@126.com E-mail:zhxiang2002@126.com
基金资助:
南京理工大学自主科研专项（30916011101）

Design of moving-mass attitude control system for nanosatellites in orbital transfer stage

LU Zhengliang, ZHANG Xiang, YU Yongjun, MO Qiankun, LIAO Wenhe

College of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China

Received:2016-09-12 Revised:2016-11-21 Online:2017-06-15 Published:2016-11-27
Supported by:
The Scientific Research Project of NJUST (30916011101)

摘要/Abstract

摘要：

提出应用质量矩控制技术实现纳卫星轨道机动过程中的姿态稳定控制。在设计出质量矩滑块构型后，利用动量和动量矩定理推导了八自由度（DOF）动力学模型，并根据动力学分析结果建立了简化控制模型。以此为基础，基于全局滑模控制理论设计了俯仰偏航通道姿态稳定和滑块位置跟踪的鲁棒控制器，并在参数不确定性条件下对控制系统进行了仿真，结果表明：所设计的二维质量矩控制系统能快速控制卫星姿态，并对系统扰动具有较强的鲁棒性，可以应用于纳卫星变轨段的姿态控制。

关键词: 变轨, 纳卫星, 质量矩, 姿态控制, 滑模控制

Abstract:

A moving-mass control technology is proposed to stabilize the attitude of nanosatellites in orbital transfer stage. After the configuration of actuator masses is obtained, 8 DOF dynamic equations are derived based on momentum and moment of momentum theorem. According to the results of dynamic analysis, a simplified control model is developed. On this basis, a robust controller characterized by a global sliding mode is given to stabilize the yaw and pitch angle and to track the actuator position. The validation of this control system is simulated with the condition of parametric uncertainty. Results indicate that the two-dimensional mass moment control system could rapidly adjust the attitude and have a good robustness against disturbance. It is concluded that this system can be applied for attitude control in orbital transfer.

Key words: orbital transfer, nanosatellite, moving-mass, attitude control, sliding mode control

中图分类号:

V448.222

陆正亮, 张翔, 于永军, 莫乾坤, 廖文和. 纳卫星变轨段质量矩姿态控制系统设计[J]. 航空学报, 2017, 38(6): 320778-320778.

LU Zhengliang, ZHANG Xiang, YU Yongjun, MO Qiankun, LIAO Wenhe. Design of moving-mass attitude control system for nanosatellites in orbital transfer stage[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(6): 320778-320778.

参考文献

[1] RHEE M S, ZAKRZWSKI C M, THOMAS M A. Highlights of nanosatellite propulsion development program at NASA-Goddard Space Flight Center[C]//Proceedings of 14th Annual AIAA/USU Small Satellite Conference. Utah: Utah State University, 2000.
[2] 吕振铎. 轨道机动期间的姿态控制[J]. 中国空间科学技术, 1994(5): 25-30. LV Z D. Attitude control during orbit maneuver[J]. Chinese Space Science and Technology, 1994(5): 25-30 (in Chinese).
[3] 李雯, 肖凯. 变轨发动机工作态主动式自旋稳定姿态控制[J]. 宇航学报, 2004, 25(2): 231-234. LI W, XIAO K. Active attitude control for a spin-stabilized spacecraft while the orbit transform motor is working[J]. Journal of Astronautics, 2004, 25(2): 231-234 (in Chinese).
[4] 张钊, 胡军. 轨道机动时考虑延迟的卫星姿态稳定控制方法[J]. 宇航学报, 2011, 32(2): 290-296. ZHANG Z, HU J. Satellite attitude stabilization with time delay during orbital maneuver[J]. Journal of Astronautics, 2011, 32(2): 290-296 (in Chinese).
[5] 高长生, 李君龙, 荆武兴, 等. 导弹质量矩控制技术发展综述[J]. 宇航学报, 2010, 31(2): 307-314. GAO C S, LI J L, JING W X, et al. Key technique and development for moving mass actuated kinetic missile[J]. Journal of Astronautics, 2010, 31(2): 307-314 (in Chinese).
[6] WHITE J E, ROBINETT R D. Principal axis misalignment control for deconing of spinning spacecraft[J]. Journal of Guidance, Control, and Dynamics, 1994, 17(4): 823-830.
[7] BYRNE R H, STURGIS B R, ROBINETT R D. A moving mass trim control system for reentry vehicle guidance: AIAA-1996-3438[R]. Reston: AIAA, 1996.
[8] REGAN F J, KAVETSKY R A. Add-on controller for reentry vehicles: U.S., Serial No.752766[P]. 1984.
[9] PETSOPOULOS, REGAN F J, BARLOW J. Moving mass control system for fixed-trim reentry vehicle[J]. Journal of Spacecraft Rockets, 1996, 33(1): 54-60.
[10] VADDI S S, MENON P K, SWERIDUK G D. Multi-stepping solution to linear two point boundary value problems in missile integrated control[C]//Proceedings of AIAA Guidance, Navigation and Control Conference. Reston: AIAA, 2005.
[11] VADDI S S, MENON P K, SWERIDUK G D. Multistepping approach to finite-interval missile integrated control[J]. Journal of Guidance, Control and Dynamics, 2006, 29(4): 1015-1019.
[12] MENON P K, SWERIDUK G D, OHLMEYER E J. Integrated guidance and control of moving-mass actuated kinetic warheads[J]. Journal of Guidance, Control and Dynamics, 2004, 27(1): 118-126.
[13] 周凤岐, 易彦, 周军. 克服旋转导弹螺旋运动的方法研究[J]. 宇航学报, 2001, 22(5): 77-81. ZHOU F Q, YI Y, ZHOU J. Research on overcoming the coning motion of rotary missile[J]. Journal of Astronautics, 2001, 22(5): 77-81 (in Chinese).
[14] 易彦, 周凤岐, 余松煜. 变质心控制导弹的稳定性分析与鲁棒控制[J]. 上海交通大学学报, 2003, 37(4): 570-573. YI Y, ZHOU F Q, YU S Y. Analysis on stability of variable centroid controlled missile and robust control[J]. Journal of Shanghai Jiaotong University, 2003, 37(4): 570-573 (in Chinese).
[15] 何珺, 周凤岐, 周军. 变质心控制导弹H_∞综合LPV鲁棒自动驾驶仪的设计[J]. 西北工业大学学报, 2004, 22(3): 360-364. HE J, ZHOU F Q, ZHOU J. On using moving-mass-center H_∞ control for simplifying design of LPV missile autopilot[J]. Journal of Northwestern Polytechnical University, 2004, 22(3): 360-364 (in Chinese).
[16] 高长生, 荆武兴, 于本水, 等. 质量矩导弹构型及自适应控制律设计[J]. 航空学报, 2010, 31(8): 1593-1599. GAO C S, JING W X, YU B S, et al. Configuration and adaptive control law design for a mass moment missile[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(8): 1593-1599 (in Chinese).
[17] 李瑞康, 荆武兴, 高长生, 等. 变质心飞行器姿态与弹道性能分析[J]. 宇航学报, 2009, 30(4): 1498-1503. LI R K, JING W X, GAO C S, et al. Performance analysis of attitude and ballistic for moving mass actuated vehicle[J]. Journal of Astronautics, 2009, 30(4): 1498-1503 (in Chinese).
[18] 魏鹏鑫, 高长生, 荆武兴. 基于稳定性分析的变质心再入飞行器布局参数设计[J]. 导弹与航天运载技术, 2012(1):34-39. WEI P X, GAO C S, JING W X. Research on the method of layout parameter design for moving mass actuated reentry vehicle based on stability analysis[J]. Missiles and Space Vehicles, 2012(1): 34-39 (in Chinese).
[19] YOUNG T A. Attitude dynamics and control of a spacecraft using shifting mass distribution[D]. Pennsylvania: The Pennsylvania State University, 2012.
[20] ATKINS B, HENDERSON T. Under-actuated moving mass attitude control for a 3U CuBeSat mission[C]//Proceedings of Spaceflight mechanics 2012. Charleston: American Astronautical Society, 2012: 2083-2094.
[21] KEVIN L Z, JERRY F, DARREN R, et al. CubeSat solid rocket motor propulsion systems providing delta-Vs greater than 500 m/s[C]//Proceedings of 28th Annual AIAA/USU Small Satellite Conference. Utah: Utah State University, 2014.
[22] 屠善澄. 卫星姿态动力学与控制(1)[M]. 北京: 中国宇航出版社, 1999: 49-73. TU S C. Satellite attitude dynamic and control(1)[M]. Beijing: China Astronautic Publishing House, 1999: 49-73 (in Chinese).
[23] 张晓宇, 贺有智, 王子才. 基于H_∞性能指标的质量矩拦截弹鲁棒控制[J]. 航空学报, 2007, 28(3): 635-640. ZHANG X Y, HE Y Z, WANG Z C. Robust control of mass moment interception missile based on H_∞ performance characteristics[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(3): 635-640 (in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

纳卫星变轨段质量矩姿态控制系统设计

Design of moving-mass attitude control system for nanosatellites in orbital transfer stage

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	苏子康, 徐忠楠, 李春涛, 陈海通, 王宏伦. 伸缩套臂式无人机空基回收建模与对接控制[J]. 航空学报, 2023, 44(1): 326315-326315.
[2]	王睿, 周洲, 郭荣化, 黄悦琛. 太阳能无人机伞降着陆多体动力学仿真与试验[J]. 航空学报, 2022, 43(8): 225721-225721.
[3]	吴慈航, 闫建国, 钱先云, 郭一鸣, 屈耀红. 受油机指定时间姿态稳定控制[J]. 航空学报, 2022, 43(2): 324996-324996.
[4]	胡庆雷, 邵小东, 杨昊旸, 段超. 航天器多约束姿态规划与控制:进展与展望[J]. 航空学报, 2022, 43(10): 527351-527351.
[5]	冉茂鹏, 王成才, 刘华华, 王薇, 吕金虎. 变体飞行器控制技术发展现状与展望[J]. 航空学报, 2022, 43(10): 527449-527449.
[6]	贾庆轩, 段嘉琪, 陈钢. 机器人在轨装配无标定视觉伺服对准方法[J]. 航空学报, 2021, 42(6): 424063-424063.
[7]	魏科鹏, 胡健, 姚建勇, 邢浩晨, 乐贵高. 航空机电作动器神经网络快速终端滑模控制[J]. 航空学报, 2021, 42(6): 624540-624540.
[8]	黄旭星, 李爽, 杨彬, 孙盼, 刘学文, 刘新彦. 人工智能在航天器制导与控制中的应用综述[J]. 航空学报, 2021, 42(4): 524201-524201.
[9]	梁小辉, 胡昌华, 周志杰, 王青. 基于自适应动态规划的运载火箭智能姿态容错控制[J]. 航空学报, 2021, 42(4): 524915-524915.
[10]	王雨辰, 林德福, 王伟, 纪毅. 大跨域条件下的自适应滚转稳定容错控制方法[J]. 航空学报, 2021, 42(3): 324368-324368.
[11]	姜斌, 张柯, 杨浩, 程月华, 马亚杰, 成旺磊. 卫星姿态控制系统容错控制综述[J]. 航空学报, 2021, 42(11): 524662-524662.
[12]	刘闯, 岳晓奎. 空间非合作航天器抓捕后姿态抗干扰控制[J]. 航空学报, 2021, 42(11): 524849-524849.
[13]	李帅聪, 何睿智, 汤国建, 敖鹏. 基于滑模控制的剖面跟踪制导律[J]. 航空学报, 2020, 41(S2): 724578-724578.
[14]	徐赫屿, 王大轶, 李文博, 刘成瑞, 符方舟. 基于算子理论的系统可重构性评价与自主重构[J]. 航空学报, 2020, 41(S1): 723747-723747.
[15]	张超凡, 董琦. 考虑输入饱和的固定翼无人机自适应增益滑模控制[J]. 航空学报, 2020, 41(S1): 723755-723755.