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论文:2019,Vol:37,Issue(4):673-681 |
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引用本文： |
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唐永兴, 朱战霞. 基于螺旋理论的DFP隔振航天器相对运动动力学建模与姿轨耦合控制[J]. 西北工业大学学报 |
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TANG Yongxing, ZHU Zhanxia. Relative Motion Dynamics Modeling and Control of DFP Vibration Isolation Spacecraft[J]. Northwestern polytechnical university |
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| 基于螺旋理论的DFP隔振航天器相对运动动力学建模与姿轨耦合控制 |
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| 唐永兴1,2, 朱战霞1,2 |
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1. 西北工业大学 航天学院, 陕西 西安 710072;
2. 航天飞行动力学技术国家级重点实验室, 陕西 西安 710072 |
| 摘要: |
| 为更好满足未来高精度任务要求，以由无接触的有效载荷模块（payload module，PM）和支持模块（support module，SM）组成的DFP （disturbance-free payload）航天器为对象，开展两模块间的相对运动动力学建模与控制研究和系统隔振性能验证。首先通过简化构型、梳理受力情况，重点推导了两模块所受力和力矩表达式；其次考虑耦合效应，利用对偶四元数建立了模型精度更高且形式简洁统一的DFP航天器两模块间的相对运动动力学方程；在此基础上设计PD控制律，考虑控制量可测性及敏感器测量误差，使PM和SM的相对运动满足DFP航天器工作要求。仿真结果验证了DFP航天器的隔振优势和姿态机动性能。 |
| 关键词:
DFP航天器
对偶四元数
相对运动动力学建模
PD控制
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| Relative Motion Dynamics Modeling and Control of DFP Vibration Isolation Spacecraft |
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| TANG Yongxing1,2, ZHU Zhanxia1,2 |
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1. School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. National Key Laboratory of Aerospace Flight Dynamics, Xi'an 710072, China |
| Abstract: |
| In order to better meet the future high precision task requirements, the DFP(Disturbance-Free Payload) spacecraft composed of non-contact PM(Payload Module)and SM(Support Module)is taken as the object to study the relative motion dynamics modeling and control between the two modules and verify the system vibration isolation performance. Firstly, the force and torque expressions of the two modules are derived by simplifying the configuration and analyzing the stress. In view of that couple effect, the relative motion dynamics equations between two modules of DFP spacecraft with high model accuracy, and simple and uniform format are established with the dual quaternions. Based on this, the PD control law is designed, and the relative motion of PM and SM could meet DFP spacecraft working requirements when the measurability of control quantity and the measurement error of sensors were taken into account. Simulation results verify the advantage of vibration isolation and attitude maneuverability of DFP spacecraft. |
| Key words:
DFP spacecraft
dual quaternions
relative motion dynamics modeling
PD control
vibration isolation
simulation
measurement error of sensors
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| 收稿日期: 2018-09-10
修回日期:
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| DOI: 10.1051/jnwpu/20193740673 |
| 基金项目: 国家自然科学基金（11472213）资助 |
| 通讯作者:
Email： |
| 作者简介: 唐永兴(1996-),西北工业大学博士研究生,主要从事飞行动力学与控制研究。
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参考文献: |
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[1] 马明阳. 双体卫星地面试验系统设计及隔振效能分析[D]. 哈尔滨:哈尔滨工业大学,2016 MA Yangming. The Design and Analysis on Vabration Isolation Efficiency of a Satellte Test System with Architecture of Disturbance Free Payload[D]. Habrbin, Harbin Institute of Technology,2016(in Chinese)
[2] 张伟,赵艳彬,廖鹤,等. 动静隔离、主从协同控制双超卫星平台设计[J]. 上海航天,2014,31(5):7-11 ZHANG Wei, ZHAO Yanbin, LIAO He, et al. Design of Active-Quiet Isolated and Master-Slave Coordination Controlled Dual-Super Satellite Platform[J]. Aerospace Shanghai,2014,31(5):7-11(in Chinese)
[3] 杜超. 一种双体卫星的动力学建模与控制研究[D]. 哈尔滨:哈尔滨工业大学,2015 DU Chao. Study on Dynamic Modeling and Controlling of a Satellite with a Architectrue of Disturbance Free Payload[D]. Harbin, Harbin Institute of Technology, 2015(in Chinese)
[4] PEDREIRO N. Spacecraft Architecture for Disturbance Free Payload[J]. Journal of Guidance Control and Dynamics,2002,26(5):794-804
[5] PEDREIRO N, CARRIER A, LORELL K, et al. Disturbance Free Payload Concept Demonstration[C]//AIAA Guidance,Navigation, and Control Conference and Exhibit,Monterey,USA, 2002
[6] GONZALES M, PEDREIRO N, BROOKES K, et al. Unprecedented Vibration Isolation Demonstration Using the Disturbance Free Payload Concept[C]//AIAA Guidance, Navigation,and Control Conference and Exhibit,Providence,USA, 2004
[7] PEDREIRO N, GONZALES M, FOSTER B, et al. Agile Disturbance Free Payload[C]//AIAA Guidance,Navigation,and Control Conference and Exhibit,San Francisco,USA, 2005
[8] 黄思萌. 基于DFP系统的三刚体航天器快速机动技术研究[D]. 哈尔滨:哈尔滨工业大学,2016 HUANG Simeng. Research on Agile Technologies of Three-Rigid-Body Spacecraft Based on DFP System[D]. Harbin, Harbin Institute of Technology,2016(in Chinese)
[9] 孔宪仁,武晨,刘源, 等. 无扰载荷航天器相对运动动力学建模[J]. 宇航学报,2017,38(11):1139-1146 KONG Xianren, WU Chen, LIU Yuan, et al. Dynamic Modeling of Relative Motion for Disturbance-Free-Payload Spacecraft[J]. Journal of Astronautics,2017,38(11):1139-1146(in Chinese)
[10] 张大卫,冯晓梅. 音圈电机的技术原理[J]. 中北大学学报,2006(3):224-228 ZHANG Dawei, FENG Xiaomei. The Technical Principle of Voice-Coil Actuator[J]. Journal of North University of China, 2006(3):224-228(in Chinese)
[11] 刘剑,朱战霞,马家瑨. 基于螺旋理论的航天器相对运动建模与控制[J]. 西北工业大学学报,2013,31(4):590-595 LIU Jian, ZHU Zhanxia, MA Jiajin. Establishing Spacecraft's Relative Orbit and Attitude Coupling Dynamics Model Based on Screw Theory[J]. Journal of Northwestern Polytechnical University,2013,31(4):590-595(in Chinese)
[12] 朱战霞,马家瑨,樊瑞山. 航天器相对运动姿轨耦合特性研究[J]. 西北工业大学学报,2015,33(6):887-891 ZHU Zhanxia, MA Jiajin, FAN Ruishan. Coupling Analysis on Relative Motion of Spacecraft Attitude and Orbit Model Based on Dual Quaternion[J]. Journal of Northwestern Polytechnical University,2015,33(6):887-891(in Chinese)
[13] 朱战霞,马家瑨,樊瑞山. 基于螺旋理论描述的空间相对运动姿轨同步控制[J]. 航空学报,2016,37(9):2788-2798 ZHU Zhanxia, MA Jiajin, FAN Ruishan. Synchronization Control of Relative Motion for Spacecraft with Screw Theory-Based Description[J]. Acta Aeronautical et Astronautica Sinica,2016,37(9):2788-2798(in Chinese) |
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