نوع مقاله : مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 دانشگاه آزاد اسلامی واحد تهران شرق،تهران، ایران

2 گروه پژوهشی طراحی وسایل فضایی، پژوهشکده سامانه های فضانوردی، پژوهشگاه هوافضا، تهران، ایران

چکیده

این مقاله به تحلیل و طراحی مکانیزم باز شدن پنل های صلب فضاپیمای نمونه با اتصالات انعطاف پذیر پرداخته است. مکانیزم گسترش با حفظ سرعت مناسب، همزمانی باز شدن پنل های خورشیدی را تضمین کرده و اثرات ناشی از ضربه و ارتعاشات اعمال شده در مرحله پایانی و پس از قفل شدن پنل ها را با بکارگیری المان های فنر پیچشی در اتصالات پنل ها و محرک پایه به حداقل می رساند. معادلات حرکت سیستم با استفاده از روابط لاگرانژ استخراج شده و رفتار مکانیزم طراحی شده برای مودهای تحریک گشتاور ثابت و متغیر بررسی شده است. نتایج ارائه شده در مقایسه با شبیه سازی های دینامیکی صورت گرفته توسط نرم افزار آدامز و مکانیزم های مشابه کارایی روش پیشنهادی را نشان می دهد.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Modeling and Simulation of a Flexible Spacecraft Solar Panels Deployment Mechanism with Yoke Driven Assembly

نویسندگان [English]

  • Hamidreza Soleimani 1
  • Milad َAzimi 2

1 Islamic Azad University, North Tehran Branch, Tehran, IRAN

2 Aerospace Research Institute of Iran Ministry of Science, Technology and Research, Tehran. IRAN

چکیده [English]

This paper analyses the dynamic behavior of the rigid solar panels deploying mechanism of a spacecraft with flexible hinges. The proposed mechanism, maintaining a proper speed, guarantees the deployment synchronization of solar panels and minimizes the effects of impact and vibration applied during the final stage and after the panels lock-up using torsional springs in the hinges and yoke driven assembly. The equations of the motion of the system are derived using Lagrangian approach and the behavior of the mechanism for constant and variable torque excitation modes is investigated. The simulation results presented along with the dynamic simulations performed by Adams software and conventional mechanisms show the efficiency of the proposed method.

کلیدواژه‌ها [English]

  • Adams
  • Deploying Solar Panels
  • Torsional Spring
  • Flexible Spacecraft
  • Yoke Driven Assembly
[1] Fiore, J., R. Kramer, P. Larkin, and E. Grebenstein, "Mechanical design and verification of the TOPEX/Poseidon deployable solar array," American Institute of Aeronautics and Astronautics, Inc, pp. 125-135, 1994.
[2] Liu, L., X. Wang, S. Sun, D. Cao, andX. Liu, "Dynamic characteristics of flexible spacecraft with double solar panels subjected to solar radiation," Int. J. of Mechanical Sciences, vol. 151, pp. 22-32, 2019.
[3] Yang, X., S. S. Ge, and W. He, "Dynamic modelling and adaptive robust tracking control of a space robot with two-link flexible manipulators under unknown disturbances," Int. J. of Control, vol. 91, pp. 969-988, 2018.
[4] Bain, D., C. Patton and A. Tendean, "Deployable Solar Array Structure: G1: 3," 2019.
[5] Hoang, B., S. White, B. Spence, and S. Kiefer, "Commercialization of Deployable Space Systems' roll-out solar array (ROSA) technology for Space Systems Loral (SSL) solar arrays," in 2016 IEEE Aerospace Conf., 2016, pp. 1-12.
[6] Wen, M., M. Yu, J. Fu, and Z. Wu, "Multi-functional hinge equipped with a magneto-rheological rotary damper for solar array deployment system," in Ninth Int. Symp. on Precision Eng. Measurement and Instrumentation, 2015, p. 944648.
[7] Renshall, J. and G. Marks, "The AstroEdge solar array for the NASA Small Spacecraft Technology Initiative" Clark" satellite," in Conference Record of the 25thIEEE Photovoltaic Specialists Conf.-1996, 1996, pp. 271-276.
[8] Zuckermandel, J., S. Enger, and N. Gupta, "Design, build, and testing of TacSat thin film solar arrays," in 4thInt. Energy Conversion Eng. Conf. and Exhibit (IECEC), 2006, p. 4198.
[9] Mallikarachchi, H. and S. Pellegrino, "Deployment dynamics of ultrathin composite boomswith tape-spring hinges," J. of Spacecraft and Rockets, vol. 51, pp. 604-613, 2014.
[10]         Kalman, A.E., "Solar Panel Hinge Release Mechanism," ed: Google Patents, 2018.
[11]         Spence, B.R. and S.F. White, "Hinge and lock mechanism for roll-out solar array," ed: US Patent App. 15/082,058, 2019.
[12] Xilun,              D., L. Xin, X. Kun, Y. Qiaolong, and P. Hailing, "Study on the behavior of solar array deployment with root hinge drive assembly," Chinese J. of Aeronautics, vol. 25, pp. 276-284, 2012.
[13]         Li, H., L. Duan, X. Liu, and G. Cai, "Deployment and control of cable-driven flexible solar arrays," Aircraft Eng. and Aerospace Tech., vol. 89, pp. 835-844, 2017.
[14]         Yan, Z., H. Shang, G. Zhao, Q. Yang, J. Ma, and J. Wang, "The Synchronization Mechanism for Solar Array with a Three-Stage Deployment," in 44thAerospace Mechanisms Symp., 2018, p. 431.
[15]         Alomar, W., J. Degnan, S. Mancewicz, M. Sidley, J. Cutler, and B. Gilchrist, "An extendable solar array integrated Yagi-Uda UHF antenna for CubeSat platforms,"IEEE Int. Symp. on Antennas and Propagation, 2011, pp. 3022-3024.
[16]         Santoni, F., F. Piergentili, S. Donati, M. Perelli, A. Negri, and M. Marino, "An innovative deployable solar panel system for Cubesats," Acta Astronautica, vol. 95, pp. 210-217, 2014.
[17]         Senatore, P., A. Klesh, T. H. Zurbuchen, D. McKague, and J. Cutler, "Concept, design, and prototyping of XSAS: A high power extendable solar array for CubeSat applications," 2010.
[18] Kwak,              M.K., S. Heo, and H. B. Kim, "Dynamics of satellite with deployable rigid solar arrays," Multibody System Dynamics, vol. 20, pp. 271-286, 2008.
[19]         Fufa, B.,C. Zhao-Bo, and M. Wensheng, "Modeling and simulation of satellite solar panel deployment and locking," Information Tech. J., vol. 9, pp. 600-604, 2010.
[20]         Li, Y., C. Wang, and W. Huang, "Dynamics analysis of planar rigid-flexible coupling deployable solar array system with multiple revolute clearance joints," Mechanical Systems and Signal Proc., vol. 117, pp. 188-209, 2019.
[21] Kim, K.-W. and Y. Park, "Solar array deployment analysis considering path-dependent behavior of a tape spring hinge," J. of Mechanical Science and Tech., vol. 29, pp. 1921-1929, 2015.
[22] Guo, S.-J., H.-Q. Li, and G.-P. Cai, "Deployment Dynamics of a Large-Scale Flexible Solar Array System on the Ground," The J. of the Astronautical Sci., vol. 66, pp. 225-246, 2019.
[23] Jones, P. A. and B. R. Spence, "Spacecraft solar array technology trends,"IEEE Aerospace and Electronic Sys. Magazine, vol. 26, pp. 17-28, 2011.
[24] Shapiro, W., F. Murray, R. Howarth, and R. Fusaro, "Space mechanisms lessons learned study. Volume 2: Literature review," 1995.
[25] Nagaraj, B., B. Nataraju, and A. Ghosal, "Dynamics ofa two-link flexible system undergoing locking: mathematical modelling and comparison with experiments," J. of sound and vibration, vol. 207, pp. 567-589, 1997.
[26] Chen, F., G. Zhao, Y. Yu, J. Wang, and P. Cao, "Modelica-based modeling and simulationof satellite On-orbit deployment and attitude control," in 2016 4th International Conference on Machinery, Materials and Information Technology Applications, 2017.
[27] Narayana, B., L.B. Nagaraj, and B. Nataraju, "Deployment dynamics of solar array withbody rates," in Materials of int. ADAMS user conf., 2000.
[28] Kuang, J., P.A. Meehan, A. Leung, and S. Tan, "Nonlinear dynamics of a satellite with deployable solar panel arrays," Int. J. of Nonlinear Mechanics, vol. 39, pp. 1161-1179, 2004.
[29] Gao, E.-w., X.-p. Zhang, and Z.-q. Yao, "Simulation and analysis of flexible solar panels’ deployment and locking processes," J. of Shanghai Jiaotong University (Science), vol. 13, pp. 275-279, 2008.