علوم و فناوری فضایی

علوم و فناوری فضایی

اصلاحی بر مدولاتور پهنا و فرکانس پالس انتگرالی

نوع مقاله : مقالة‌ پژوهشی‌

نویسندگان
1 دانشیار، دانشکده مهندسی مکانیک، دانشگاه تربیت مدرس، تهران، ایران
2 دانشجوی دکتری، دانشکده مهندسی مکانیک؛ دانشگاه تربیت مدرس؛ تهران؛ ایران
چکیده
این مقاله به اصلاح نوع خاصی از مدولاتور پهنا و فرکانس پالس با بلوک انتگرالگیر می‌پردازد. در این مدولاتور به جای فیلتر پایین گذر از یک انتگرالگیر استفاده شده، و به همین دلیل در اینجا مدولاتور پهنا و فرکانس پالس انتگرالی نامیده می‌شود. به منظور بهبود رفتار حلقه کنترلی، ساختار مدولاتور با یک شرط منطقی برای بازتنظیم خروجی انتگرالگیر اصلاح شده است. در این شرط منطقی، در صورتی که سیگنال خطا کوچکتر از بازة مشخصی باشد، خروجی انتگرالگیر صفر می‌گردد. این بهبود در دو مود پایدارساز و نشانه‌روی اعمال شده است. در مود پایدارساز، ضریب بهرة پایدارساز با استفاده از حل تحلیلی به گونه‌ای استخراج شده است تا با یک پالس، کسر معینی از سرعت زاویه‌ای اولیه مستهلک گردد. در مود نشانه‌روی، عملکرد مدولاتور اصلاح شده، قابل مقایسه با مدولاتور پهنا و فرکانس پالس می‌باشد.
کلیدواژه‌ها
موضوعات

[1]    Markley, F. L., Funamentals of Spacecraft Attitude Determination and Control, Springer Press, 2014.
[2]    Lay, W. and Wittmann, K, Handbook of Space Technology, John Wiley & Sons, Ltd, 2009.
[3]    Arefkhani, H., Mehdi-abadi, M., and Dehghan, S.M.M.,  “Satellite Spin Stabilization by Magnetic Torquers and Validation with Air-Bearing Simulator,” Journal of space science & Technology (JSST), Vol. 9, No. 2, 2016, pp. 25-34 (in Persian).
[4]   Navabi, M., Tavana, M., and Mirzayi, H.R., “Attitude Control of Spacecraft by State Dependent Riccati Equation and Power Series Expansion of Riccati Methods,” Journal of space science & Technology, (JSST), Vol. 7, No. 4, 2015, pp. 39-49 (in Persian).
[5]   Maani, E., Pishkenari, H.N., and Kosari, A.R,  “Satellite 3-Axis Attitude Control Using the Combination of Reaction Wheels and Thrusters,” Journal of space science & Technology, (JSST), Vol. 1, No. 1, 2019, pp. 63-71 (in Persian).
[6]   Werts, R., Spacecraft Attitude Determination and Control, Kluwer Academic  Publisher, 1978.
[7]   Santana, C. and Martin, L. S, “Attitude Stablization of the PMM Satellite Using a LQG-Based Control Strategy,” Trends in Applied and Computational Mathematics,Vol. 9, No. 2, 2008, pp. 321-330.
[8]   Webster, E. S, “Active Nutation Control for Spinning Solid Motor  Upper Stage,” McDonnel Doglas Astronautics Company, Presented In AIAA, 1985.
[9]   Johnson, G. B., “Nutation Correction System For Spin-Stablized Satellite,” United States Patent,1968.
[10]   Lian, Y. and Tang, G., “Libration Point Orbit Rendezvous Using PWPF Modulated Terminal Sliding Mode Control,” Advances in Space Research, Vol. 52, No. 12, pp. 2156-2167, 2013.
[11]   Lebedev, D. V, and Tkachenco, A. I, “High-Precision Attitude Control of Remote Sensing Sattelite,” IFAC Automatic Control in Aerospace, Russia, 2004.
[12]   Diedrich, B., Attitude Control and Dynamic of Sollar Sails, MS Thesis, University of Washington, 2001.
[13]   Silik, Y. and Yaman, U., “Single Axis Attitude Controller Design Using Pulse Width Modulated Thruster,” 20th Inernational Conference on Research and Education in Mechatronics(REM), 2019.
[14]   Delavault, S., and Prieur, P., “Drag-Free and Attitude Control System in LEO Using Cold Gas Propulsion System,” 18th Australian International Aerospace Congree, Australia, 2019.
[15]   Bryson, A. E, Control of Spacecraft and Aircraft, 1st Ed., Prinston University Press, 1994.
[16]   Brown, C. D., Elements of Spacecraft Design, AIAA, Reston, Virginia, 2002.
[17]   Nicklas, J. C., “Derived-Rate Increment Stablization: Its Application to the Attitude Control Problem” Transaction of the ASME, Vol. 84, 1962.
[18]  Sidi, M. J., Spacecraft Dynamic and Control, Cambridge University Press, 1997.
[19]   Navabi, M., and Rangraz, H., “Comparing optimum operation of pulse width-pulse frequency and pseudo-rate modulators in spacecraft attitude control subsystem employing thruster,” Proceeding of 6th international conference on recent advances in space technologies, IEEE, 2013, pp. 625-630.
[20]   Feron, E., “Pulse Modulation,” Lecture Note, MIT University.
[21]   Buck, N.V., “Minimum Vibration Maneuvers Using Input Shaping and Pulse-Width Pulse-Frequency Modulated Thruster Control,” Naval Postgraduate School, Monterey, CA, 1996.
[22]  Song, G., Buck, N.V. and Agrawal, B.N., “Spacecraft Vibration Reduction Using Pulse-Width Pulse-Frequency Modulated Input Shaper”, Journal of Guidance, Control and Dynamics, Vol. 22, 1999, pp.433-440.
[23]  Song, G. and Agrawal, B., “Vibration Suppression of Flexible Spacecraft During Attitude Control,” Acta Astronautica, Vol. 49, No. 2, 2001, pp. 73-83.
[24]  Krovel, T. D., Optimal Tuning of PWPF Modulator for Attitude Control, MS Thesis, Norwegian University of Science and Technology, Trondheim, 2005.
[25]  Jalali-Naini, S. H., “Normalizing the Single-Axis Spacecraft Attitude Control Equations with Pulse-Width Pulse-Frequency Modulator,” the 13th Conference of Iranian Aerospace Society, 2014 (in Persian).
[26]  Jalali-Naini, S. H. and Ahmadi Darani, Sh., “Preliminary Design of  Spacecraft Attitude Control with Pulse-Width Pulse-Frequency Modulator for Rest-to-Rest Maneuver,” Journal of Aerospace Science and Technology, Iranian Aerospace Society, Vol. 11, No. 1, 2017, pp. 1-8.
[27]  Jalali-Naini, S. H. and Bohlouri, V., “Quazi-Normalized Static and Dynamic Analysis of Pulse-Width Pulse-Frequency Modulator in Presence of Input Noise,” Modares Mechanical Engineering, Vol. 16, No. 12, 2016, pp. 455-466 (in Persian).
[28]  Jalali-Naini S. H. and Bohlouri, V., “Quazi-Normalized Analysis of Satellite Stablization with Pulse-Width Pulse-Frequency Modulator in Presence of Input Noise,” Modares Mechanical Engineering, Vol. 18, No. 01, 2018, pp. 165-176 (in Persian).
[29]  Jalali-Naini, S. H., “Static Analysis of Pulse-Width Pulse-Frequency Modulator Based on Analytical and Numerical Solutions,” Journal of Aerospace Science and Technology, Vol. 11, No. 1, 2018, pp. 13-29 (in Persian).
[30]  Kunkle, J. L., “The Agena Pneumatic System-control Gas Requirements Stability and Response,” LXSC/A313082, Lockheed Missiles and Space Corporation, Sunnyvale, Calif.
[31]  Anthony, T. C. and Wie, B., “Pulse-Modulated Control Synthesis for a Flexible Spacecraft,” Journal of Guidance, Control, and Dynamics, Vol. 13, No. 6, 1990, pp. 1014-1022.

  • تاریخ دریافت 11 شهریور 1398
  • تاریخ بازنگری 12 بهمن 1398
  • تاریخ پذیرش 15 اردیبهشت 1399
  • تاریخ اولین انتشار 01 فروردین 1400