آرام سازی سرعت زاویه ای ماهواره با عملگر مغناطیسی در بستر سخت‌افزار و نرم افزار در حلقه

نوع مقاله: مقالة‌ تحقیقی‌ (پژوهشی‌)

نویسندگان

1 دانشکده فنی مشهد، دانشگاه فنی خراسان رضوی

2 دانشگاه علم و صنعت

3 پژوهشکده سامانه های ماهواره، پژوهشگاه فضایی ایران

چکیده

در این مقاله، مود آرام‌سازی سه‌محوره سرعت زاویه‌ای یک ماهواره در بستر نرم‌افزار و سخت‌افزار در حلقه، با عملگر مغناطیسی طراحی و پیاده‌سازی شده است. در این راستا، مدل میدان مغناطیسی توسط سیم‌پیچ هلمهولتز ایجاد شده و ماهواره با جانمایی روی میز سه‌درجه آزادی، در میدان مغناطیسی معادل موقعیت مداری قرار می‌گیرد. الگوریتم کنترلی که بر روی برد پردازشی پیاده‌‌سازی شده، با اندازه‌گیری میدان مغناطیسی و تغییرات آن، اقدام به تحریک عملگرهای مغناطیسی نموده، از تعامل دو میدان مدار و میدان تولیدی عملگر، نهایتاً گشتاور ترمزی ایجاد شده و سرعت زاویه‌ای مستهلک می‌شود. ملاحظات و محدودیت‌های عملی ویژه‌ای، از جمله عدم‌همزمانی کارکرد عملگر و حسگر مغناطیسی، غلبه گشتاور تولیدی بر اصطکاک میز و اندازه سرعت زاویه‌ای اولیه در پیاده‌سازی مورد توجه بوده که در نرم‌افزار درحلقه نیز لحاظ شده است. با شناسایی مدل اغتشاشی میز، نتایج نرم‌افزار و سخت‌افزار در حلقه با یکدیگر مقایسه شده که علاوه بر تطابق زیاد نتایج، نشانگر توانمندی این بستر در استهلاک سرعت زاویه‌ای است.

کلیدواژه‌ها


عنوان مقاله [English]

Damping mode of satellite angular velocity using magnetic actuators in hardware/software in the loop

نویسندگان [English]

  • Vahid Bohlouri 1
  • Hosein Haghighi 2
  • Soheil Seyedzamani 3
1 Technical and Vocational University
2 Iran university
3 Iranian Space Research Center
چکیده [English]

In this paper, damping mode of a satellite attitude control is designed and implemented using magnetic actuators in software /hardware-in-the-loop testbed. To do this, the equivalent of Earth’s magnetic field is designed using Helmholtz coil, frictionless is made by air-bearing, and algorithms are developed on designed control board. By measuring the Earth’s magnetic field, actuator commands are generated by the damping algorithm then braking torque is produced. Some applied restrictions and special requirements such as non-simultaneous operation between magnetic sensor and magnetic actuators, air-bearing friction, initial angular velocity are considered. By identifying the air-bearing frictional model, the results are compared in software/hardware-in-the-loop. The compared results show that the ability of the designed system to perform damping mode.

کلیدواژه‌ها [English]

  • Angular Velocity Damping
  • Satellite attitude control
  • Software/Hardware in the Loop
  • 3-Axis Air-bearing
  • Helmholtz coil
[1]    Fortescue, P. and Stark, J., Spacecraft system Engineering, John Wiley & Sons, 2003, pp. 299-319.

[2]    Wertz, J.R., Spacecraft Attitude Determination and Control, Kluwer, 1990, pp. 636-661.

[3]    Sidi, M.J. and Stengel, R.F., Spacecraft Dynamics and Control, Cambridge University Press, 1997, pp. 114-117.

[4]    Ley, W. and Wilfried, K., Handbook of space Technology, John Wiley & Sons, 2009, pp. 332-361.

[5]    Bryson, E., Control of Spacecraft and Aircraft, Princeton University Press, 1994, pp. 16-45.

[6]    Servidia, P.A. and Pena, R.S. Practical stabilization in attitude thruster control, IEEE Transactions on Aerospace and Electronic systems, Vol. 41, No. 2, 2005, pp. 584-598.

[7]    G. and L. S. Martins-Filho, Optimal on-off attitude control for the Brazilian multi mission Arantes platform satellite, Mathematical Problems in Engineering, Vol. 2009, No. 1, 2009, pp. 1- 17.

[8]    Avanzin, G. and Giulietti, F. Magnetic Detumbling of a Rigid Spacecraft, Guidanc, Control and Dynamic, Vol. 35, No. 14, 2012, pp. 1326-133.

[9]    Dee, S., Design of a Three-axis Stabilized ORION Satellite Using an All-Thruster Attitude Control System, Diss. Ph.D. Thesis,1988.

[10]  Magnetic, J.G., Development of an Active Magnetic Attitude Determination and Control System for Picosatellites on highly inclined circular Low Earth Orbits,Engineering and Technology Portfolio RMIT University, (Thesis for the degree M.S)., 2006, pp. 90-107,.

[11]  Martins-Filho, L.S., Santana, A.C., Adrielle, R.O. and Junior, G. A., Processor-in-the-Loop Simulations Applied to the Design And Evaluation of A Satellite Attitude Control." In Computational and Numerical Simulations. Intech Open, 2014.

[12]  Shishko, R. and Aster, R., NASA Systems Engineering Handbook, NASA Special Publication, 1995.

[13]  Tavakoli, A. Faghihinia, and Kalhor, A., An Innovative Test Bed for Verification of Attitude Control System, IEEE Aerospace and Electronic Systems Magazine, Vol. 32, No. 6, 2017, pp. 16-22,.

[14]  Mirshams, M. and et al., Using Air-Bearing Based Platform and Cold Gas Thruster Actuator for Satellite Attitude Dynamics Simulation, Modares Mechanical Engineering, Vol. 14, No. 12, 2015, pp. 1-12.

[15]  Theoret, N., Attitude Determination Control Testing System (Helmholtz Cage and Air Bearing), Honors Theses, Western Michigan University, 2016, pp. 13-55.

[16]  Ptak, and K. Foundy, Real-time spacecraft simulation and hardware-in-the-loop testing, in rtas, p. 230. IEEE, 1998.

[17]  Leitner, J., A Hardware-in-The-Loop Testbed for Spacecraft Formation Flying Applications. in Aerospace Conference, 2001, IEEE Proceedings. Vol. 2, pp. 2-615.

[18]  Wang, F., Xu, G.D., Geng, Y.H. and Cao, X.B., Hardware-in-the-loop Simulation of Satellite Attitude Control Based on Information Electronic System of Microkernel. Journal of System Simulation, Vol. 19, No. 5, pp.1131-1135, 2007.

[19]  Malekzadeh, M., Rezayati, M. and Saboohi, M., Hardware-in-the-loop attitude control via a high-order sliding mode controller/ observer, Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering Vol. 232, No. 10, pp.1944-1960, 2018.

[20]  Liu, X., Lu, Y., Zhou,Y. and Yin,Y., Prospects of Using A Permanent Magnetic End Effector to Despin And Detumble an Uncooperative Target. Advances in Space Research, Vol. 61, No. 8, 2018, pp.2147-2158.

[21]  Hurtado-Velasco, R. and Gonzalez-Llorente, J., Simulation of the Magnetic Field Generated Bysquare Shape Helmholtz Coils, Applied Mathematical Modelling, Vol. 40, No. 23-24, 2016, pp. 9835-9847.

[22]  Chesi, S., Perez, O. and Romano, M., A Dynamic, Hardware-in-the-Loop, Three-Axis Simulator of Spacecraft Attitude Maneuvering with Nanosatellite Dimensions, 2015.

[23]  Inumoh, L.O., Forshaw, J.L. and Horri, N.M., Tilted wheel satellite attitude control with air-bearing table experimental results,Acta Astronautica, Vol. 117, 2015, pp. 414-429.

[24]  JalaliNaini, S.H., Bohlouri, V., Quasi-Normalized Analysis of Satellite Stabilization with Pulse-Width Pulse-Frequency Modulator in Presence of Input Noise, Modares Mechanical Engineering, Vol. 18, No. 01, 2018, pp. 165-176 (in Persian).

[25]  Bellini, N., Magnetic Actuators For Nanosatellite Attitude Control, (PhD diss.), 2013.

[26]  Schwartz, J.L., Peck, M.A. and Hall, C.D., Historical Review of Air-Bearing Spacecraft Simulators, Journal of Guidance, Control, and Dynamics, Vol. 26, No. 4, 2003, pp.513-518.

[27]  Available, [On Line]: https://www.digi. com/ xbee

[28]  Available, [On Line]:http://www.ni.com/en-us.html