Khalil ULLAH, Anwar ALI, Zeeshan MUKHTAR, Leonardo REYNERI

Design and comparison of embedded air coils for small satellites

The paper discusses the comparison of different shapes of embedded air coils for the attitude control ofsmall satellites. Various systems are available in the market for the attitude control of small satellites such as reactionwheels, permanent magnets, magnetic rods, and thrusters. The available systems have large size, heavier weight, andrelatively higher power consumption. A miniaturized system with less power consumption and heat dissipation is requiredthat can provide the anticipated torque. This paper focuses on the design and comparison of square and circular aircoils embedded in four internal layers (i.e. 2nd, 3rd, 4th, and 5th) of the eight layer CubeSat power management tile(CubePMT) PCB. Each layer has 50 turns of copper traces and four layers have a total of 200 turns. The four embeddedcoils are reconfigurable and can be connected in different configurations (single, series, parallel, and hybrid) throughswitches. The two shapes are compared on the basis of dipole moment, torque generated, power dissipated, time ofrotation, and thermal heat generation.

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[1] Puig-Suari J, Turner C, Ahlgren W. Development of the standard CubeSat deployer and a CubeSat class PicoSatellite. 2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542), Big Sky, MT, 2001, pp. 1/347-1/353 vol. 1.
[2] Alminde L, Bisgaard M, Vinther D, Viscor T, Ostergard K. Educational value and lessons learned from the AAUCubeSat project. Proceedings of International Conference on Recent Advances in Space Technologies, 2003. RAST ’03, Istanbul, Turkey, 2003, pp. 57-62.
[3] Hu Y, Wang D, Liu C. Reconfigurability research of satellite attitude control system under reliability constraints. Proceedings of the 33rd Chinese Control Conference, Nanjing, 2014, pp. 3244-3248.
[4] Shams N, Tanveer F, Ahmad S. Design and development of attitude control system (ACS) using COTS based components for small satellites. 2008 2nd International Conference on Advances in Space Technologies, Islamabad, 2008, pp. 6-11.
[5] Russell B, Clement L, Hernandez J, Byagowi A, Schor D, Kinsner W. Implementation of a nanosatellite attitude determination and control system for the T-Sat1 mission. 2013 26th IEEE Canadian Conference on Electrical and Computer Engineering (CCECE), Regina, SK, 2013, pp. 1-5.
[6] Mukhtar Z, Ali A, Mughal R, Reyneri L. Design and comparison of different shapes embedded magnetorquer coils for CubeSat standard nanosatellites. 2016 International Conference on Computing, Electronic and Electrical Engineering (ICE Cube), Quetta, Pakistan, 2016, pp. 175-180.
[7] Ali A, Mughal R, Ali H, Reyneri L, Aman N. Design, implementation, and thermal modeling of embedded reconfigurable magnetorquer system for nanosatellites. IEEE T Aero Elec Sys 2015; 51: 2669-2679.
[8] Rehman S, Marchand R, Berthelier J, Onishi T, Burchill J. Earth magnetic field effects on particle sensors on LEO satellites. IEEE T Plasma Sci 2013; 41: 3402-3409.
[9] Bakshi UA, Bakshi MV. Electromechanical Energy Conversion & D.C. Machines. First edition. Pune, India: Technical Publications, 2009.
[10] Howell JR, Meng¨u¸c MP, Siegel R. Thermal Radiation Heat Transfer, 6th edition. Boca Raton, FL, USA: CRC Press, 2015.
[11] Chen Z. Integrated electrical and thermal modeling, analysis and design for IPEM. PhD, Virginia Polytechnic Institute and State University, Blacksburg, VA, USA, 2004.