Design and implementation of a reaction wheel system for CubeSats

N. Sai Krishna, Sushmita Gosavi, Shivika Singh, Naman Saxena, Anirudh Kailaje, Vishwanath Datla, Paras Shah

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper describes the dynamics and control of a reaction wheel system for three axis control of a nano-satellite. The dynamics equations governing the reaction wheel system, the controller-reaction wheel interface and the motor control mechanism have been elaborated. The Controller-Reaction wheel interface which includes speed control of the motor of the reaction wheel system from the obtained torques has been described. Due to the presence of continuous disturbance torques in space the reaction wheels will saturate after a certain period, the momentum must be unloaded from the reaction wheels to use them again for attitude control. The results of a momentum dumping strategy using three magnetorquers have been discussed. The speed control system for the motor and the momentum dumping strategy have been tested using a SIL (Software-In-the-Loop) system and all the relevant results have been shown. The BLDC motor used requires a three phase supply. Since the on-board battery provides a DC voltage, power electronic circuits are used to convert this DC to a 3 phase AC using SVPWM method. SVPWM is used to reduce any possible vibrations in the motor due to supply harmonics. The rotor position and speed is determined by both hall effect sensors and the back emf measurements. Since the motor is a slow responding device with a large mechanical time constant, a PID controller is used to speed up any transitions in the rotor speed. The design of this controller has been discussed in detail.

Original languageEnglish
Title of host publication2018 IEEE Aerospace Conference, AERO 2018
PublisherIEEE Computer Society
Pages1-7
Number of pages7
Volume2018-March
ISBN (Electronic)9781538620144
DOIs
Publication statusPublished - 25-06-2018
Externally publishedYes
Event2018 IEEE Aerospace Conference, AERO 2018 - Big Sky, United States
Duration: 03-03-201810-03-2018

Conference

Conference2018 IEEE Aerospace Conference, AERO 2018
CountryUnited States
CityBig Sky
Period03-03-1810-03-18

Fingerprint

reaction wheels
Wheels
momentum
controllers
torque
dumping
speed control
Momentum
Controllers
Speed control
Torque
Rotors
direct current
rotor speed
control system
attitude control
vibration
Attitude control
Hall effect
Electric potential

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

Krishna, N. S., Gosavi, S., Singh, S., Saxena, N., Kailaje, A., Datla, V., & Shah, P. (2018). Design and implementation of a reaction wheel system for CubeSats. In 2018 IEEE Aerospace Conference, AERO 2018 (Vol. 2018-March, pp. 1-7). IEEE Computer Society. https://doi.org/10.1109/AERO.2018.8396584
Krishna, N. Sai ; Gosavi, Sushmita ; Singh, Shivika ; Saxena, Naman ; Kailaje, Anirudh ; Datla, Vishwanath ; Shah, Paras. / Design and implementation of a reaction wheel system for CubeSats. 2018 IEEE Aerospace Conference, AERO 2018. Vol. 2018-March IEEE Computer Society, 2018. pp. 1-7
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abstract = "This paper describes the dynamics and control of a reaction wheel system for three axis control of a nano-satellite. The dynamics equations governing the reaction wheel system, the controller-reaction wheel interface and the motor control mechanism have been elaborated. The Controller-Reaction wheel interface which includes speed control of the motor of the reaction wheel system from the obtained torques has been described. Due to the presence of continuous disturbance torques in space the reaction wheels will saturate after a certain period, the momentum must be unloaded from the reaction wheels to use them again for attitude control. The results of a momentum dumping strategy using three magnetorquers have been discussed. The speed control system for the motor and the momentum dumping strategy have been tested using a SIL (Software-In-the-Loop) system and all the relevant results have been shown. The BLDC motor used requires a three phase supply. Since the on-board battery provides a DC voltage, power electronic circuits are used to convert this DC to a 3 phase AC using SVPWM method. SVPWM is used to reduce any possible vibrations in the motor due to supply harmonics. The rotor position and speed is determined by both hall effect sensors and the back emf measurements. Since the motor is a slow responding device with a large mechanical time constant, a PID controller is used to speed up any transitions in the rotor speed. The design of this controller has been discussed in detail.",
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Krishna, NS, Gosavi, S, Singh, S, Saxena, N, Kailaje, A, Datla, V & Shah, P 2018, Design and implementation of a reaction wheel system for CubeSats. in 2018 IEEE Aerospace Conference, AERO 2018. vol. 2018-March, IEEE Computer Society, pp. 1-7, 2018 IEEE Aerospace Conference, AERO 2018, Big Sky, United States, 03-03-18. https://doi.org/10.1109/AERO.2018.8396584

Design and implementation of a reaction wheel system for CubeSats. / Krishna, N. Sai; Gosavi, Sushmita; Singh, Shivika; Saxena, Naman; Kailaje, Anirudh; Datla, Vishwanath; Shah, Paras.

2018 IEEE Aerospace Conference, AERO 2018. Vol. 2018-March IEEE Computer Society, 2018. p. 1-7.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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Krishna NS, Gosavi S, Singh S, Saxena N, Kailaje A, Datla V et al. Design and implementation of a reaction wheel system for CubeSats. In 2018 IEEE Aerospace Conference, AERO 2018. Vol. 2018-March. IEEE Computer Society. 2018. p. 1-7 https://doi.org/10.1109/AERO.2018.8396584