TY - GEN
T1 - Design, Test, And Verifiaction Of A Reaction Wheel For Cubesats
AU - Alkatheeri, Zayed
AU - Nabi, Abderrahim
AU - Darfilal, Djamal
AU - Fantino, Elena
AU - Swei, Sean
N1 - Publisher Copyright:
Copyright ©2024 by the International Astronautical Federation (IAF). All rights reserved.
PY - 2024
Y1 - 2024
N2 - Khalifa University’s initiatives in designing and constructing CubeSats for technology demonstration show a significant leap in advancing space capabilities. The ongoing project involves a 6U CubeSat destined for Low Earth Orbit (LEO) at YahSat space lab. This research primarily focuses on designing, testing, and developing a flight model reaction wheel for integration into the current 6U CubeSat mission at Khalifa University. The design phase involves careful analysis of key factors, such as flywheel design and motor selection from low-cost commercial of the shelf motors, with a primary focus on reducing the weight and size while maintaining optimal performance. Furthermore, a thorough modelling, simulation, and analysis of the reaction wheel are presented, using a Proportional Integral (PI) controller to illustrate the performance of the selected Brushless DC motor under flywheel loading conditions. The results showed that the reaction wheel performs within the expected behaviour proving the compatibility of the flywheel geometric properties at the operational speed and torque limits. Furthermore, the paper presents a block diagram of miniaturized flight model reaction wheel with a diameter of only 33mm and a total mass that does not exceed 38g, with a maximum torque of 0.5mNm and the ability to store angular momentum up to 1.32mNms. At the hardware level, the reaction wheel is integrated with a PI controller circuit, initially tuned using a trial-and-error method. Functional test results similar to the simulation study are illustrated to show the performance of the reaction wheel at different operational modes taking into account all physical factors including friction and vibrations. Finally, the characterization of micro vibrations induced by miniaturized reaction wheels is presented using a developed cost-effective test bed. The in-house development of the reaction wheel contributes to the space heritage of the United Arab Emirates in space systems technology.
AB - Khalifa University’s initiatives in designing and constructing CubeSats for technology demonstration show a significant leap in advancing space capabilities. The ongoing project involves a 6U CubeSat destined for Low Earth Orbit (LEO) at YahSat space lab. This research primarily focuses on designing, testing, and developing a flight model reaction wheel for integration into the current 6U CubeSat mission at Khalifa University. The design phase involves careful analysis of key factors, such as flywheel design and motor selection from low-cost commercial of the shelf motors, with a primary focus on reducing the weight and size while maintaining optimal performance. Furthermore, a thorough modelling, simulation, and analysis of the reaction wheel are presented, using a Proportional Integral (PI) controller to illustrate the performance of the selected Brushless DC motor under flywheel loading conditions. The results showed that the reaction wheel performs within the expected behaviour proving the compatibility of the flywheel geometric properties at the operational speed and torque limits. Furthermore, the paper presents a block diagram of miniaturized flight model reaction wheel with a diameter of only 33mm and a total mass that does not exceed 38g, with a maximum torque of 0.5mNm and the ability to store angular momentum up to 1.32mNms. At the hardware level, the reaction wheel is integrated with a PI controller circuit, initially tuned using a trial-and-error method. Functional test results similar to the simulation study are illustrated to show the performance of the reaction wheel at different operational modes taking into account all physical factors including friction and vibrations. Finally, the characterization of micro vibrations induced by miniaturized reaction wheels is presented using a developed cost-effective test bed. The in-house development of the reaction wheel contributes to the space heritage of the United Arab Emirates in space systems technology.
KW - ADCS
KW - CubeSat
KW - Flywheel
KW - Reaction wheel Design
KW - Satellite Attitude Control
UR - https://www.scopus.com/pages/publications/105033361511
U2 - 10.52202/078368-0088
DO - 10.52202/078368-0088
M3 - Conference contribution
AN - SCOPUS:105033361511
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 1043
EP - 1050
BT - IAF Human Spaceflight Symposium - Held at the 75th International Astronautical Congress, IAC 2024
PB - International Astronautical Federation, IAF
T2 - 2024 IAF Astrodynamics Symposium at the 75th International Astronautical Congress, IAC 2024
Y2 - 14 October 2024 through 18 October 2024
ER -