Prototype of Micro Reaction Wheel for Cubesat

Manggala, Fhadli Hudaya; Ramadhan, Rizki Pratama; Wijanto, Heroe; Mayditia, Hasan; Edwar, Edwar; Vidyaningtyas, Hurianti

doi:10.1109/tssa48701.2019.8985474

Cited by 5 publications

(2 citation statements)

References 7 publications

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“…In recent years, CubeSat missions have gained increasing popularity due to their cost effectiveness, rapid development cycles, and adaptability for various space applications. The attitude determination and control system (ADCS) play a crucial role in CubeSat missions by ensuring precise control of the satellite's orientation and stability [1]- [4]. However, designing and implementing a cost-effective and efficient ADCS for small satellite applications remains a challenge.…”

Section: Introductionmentioning

confidence: 99%

Innovative design and development of attitude determination and control systems for CubeSats with reaction wheels

Harsha S.,

Thentral T. M.,

Ramasamy

et al. 2024

IJEECS

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Attitude determination and control systems (ADCS) represent a critical facet of CubeSat missions, orchestrating the precise orientation and stabilization of these small satellites in the space environment. This paper presents a comprehensive design and development of an ADCS tailored for CubeSats, harnessing a reaction wheel system to deliver a cost-effective and dependable solution for small satellite applications. The research begins by elucidating the requisites and specifications for the ADCS and then delves into the design phase, complemented by intricate modelling and simulation employing MATLAB Simulink and the Webots Simulator. The results of this study underscore the exceptional performance of the proposed ADCS configuration, leveraging the reaction wheel model. This system demonstrates an unparalleled capacity to achieve precise and controlled attitude adjustments, well within the defined parameters. Furthermore, this research underscores the pivotal role played by efficient system design, meticulous simulation, and rigorous testing in the triumphant implementation of ADCS, greatly enhancing CubeSat missions and their contributions to the realm of space exploration and technology innovation. This comprehensive approach to the design and testing of an ADCS for CubeSats ensures that these diminutive satellites continue to make significant strides in space missions, paving the way for an exciting future of space research and technology development.

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Section: Introductionmentioning

confidence: 99%

Innovative design and development of attitude determination and control systems for CubeSats with reaction wheels

Harsha S.,

Thentral T. M.,

Ramasamy

et al. 2024

IJEECS

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“…They selected a solid disc and arranged four RWs in a tetrahedral configuration to retain threeaxis control if one RW fails. Manggala et al [5] designed a micro reaction wheel for a 1U CubeSat that consists of a bowlshaped flywheel that fits the motor in its cavity. Munter et al [6] present a flywheel design for CubeSats that uses a thin inner disc and thicker outer ring, similar in design to Oland and Schlanbusch [3], except that the two cavities on either side of the thin inner disc are not symmetric.…”

Section: Introductionmentioning

confidence: 99%

Multi-Shaft Reaction Wheel Design For A 2U Cubesat

Popp¹,

Krishnan²,

Vautour³

et al. 2021

Progress in Canadian Mechanical Engineering. Volume 4

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In this paper, a reaction wheel design is presented and proposed for use in Dalhousie University's Low Earth Orbit Reconnaissance Imagery Satellite (LORIS) 2U CubeSat. After estimating a cumulative maximum disturbance torque of 7.16 × 10 -7 Nm in low Earth orbit, a flywheel design was developed with a momentum storage of 1.01 × 10 -2 Nms. The authors propose to machine the flywheel in a skate-wheel shape to provide a large inertia-to-mass ratio compared to solidcylindrical designs. A novel three-shaft system is employed wherein a Brushless DC motor shaft is rigidly connected to a spline-toothed inner shaft which transmits power to an outer shaft rigidly fixed to the flywheel. The inner shaft provides torsional flexibility to the system and ultimately reduces the transfer of vibration due to shaft misalignments. Splines and back-to-back angular contact bearings accommodate axial and radial misalignments between the inner and outer shaft experienced during mounting and operation. Finite element analysis was employed to validate the design across worst-case loading scenarios including rocket launch and misaligned inner and outer shafts.

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