Attitude determination and control system of the uruguayan cubesat, AntelSat

Tassano, Matias; Monzón, Pablo; Pechiar, Juan

doi:10.1109/icar.2013.6766523

Cited by 4 publications

(2 citation statements)

References 12 publications

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“…1, April 2024: 109-118 110 introduces a reaction wheel system with momentum storage of 30 mNms and a torque of 2.5 mNm, designed for small satellites weighing between 5 kg to 20 kg. Test bench for nanosatellite attitude determination and control system ground tests [8] proposes a three-degree-of-freedom (3DOF) test bench for CubeSats, providing a reliable platform for ground-based ADCS testing without motion interference. Prototype of micro reaction wheel for CubeSat [9] describes the design and validation of micro reaction wheels used in Tel-USat CubeSat, capable of generating 0.74 mNm of torque [10].…”

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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“…CubeSats are considered extraordinary satellites innovation in the astronautics field due to their light weight, short advancement cycle, low improvement cost, high functional density, and adaptable outflow attributes. These CubeSats are described as a class of nanosatellites ranging from 10 × 10 × 10 cm 3 and upwards in 10‐cm increments of length …”

Section: Introductionmentioning

confidence: 99%

High‐precision attitude determination and control system design and real‐time verification for CubeSats

Gaber

Mashade

Aziz

2020

Int J Communication

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This paper presents the design and real-time verification of a high-precision and low-cost attitude determination and control system (ADCS) for CubeSat based on a micro-electro-mechanical (MEMS) gyroscope. The CubeSat new missions require accurate and sophisticated ADCS with attitude drift adjustment. Moreover, designing an effective ADCS for the CubeSat poses a difficult challenge. The satellite comprises of a two-unit CubeSat, which denotes that the ADCS is designed with small size, tight mass, and energy limitations. The ADCS has been enhanced in the former few years from fairly small resolution of 10 to around 0.6 m. This attitude drift, if not properly compensated, will cause a slow attitude information loss as the error in attitude rises between the actual and estimated. To correct the attitude adrift, the proposed system utilizes a MEMS gyroscope sensor which offers a comparative attitude to the Kalman filter for estimated attitude update. Real-time verification and validation for the ADCS are performed through Matlab/Simulink environment and lab testing to prove the efficacy of the proposed system. Simulation of the ADCS shows accurate results with error of no more than 1 . K E Y W O R D Sattitude determination, CubeSat, gyroscope, MEMS ADCS computer that holds the whole algorithms and the control schemes of the ADCS. The resolution of the ADCS is increased to around 0.6 m in the former 10 years. 6 The CubeSat U-class spacecraft 7 belongs to a category of reduced satellites that is mainly used in research and comprises several numbers of cubic elements. Moreover, the single largest step in reducing software cost is the usage of commercial, off-the-shelf (COTS) software. 8 This is analogous for the adoption of COTS microelectronics in space application. The CubeSats usually employ COTS in their structure: electronics design, and weights around 1.3 kg/unit. 9 For the control of the CubeSat, there are three phases after launch: de-tumbling, initial attitude determination (AD), and recursive AD. As the most prevalently used algorithms in satellite de-tumbling process, B-Dot controller controls the satellite by aligning it with the earth magnetic field vectors. Indeed, all small satellites used some variation of B-Dot as the controller for de-tumbling process. [10][11][12] As for preliminary AD, TRIAD method is one of the initial and simplest solutions to the spacecraft AD problem. This technique entails two sets of vectors: an observation vector from magnetometer and sun sensors, and a vector command for each observation according to its inertial reference frame. In 1977, Davenport presented the first successful application of Wahba's problem to spacecraft AD (as reported by Keat 13 ) using the quaternion parameterization of the direction cosine matrix (DCM) with the q-method algorithm. In 1979 (as reported by Shuster and Oh 14 ), the QUaternion estimator (QUEST) algorithm appeared as an alternative to the q-method. Although less robust than the qmethod, QUEST is the most used algorithm for Wahba's problem. 1...

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Attitude Determination and Control System for Nadir Pointing and Detumbling Using Magnetorquer for 1U Bolivian Cubesat

Ticona¹,

Rojas²,

Vidaurre³

et al. 2022

2022 International Conference on Control, Robotics and Informatics (ICCRI)

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Attitude determination and control system of the uruguayan cubesat, AntelSat

Cited by 4 publications

References 12 publications

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

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

High‐precision attitude determination and control system design and real‐time verification for CubeSats

Attitude Determination and Control System for Nadir Pointing and Detumbling Using Magnetorquer for 1U Bolivian Cubesat

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