In-Orbit Attitude Determination of the UVSQ-SAT CubeSat Using TRIAD and MEKF Methods

Finance, Adrien; Dufour, Christophe; Boutéraon, Thomas; Sarkissian, Alain; Mangin, Antoine; Keckhut, Philippe; Meftah, Mustapha

doi:10.3390/s21217361

Cited by 8 publications

(4 citation statements)

References 30 publications

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“…The results are consistent with the error analyses shown in Figure 13 . In the dawn-dusk orbit, IPSS together with a COTS magnetometer can achieve an average attitude determination accuracy of 0.32

after filtering (such as a gyro-free MEKF filter [ 19 ]). As is shown in Figure 17 b, the mean sun vector inversion error in the 12:00 orbit is 3.12

.…”

Section: Experimental Results and On-orbit Performancementioning

confidence: 99%

Design and Verification of an Integrated Panoramic Sun Sensor atop a Small Spherical Satellite

Zhang

2022

Sensors

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This paper proposes an integrated panoramic sun sensor (IPSS) for the small spherical satellite Q-SAT that has been working in orbit since 2020. IPSS is essentially a set of temperature-compensated photoelectric cells distributed on the spherical surface of Q-SAT. Compared with traditional sun sensors, IPSS has full spherical coverage of 4π so that the sun vector from any direction can be inversed. The mechatronic design and mathematical model of the proposed IPSS are presented. In-depth error analyses in terms of albedo effect, sampling error, parameter deviation, etc. are carried out. IPSS can provide a sun vector inversion accuracy of 1.5∘ where albedo disturbance does not dominate. Simulation results show that the measurement of IPSS together with a COTS magnetometer can support the three-axis attitude determination of satellites in various orbits and can adapt to the seasonal variations of subpolar points. Ground experimental results and on-orbit data have also verified the feasibility and performance of IPSS. Although the panoramic sun sensor is designed for the small spherical Q-SAT, it can also be applied to other satellites with limited power budgets.

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after filtering (such as a gyro-free MEKF filter [ 19 ]). As is shown in Figure 17 b, the mean sun vector inversion error in the 12:00 orbit is 3.12

.…”

Section: Experimental Results and On-orbit Performancementioning

confidence: 99%

Design and Verification of an Integrated Panoramic Sun Sensor atop a Small Spherical Satellite

Zhang

2022

Sensors

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“…OSR and OLR time series are derived from the measurements made by the various sensors on board the CubeSat and from in-orbit attitude knowledge. New methods were developed to obtain UVSQ-SAT in-orbit attitude knowledge using Tri-Axial Attitude Determination (TRIAD) and Multiplicative Extended Kalman Filter (MEKF) methods [16]. The different inputs available to the algorithms are three-axis angular velocities (UVSQ-SAT gyrometer), six-axis solar direction (UVSQ-SAT photodiodes in the visible domain), and three-axis magnetic field (UVSQ-SAT magnetometer).…”

Section: Uvsq-sat Cubesat Observations Inmentioning

confidence: 99%

“…To solve this issue, we developed new methods (Tri-Axial Attitude Determination (TRIAD), Multiplicative Extended Kalman Filter (MEKF)) to have a knowledge of the satellite attitude. These methods were validated with UVSQ-SAT data in orbit [16], and represent an important issue for the INSPIRE-SAT 7 scientific analysis.…”

mentioning

confidence: 99%

INSPIRE-SAT 7, a Second CubeSat to Measure the Earth’s Energy Budget and to Probe the Ionosphere

et al. 2022

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INSPIRE-SAT 7 is a French 2-Unit CubeSat (11.5 × 11.5 × 22.7 cm) primarily designed for Earth and Sun observation. INSPIRE-SAT 7 is one of the missions of the International Satellite Program in Research and Education (INSPIRE). Twice the size of a 4 × 4 Rubik’s Cube and weighing about 3 kg, INSPIRE-SAT 7 will be deployed in Low Earth Orbit (LEO) in 2023 to join its sister satellite, UVSQ-SAT. INSPIRE-SAT 7 represents one of the in-orbit demonstrators needed to test how two Earth observation CubeSats in orbit can be utilized to set up a satellite constellation. This new scientific and technological pathfinder CubeSat mission (INSPIRE-SAT 7) uses a multitude of miniaturized sensors on all sides of the CubeSat to measure the Earth’s energy budget components at the top-of-the-atmosphere for climate change studies. INSPIRE-SAT 7 contains also a High-Frequency (HF) payload that will receive HF signals from a ground-based HF transmitter to probe the ionosphere for space weather studies. Finally, this CubeSat is equipped with several technological demonstrators (total solar irradiance sensors, UV sensors to measure solar spectral irradiance, a new Light Fidelity (Li-Fi) wireless communication system, a new versatile telecommunication system suitable for CubeSat). After introducing the objectives of the INSPIRE-SAT 7 mission, we present the satellite definition and the mission concept of operations. We also briefly show the observations made by the UVSQ-SAT CubeSat, and assess how two CubeSats in orbit could improve the information content of their Earth’s energy budget measurements. We conclude by reporting on the potential of future missions enabled by CubeSat constellations.

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“…The technology used in the development of CubeSat orientation sensors includes solar and magnetic sensors [ 1 , 2 ]. This information is necessary for spacecraft orientation [ 3 , 4 ], control, and collecting accurate scientific data [ 5 ]. The purpose of the solar sensor is to determine the coordinates of the satellite–Sun vector [ 6 , 7 ] in the reference frame associated with the satellite.…”

Section: Introductionmentioning

confidence: 99%

Low-Cost Orientation Determination System for CubeSat Based Solely on Solar and Magnetic Sensors

Nurgizat

Ayazbay

Galayko

et al. 2023

Sensors

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CubeSats require accurate determination of their orientation relative to the Sun, Earth, and other celestial bodies to operate successfully and collect scientific data. This paper presents an orientation system based on solar and magnetic sensors that offers a cost-effective and reliable solution for CubeSat navigation. Solar sensors analyze the illumination on each face to measure the satellite’s orientation relative to the Sun, while magnetic sensors determine the Earth’s magnetic field vector in the satellite’s reference frame. By combining the measured data with the known ephemeris of the satellite, the satellite–Sun vector and the magnetic field orientation can be reconstructed. The orientation is expressed using quaternions, representing the rotation from the internal reference system of the satellite to the selected reference system. The proposed system demonstrates the ability to accurately determine the orientation of a CubeSat using only two sensors, making it suitable for installations where more complex and expensive instruments are impractical. Additionally, the paper presents a mathematical model of a low-cost CubeSat orientation system and a hardware implementation of the sensor. The technology, using solar and magnetic sensors, provides a reliable and affordable solution for CubeSat navigation, supporting the increasing sophistication of miniature payloads and enabling accurate satellite positioning in space missions.

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In-Orbit Attitude Determination of the UVSQ-SAT CubeSat Using TRIAD and MEKF Methods

Cited by 8 publications

References 30 publications

Design and Verification of an Integrated Panoramic Sun Sensor atop a Small Spherical Satellite

Design and Verification of an Integrated Panoramic Sun Sensor atop a Small Spherical Satellite

INSPIRE-SAT 7, a Second CubeSat to Measure the Earth’s Energy Budget and to Probe the Ionosphere

Low-Cost Orientation Determination System for CubeSat Based Solely on Solar and Magnetic Sensors

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