Unscented Kalman Filter for Spacecraft Attitude Estimation and Calibration Using Magnetometer Measurements

Ma, Guangfu; Xue-yuan, Jiang

doi:10.1109/icmlc.2005.1526998

Cited by 13 publications

(4 citation statements)

References 4 publications

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“…After having verified the performance of the algorithm, it is worth to compare it to other magnetometer-only solutions available in the literature [19][20][21][22][23][24][25]. As mentioned in the introduction, these are typically based on the use of a Kalman filter (EKF or UKF) and can provide accuracy as good as 1 • and 0.01 • /s in the estimation of, respectively, the Euler angles and the angular rates.…”

Section: Discussionmentioning

confidence: 99%

“…It can be noticed that the estimated power usage from the algorithm proposed, implementing 3 × 3 matrix operations, is equal to 277 mW, a value compatible with those in Table 12. If referring to the methods [20][21][22][23][24][25], the matrix size ranges from 6 × 6 to 9 × 9; therefore, their power usage can be estimated to approximately 2.7 times higher.…”

Section: Discussionmentioning

confidence: 99%

“…The most popular methods for three-axis magnetometer-only attitude determination are based on the Extended Kalman Filter (EKF) and can reach an accuracy below 5 • on attitude and 0.01 • /s on the angular rates [21][22][23]. Other solutions include the Unscented Kalman Filter (UKF) algorithm by Ma and Jiang [24], or the two-step EKF algorithm proposed by Searcy and Pernicka [25], which achieves accuracies of less than 1 • , but is effective only if the angular rates along at least one axis exceeds 0.1 • /s.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A Magnetometer-Only Attitude Determination Strategy for Small Satellites: Design of the Algorithm and Hardware-in-the-Loop Testing

2020

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Attitude determination represents a fundamental task for spacecraft. Achieving this task on small satellites, and nanosatellites in particular, is further challenging, because the limited power and computational resources available on-board, together with the low development budget, set strict constraints on the selection of the sensors and the complexity of the algorithms. Attitude determination is obtained here from the only measurements of a three-axis magnetometer and a model of the Geomagnetic field, stored on the on-board computer. First, the angular rates are estimated and processed using a second-order low-pass Butterworth filter, then they are used as an input, along with Geomagnetic field data, to estimate the attitude matrix using an unsymmetrical TRIAD. The computational efficiency is enhanced by arranging complex matrix operations into a form of the Faddeev algorithm, which is implemented using systolic array architecture on the FPGA core of a CubeSat on-board computer. The performance and the robustness of the algorithm are evaluated by means of numerical analyses in MATLAB Simulink, showing pointing and angular rate accuracy below 10° and 0.2°/s. The algorithm implemented on FPGA is verified by Hardware-in-the-loop simulation, confirming the results from numerical analyses and efficiency.

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Section: Discussionmentioning

confidence: 99%

Section: Discussionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A Magnetometer-Only Attitude Determination Strategy for Small Satellites: Design of the Algorithm and Hardware-in-the-Loop Testing

2020

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“…This information is contained in a list of orbital elements for a given point in time called a two-line element set (retrieved by the NORAD). The angular velocity with respect to the orbital frame is computed at each time given the attitude matrix at that time with respect to the orbital frame in Equation (9).…”

Section: Theoretical Approach Of the Methodsmentioning

confidence: 99%

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

Finance

Dufour

Boutéraon

et al. 2021

Sensors

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Ultraviolet and infrared sensors at high quantum efficiency on-board a small satellite (UVSQ-SAT) is a CubeSat dedicated to the observation of the Earth and the Sun. This satellite has been in orbit since January 2021. It measures the Earth’s outgoing shortwave and longwave radiations. The satellite does not have an active pointing system. To improve the accuracy of the Earth’s radiative measurements and to resolve spatio-temporal fluctuations as much as possible, it is necessary to have a good knowledge of the attitude of the UVSQ-SAT CubeSat. The attitude determination of small satellites remains a challenge, and UVSQ-SAT represents a real and unique example to date for testing and validating different methods to improve the in-orbit attitude determination of a CubeSat. This paper presents the flight results of the UVSQ-SAT’s attitude determination. The Tri-Axial Attitude Determination (TRIAD) method was used, which represents one of the simplest solutions to the spacecraft attitude determination problem. Another method based on the Multiplicative Extended Kalman Filter (MEKF) was used to improve the results obtained with the TRIAD method. In sunlight, the CubeSat attitude is determined at an accuracy better than 3° (at one σ) for both methods. During eclipses, the accuracy of the TRIAD method is 14°, while it reaches 10° (at one σ) for the recursive MEKF method. Many future satellites could benefit from these studies in order to validate methods and configurations before launch.

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Erratum to: Development of a low-cost wearable sensing glove with multiple inertial sensors and a light and fast orientation estimation algorithm

Choi¹,

Yoo²,

Kang

et al. 2017

J Supercomput

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Unscented Kalman Filter for Spacecraft Attitude Estimation and Calibration Using Magnetometer Measurements

Cited by 13 publications

References 4 publications

A Magnetometer-Only Attitude Determination Strategy for Small Satellites: Design of the Algorithm and Hardware-in-the-Loop Testing

A Magnetometer-Only Attitude Determination Strategy for Small Satellites: Design of the Algorithm and Hardware-in-the-Loop Testing

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

Erratum to: Development of a low-cost wearable sensing glove with multiple inertial sensors and a light and fast orientation estimation algorithm

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