Gyroless Attitude Estimation of Sun-Pointing Satellites Using Magnetometers

Ahn, Hyo‐Sung; Lee, Seon-Ho

doi:10.1109/lgrs.2004.840608

Cited by 20 publications

(10 citation statements)

References 8 publications

(13 reference statements)

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“…Highlights include the use of a magnetometeronly sun-pointing algorithm by Ahn and Lee in 2003 [12]. The magnetometer-derived attitude was within 3°of a gyroscope-derived "truth."…”

Section: Introductionmentioning

confidence: 98%

Performance Trades for Multiantenna GNSS Multisensor Attitude Determination Systems

Tehrani

Gross

2018

International Journal of Aerospace Engineering

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We present various performance trades for multiantenna global navigation satellite system (GNSS) multisensor attitude estimation systems. In particular, attitude estimation performance sensitivity to various error sources and system configurations is assessed. This study is motivated by the need for system designers, scientists, and engineers of airborne astronomical and remote sensing platforms to better determine which system configuration is most suitable for their specific application. In order to assess performance trade-offs, the attitude estimation performance of various approaches is tested using a simulation that is based on a stratospheric balloon platform. For GNSS errors, attention is focused on multipath, receiver measurement noise, and carrierphase breaks. For the remaining attitude sensors, different performance grades of sensors are assessed. Through a Monte Carlo simulation, it is shown that, under typical conditions, sub-0.1-degree attitude accuracy is available when using multiple antenna GNSS data only, but that this accuracy can degrade to degree level in some environments warranting the inclusion of additional attitude sensors to maintain the desired level of accuracy. Further, we show that integrating inertial sensors is more valuable whenever accurate pitch and roll estimates are critical.

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“…Highlights include the use of a magnetometeronly sun-pointing algorithm by Ahn and Lee in 2003 [12]. The magnetometer-derived attitude was within 3°of a gyroscope-derived "truth."…”

Section: Introductionmentioning

confidence: 98%

Performance Trades for Multiantenna GNSS Multisensor Attitude Determination Systems

Tehrani

Gross

2018

International Journal of Aerospace Engineering

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“…During these intervals, attitude can be estimated by making use of the sensor measurements like single-frame methods. In [8], a simple method is suggested for attitude estimation of low Earth orbiting satellite in the Sun acquisition mode. In [9], an algorithm is proposed having switch logic depending on the phase of the mission, eclipse period, critical angular velocity, and critical attitude.…”

Section: Introductionmentioning

confidence: 99%

Singular value decomposition based satellite attitude determination using different sensor configurations

Cilden–Guler

Hajiyev

2017

Int. J. Metrol. Qual. Eng.

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Abstract. Satellite's attitude can be determined by using several different ways. In order to use a recursive filter to determine the attitude especially after crucial intervals for the satellite including detumbling, eclipse, etc., single-frame methods can be used, and singular value decomposition (SVD) method has been selected because of its robustness for this paper. They can be placed for the initial values, or continuous input to the filter in addition to covariance matrix at each step. Also, sensor configurations depending on the position of the Sun are considered and used in the SVD method. Wahba's loss function is minimized with separating the basic matrix including the reference and model vectors into singular values because many researches show the SVD as the most robust algorithm after error analyses between several single-frame methods. Sun sensor, magnetometer, and horizon sensor are the selected common attitude sensors for small satellites in order to compare their attitude determination performances. For this purpose, absolute errors for different sensor configurations in the simulation environment in addition to the RMS errors are presented. The purpose of the paper is to present an attitude determination concept for a nanosatellite. Also, different sensor configurations are considered in the single-frame method with switching logic depending on the vector data. Horizon sensor and sun sensor are the optimum pair for the light side of the Earth on the other hand, during the eclipse; horizon sensor and magnetometer give the most accurate results. Study shows that the proposed algorithm can be performed for initial values to the Kalman filter, and in the transient phase before the filter tuned in practical satellite usage. In the eclipse period, sun-independent sensors are used and changing configurations provide better attitude estimation results to filtering techniques.

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“…Recently, new attitude determination schemes have been developed for satellite control in the presence of incomplete vector measurements (see the next section for the precise definition of ''incomplete vector measurements'') 16,17) based on geometrical configuration. A deterministic attitude estimation method was established for the coarse-attitude calculation of the sun-pointing satellites.…”

Section: Introductionmentioning

confidence: 99%

“…A deterministic attitude estimation method was established for the coarse-attitude calculation of the sun-pointing satellites. 16) Although the method proposed by Ahn and Lee 16) is capable of estimating the attitude in the presence of incomplete vector measurements, the application is limited to the attitude estimation only when the x-axis is pointing towards a known direction. Nonlinear simultaneous equation was solved for a closedloop form of attitude determination with incomplete vector measurements.…”

Section: Introductionmentioning

confidence: 99%

“…This paper seeks to generalize the geometrical attitude determination method of Ahn and Lee 16) such that the modified method can be used for three-axis attitude determination even in the presence of incomplete vector measurements. Though the capability of the new method is almost similar to the TRIAD algorithm and can be used for the same purpose as the TRIAD, the method established in this paper does not require the whole measured vector components and its derivation process is entirely different from the TRIAD.…”

Section: Introductionmentioning

confidence: 99%

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Geometrical Attitude Determination Algorithm Based on Vector Measurements

Ahn

Lee

2010

Trans. Japan Soc. Aero. S Sci.

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This paper addresses a novel vector-based attitude determination algorithm on the basis of geometrical configuration of external reference vectors. The proposed method called a geometrical attitude determination algorithm can be used for the attitude estimation of moving vehicles when two external reference vectors are partially measured on three orthogonal body axes. Applications of the new method range from the ground robotics navigation to satellite attitude control. Numerical simulations demonstrate that the algorithm can be reliably utilized for the three-axis attitude determination in the presence of inaccurately-measured reference vectors.

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Gyroless Attitude Estimation of Sun-Pointing Satellites Using Magnetometers

Cited by 20 publications

References 8 publications

Performance Trades for Multiantenna GNSS Multisensor Attitude Determination Systems

Performance Trades for Multiantenna GNSS Multisensor Attitude Determination Systems

Singular value decomposition based satellite attitude determination using different sensor configurations

Geometrical Attitude Determination Algorithm Based on Vector Measurements

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