Attitude determination and disturbance estimation based on adaptive Kalman filter for nano-satellite

Choi, Sung Hyuk; Park, Chan Gook

doi:10.1109/iccas.2016.7832434

Cited by 2 publications

(2 citation statements)

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“…Therefore according to equations (6), (9), and (12), another method for obtaining the Euler angles can be obtained namely…”

Section: Derivation Of Different Computation Methods For Euler Anglesmentioning

confidence: 99%

“…6,7 An adaptive scheme based on multiple coefficients in the KF has been utilized in Jiang et al 8 Attitude determination and disturbance estimation algorithms based on adaptive EKF has been introduced in Choi and Park. 9 Also, Lim and Park 10 suggest an adaptive fading EKF. Wang et al 11 dealt with an inertial/celestial-based adaptive UKF in which a fuzzy adaptive tuning method is used to help tuning.…”

Section: Introductionmentioning

confidence: 99%

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Design of a supervisory algorithm based on failure mode effect criticality analysis for classification of different fault types of attitude determination sensors

Abedi

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, a supervisory algorithm for attitude determination sensors of a three-axis satellite is suggested to classify different fault types of this system. The presented solution is based on the computation of rotation matrices between the orbital and body frames. Using the Euler angles provided by these rotations, some variance measures are computed, which utilized as an analytical tool for the determination of faulty sensors and the related fault sources. According to the mentioned idea, it is shown that the fault sources could be categorized into four levels. Each level shows the fault extent and its criticality. To include the reliability aspects in this paper, a failure mode effect criticality analysis is conducted to determine different failure modes, which really occur in sensors. For this, the probability levels and the severity numbers were assigned to derive the critical ones. It is shown that most of the critical failure modes could be isolated by the proposed methods; in other words, the design process is based on real faulty scenarios that can improve the system reliability. Finally, by performing some numerical simulations, performance of the developed algorithms are validated.

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“…Therefore according to equations (6), (9), and (12), another method for obtaining the Euler angles can be obtained namely…”

Section: Derivation Of Different Computation Methods For Euler Anglesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Design of a supervisory algorithm based on failure mode effect criticality analysis for classification of different fault types of attitude determination sensors

Abedi

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

Gyro-stellar inertial attitude estimation for satellite with high motion rate

Lin

Chiu

et al. 2022

Aeronaut. j.

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For a common micro-satellite, orbiting in a circular sun-synchronous orbit (SSO) at an altitude between 500 and 600km, the satellite attitude during off-nadir imaging and staring-imaging operations can be up to ±45 degree on roll and pitch angles. During these off-nadir pointing for both multi-trip operation and staring imaging operations, the spacecraft body is commonly subject to high-rate motion. This posts challenges for a spacecraft attitude determination subsystem called Gyro Stellar Inertial Attitude Estimate (GS IAE), which employs gyros and star sensors to maintain the required attitude knowledge, since star trackers will severely degrade attitude estimation accuracies when the spacecraft is subject to high-rate motion. This paper analyses the star motion-induced errors for a typical star tracker, models the star motion-induced errors to assess the performance impact on the attitude estimation accuracy, and investigates the adaptive extended Kalman filter design in the GS IAE while evaluating its effectiveness.

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Attitude determination and disturbance estimation based on adaptive Kalman filter for nano-satellite

Cited by 2 publications

References 12 publications

Design of a supervisory algorithm based on failure mode effect criticality analysis for classification of different fault types of attitude determination sensors

Design of a supervisory algorithm based on failure mode effect criticality analysis for classification of different fault types of attitude determination sensors

Gyro-stellar inertial attitude estimation for satellite with high motion rate

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