Fundamentals of Spacecraft Attitude Determination and Control
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The MEKF approach that does not use rotational dynamics models or gyroscope information to update measurements avoids corrupting gyro data from inaccurate dynamic models and requires much less computational effort.
“According to [Markley and Crassidis, 2014], this approach avoids corrupting gyro data from inaccurate dynamic models, and requires much less computational effort.”
From <sup>3</sup>CAT-2: Attitude Determination and Control System for a GNSS-R Earth Observation 6U CubeSat Mission (2016) · cites this paper as Markley and Crassidis, 2014
The Extended Kalman Filter selected for 3CAT-2 is the Multiplicative Extended Kalman Filter (MEKF), which hinges upon quaternions and their properties.
“The Extended Kalman Filter selected for 3 Cat-2 is known as Multiplicative Extended Kalman Filter (MEKF) which hinges upon quaternions and their properties [Markley and Crassidis, 2014].”
From <sup>3</sup>CAT-2: Attitude Determination and Control System for a GNSS-R Earth Observation 6U CubeSat Mission (2016) · cites this paper as Markley and Crassidis, 2014
According to Markley and Crassidis (2014), the proposed control law is global, asymptotically stable in a torque free environment, assuming full control is available.
“According to reference [Markley and Crassidis, 2014], the proposed control law is global, asymptotically stable in a torque free environment, and assuming that full control is available.”
From <sup>3</sup>CAT-2: Attitude Determination and Control System for a GNSS-R Earth Observation 6U CubeSat Mission (2016) · cites this paper as Markley and Crassidis, 2014
The benefit of QUEST over the q-method is that the optimal quaternion is obtained by solving a quartic equation instead of an eigenvalue problem, making it computationally suitable.
“The benefit of QUEST instead of q-method is that the optimal quaternion is obtained by solving a quartic equation instead of an eigenvalue problem, resulting in a computationally suitable method.”
From <sup>3</sup>CAT-2: Attitude Determination and Control System for a GNSS-R Earth Observation 6U CubeSat Mission (2016) · cites this paper as Markley and Crassidis, 2014
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“The Extended Kalman Filter selected for 3Cat-2 is known as Multiplicative Extended Kalman Filter (MEKF) which hinges upon quaternions and their properties [Markley and Crassidis, 2014].”
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Attitude Trajectory Optimization for Agile Satellites in Autonomous Remote Sensing Constellations
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- Authors
- Markley, F. L., & Crassidis, J. L.
- Affiliations
- Goddard Space Flight Center (US)
- University at Buffalo, State University of New York (US)
- ORCID
- Crassidis, John L.
- Venue
- Springer eBooks
- Publisher
- Springer New York
- Published
- 2014
- OpenAlex
- W636927631
- Cited by
- 1,035
- References
- 0
- Citations by year
- 2026: 71 · 2025: 79 · 2024: 114 · 2023: 115 · 2022: 96 · 2021: 119 · 2020: 100 · 2019: 94 · 2018: 92 · 2017: 69 · 2016: 58 · 2015: 27 · 2013: 1
- FWCI
- 52.78
- Type
- book
- Language
- en
- Open access
- closed
- Locations
- Springer eBooks (publishedVersion)
- CERN Document Server (European Organization for Nuclear Research) (submittedVersion)
- DIAL (Catholic University of Leuven) (submittedVersion)
- Topics
- Physical Sciences › Engineering › Aerospace Engineering › Spacecraft Dynamics and Control
- Physical Sciences › Engineering › Aerospace Engineering › Spacecraft Design and Technology
- Physical Sciences › Engineering › Aerospace Engineering › Inertial Sensor and Navigation
- Keywords
- spacecraft attitude determination, spacecraft attitude control, attitude estimation algorithms, spacecraft dynamics, attitude dynamics
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