Optimal Reorientation Maneuver of Bias Momentum Spacecraft
Author:
Affiliation:
1. Korea Aerospace Research Institute, Daejon 305-600, Republic of Korea
2. Korea Telecom, Seoul 680-63, Republic of Korea
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Applied Mathematics,Electrical and Electronic Engineering,Space and Planetary Science,Aerospace Engineering,Control and Systems Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/2.4188
Reference19 articles.
1. Junkins, J. L., and Turner, J. D., Optimal Spacecraft Rotational Maneuvers, Elsevier, Amsterdam, 1985, pp.171-223.
2. Numerical approach for solving rigid spacecraft minimum time attitude maneuvers
3. Near-minimum time open-loop slewing of flexible vehicles
4. Near-minimum-time control of distributed parameter systems - Analytical and experimental results
5. Time-optimal three-axis reorientation of a rigid spacecraft
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1. Analytical Solution for Attitude Command Generation of Agile Spacecraft;Journal of the Korean Society for Aeronautical & Space Sciences;2018-08-31
2. Adaptive robust attitude control and active vibration suppression of flexible spacecraft;Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering;2016-05-18
3. Magnetometer-only linear attitude estimation for bias momentum pico-satellite;Journal of Zhejiang University-SCIENCE A;2010-06
4. Variable structure control and active vibration suppression of flexible spacecraft during attitude maneuver;Aerospace Science and Technology;2005-06
5. Optimum Reorientation of a Gyroscope Device;AIAA/AAS Astrodynamics Specialist Conference and Exhibit;2002-06-25
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