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Dr. Daero Lee
Department of Aerospace Science and Engineering, Tuskegee University, Tuskegee, AL 36088, USA

Basic Info

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Research Keywords & Expertise

0 Orbital mechanics, astrodynamics and spacecraft GNC
0 Spacecraft trajectory optimization
0 Orbit determination using GPS
0 Spacecraft navigation and control for asteroid exploration
0 Rendezvous, proximity operations and docking of spacecraft

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Regular papers
Published: 06 September 2017 in International Journal of Control, Automation and Systems
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A robust unscented Kalman filter based on a multiplicative quaternion-error approach is proposed for nanosat estimation in the presence of measurement faults. The global attitude parameterization is given by a quaternion, while the local attitude error is defined using a generalized three-dimensional attitude representation. The proposed algorithm uses a statistical function including measurement residuals to detect measurement faults and then uses an adaptation scheme based on multiple measurement scale factor for filter robustness against faulty measurements. The proposed algorithm is demonstrated for the attitude estimation of a nanosat with an on-board three-axis magnetometer and rate-integrating gyros in the presence of measurement faults as well as satellite orbit errors. To compare the estimation performance of the proposed algorithm, the robust unscented Kalman filter with single measurement noise scale factor, the standard extended Kalman filter and the unscented Kalman filter are also implemented under the same simulation conditions.

ACS Style

Daero Lee; George Vukovich; Regina Lee. Robust unscented Kalman filter for nanosat attitude estimation. International Journal of Control, Automation and Systems 2017, 15, 2161 -2173.

AMA Style

Daero Lee, George Vukovich, Regina Lee. Robust unscented Kalman filter for nanosat attitude estimation. International Journal of Control, Automation and Systems. 2017; 15 (5):2161-2173.

Chicago/Turabian Style

Daero Lee; George Vukovich; Regina Lee. 2017. "Robust unscented Kalman filter for nanosat attitude estimation." International Journal of Control, Automation and Systems 15, no. 5: 2161-2173.

Article
Published: 22 May 2017 in International Journal of Control, Automation and Systems
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This paper presents finite-time stabilization of spacecraft formation flying with a decentralized collision avoidance in the framework of geometric mechanics. A finite-time control scheme is developed such that each spacecraft achieves desired relative configuration and velocities with respect to the virtual leader autonomously. The finite-time control scheme is combined with a decentralized collision avoidance scheme. A Lyapunov analysis guarantees that the spacecraft motions converge to the desired state trajectories with the combined control scheme in finite time. Numerical simulation results verify the successful application of the proposed combined control scheme for spacecraft formation flying in the presence of unknown external disturbances while avoiding collisions via the decentralized collision avoidance.

ACS Style

Daero Lee; George Vukovich. Almost global finite-time stabilization of spacecraft formation flying with decentralized collision avoidance. International Journal of Control, Automation and Systems 2017, 15, 1167 -1180.

AMA Style

Daero Lee, George Vukovich. Almost global finite-time stabilization of spacecraft formation flying with decentralized collision avoidance. International Journal of Control, Automation and Systems. 2017; 15 (3):1167-1180.

Chicago/Turabian Style

Daero Lee; George Vukovich. 2017. "Almost global finite-time stabilization of spacecraft formation flying with decentralized collision avoidance." International Journal of Control, Automation and Systems 15, no. 3: 1167-1180.