Abstract
Observer-based hovering control over a tumbling asteroid in the body-fixed frame is studied. An extended Kalman filter (EKF) is used to process range measurements from a small collection of ground stations, yielding estimates of the spacecraft state vector and the gravitational parameters of the asteroid assuming a second degree and order gravity field model. The estimated states are used in the optimal feedback control algorithm which consists of two alternatives: time-varying LQR or the Lyapunov-Floquet transformation (LFT) and time-invariant LQR. The closed-loop response of the system and the control effort required are investigated and compared for both control strategies.
Original language | English (US) |
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Pages (from-to) | 124-139 |
Number of pages | 16 |
Journal | Acta Astronautica |
Volume | 102 |
DOIs | |
State | Published - 2014 |
Keywords
- Continuous control
- Extended Kalman filter
- Lyapunov-Floquet transformation
- Time-varying LQR
- Tumbling asteroid
ASJC Scopus subject areas
- Aerospace Engineering