Attitude control of a bias momentum satellite using moment of inertia

IEEE Transactions on Aerospace and Electronic Systems

Volumn 38, Issue 1, 2002, Pages 243-250

  Bang, Hyochoong ^a   Choi, Hyung Don ^b  

^a Korea Advanced Institute of Science and Technology (KAIST)   (South Korea)

^b Korea Aerospace Research Institute (KARI)   (South Korea)

Author keywords

[No Author keywords available]

Indexed keywords

ATTITUDE CONTROL; BIAS MOMENTUM SATELLITE; DYNAMIC COUPLING EFFECT; NUTATIONAL MODE CONTROL;

APPROXIMATION THEORY; COMPUTER SIMULATION; CONTROL SYSTEM SYNTHESIS; EQUATIONS OF MOTION; FEEDBACK CONTROL; LAPLACE TRANSFORMS; LINEARIZATION; POLYNOMIALS; TORQUE; TWO TERM CONTROL SYSTEMS;

SATELLITES;

EID: 0036250772     PISSN: 00189251     EISSN: None     Source Type: Journal    
DOI: 10.1109/7.993243     Document Type: Article

References (8)

1. Spacecraft attitude acquisition from an arbitrary spinning or tumbling state
2. Formulation of stability conditions for systems containing driven rotors
3. Active nutation damping utilizing spacecraft mass properties
4. An active nutation control system for spin stabilized satellites
5. Attitude control subsystem performance of the RCA series 3000 satellite