Author(s)

S.D. Zemlyakov, V.M. Glumov & S.J. Dodds

Abstract

A new form of adaptive attitude control system is developed for spacecraft comprising attitude sensors and torque actuators collocated on a rigid centrebody having attached flexible appendages with negligible natural damping, the dynamics parameters and order being unknown. Better overall active modal damping is achieved than attainable with conventional fixed-gain PD controllers. This initial investigation focusses on single-axis control without inter-axis coupling. First, the method of local replacement of characteristic polynomials is employed to determine, using the root locus, the derivative feedback gain of a PD control

Keywords