Abstract
An analysis is presented for the dynamic response and proof-mass actuator (PMA) closed loop control of the COFS-I flexible astromast, excited by pitching manoeuvres of the Space Shuttle. The PMA control loop parameters are investigated in order to give a specific damping ratio for the fundamental mode of the cantilever astromast for the case of a colocated PMA/sensor placed at the free end of the mast. The equations of motion are derived for the transient response of the mast in modal form as well as the equation for the response of the PMA, numerical results being given for the first three modes of vibration. The equations of motion are found to be coupled by the active modal damping and it is found for a single colocated PMA/sensor placed at the mast tip that the system is stable for any value of the velocity feedback gain.
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