Accession Number : ADA257632


Title :   The Design of an Adaptive Attitude Control System


Descriptive Note : Master's thesis,


Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA


Personal Author(s) : Russo, Nicholas F


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a257632.pdf


Report Date : Sep 1992


Pagination or Media Count : 91


Abstract : This research designed and simulated an adaptive attitude control system for the Crew Equipment/Retriever (CER) during autonomous attitude hold and large angle or slewing maneuvers. The CER is a proposed space robot that deploys from the Space Station and retrieves any lost equipment or incapacitated astronauts. The moment of inertia tensor for the CER and acquired target is not known a priori. In this research, the moment of inertia tensor is estimated by a Kalman filter and used to update the derived linear quadratic regulator (LQR) and quaternion feedback regulator (QFR) control laws. Computer simulation results show that during attitude hold the adaptive LQR design stabilizes the CER and provides a more fuel efficient controller effort: as compared with a previously designed nonadaptive minimum time controller and a nonadaptive LQR design. Computer simulation results of slewing maneuvers show that the adaptive QFR design provides a more fuel efficient controller: as compared with a nonadaptive QFR design.


Descriptors :   *ATTITUDE CONTROL SYSTEMS , *SPACE STATIONS , CONTROL , STATIONS , SIMULATION , COMPUTERS , ROBOTS , TARGETS , TIME , FEEDBACK , ASTRONAUTS , MOMENT OF INERTIA , SLEWING , FILTERS , TENSORS , MANEUVERS , CREWS , FUELS , REGULATORS , MOMENTS , PARAMETERS , INERTIA , ANGLES , CONTROL SYSTEMS


Subject Categories : Spacecraft Trajectories and Reentry


Distribution Statement : APPROVED FOR PUBLIC RELEASE