SIMULATOR STUDY OF A SATELLITE ATTITUDE CONTROL SYSTEM USING INERTIA WHEELS AND A MAGNET
Automatic attitude control system test for satellite using inertia wheels mounted on air bearings
Engineering topics
Publications and source records attributed to Adams, J. J..
Automatic attitude control system test for satellite using inertia wheels mounted on air bearings
Human pilot transfer function in closed loop single degree of freedom attitude control system
Measuring human transfer functions - determination of variable gains using analog autopilot and human pilot operating flight simulator controls
Use of simulators, currently in being or under development for the study of piloting problems of space vehicles
Transfer function of a human pilot operating in a closed loop control situation, using single axis and two axes tests, and comparison of pilot and model pilot performance
Simulator study of an active control system for a spinning body
The mission requirements for some satellites require that they spin continuously and at the same time maintain a precise direction of the spin axis. An analog-computer study has been made of an attitude control system which is suitable for such a satellite. The control system provides the necessary attitude control through the use of a spinning wheel, which will provide precession torques, commanded by an automatic closed-loop servomechanism system. The sensors used in the control loop are rate gyroscopes for damping of any wobble motion and a sun seeker for attitude control. The results of the study show that the controller can eliminate the wobble motion of the satellite resulting from a rectangular pulse moment disturbance and then return the spin axis to the reference space axis. The motion is damped to half amplitude in less than one cycle of the wobble motion. The controller can also reduce the motion resulting from a step change in product of inertia both by causing the new principal axis to be steadily alined with the spin vector and by reducing the cone angle generated by the reference body axis. These methods will reduce the motion whether the satellite is a disk, sphere, or rod configuration.