چكيده به لاتين
Design and Manufacturing of a Single Gimbal Control Moment Gyroscope (SGCMG)
Abstract
Due to tracking of moving objects in space or on the ground, satellites need to perform fast maneuvers. Control moment gyro is a kind of actuator based on gyroscope inertia and is capable of producing required torque to do desired maneuver. The most advantages of Control Moment Gyro are its torque amplification and non-consuming fuel system.
First In this thesis, a lab-model of Single Gimbal Control Moment Gyro is designed and then manufactured in order to verify functional test. it should be mentioned that DC motors are utilized in this SGCMG.
In order to achieve requirements, a disk is attached to a dc motor shaft and turns around its spin axis in a constant speed using a controller to produce a constant and stable angular momentum. To produce the designed torque, the direction of spinning disk should vary constantly, therefore using another dc motor to turn the gimbal shaft, yields spin axis vary and then required torque is generated. In this research a dc motor is utilized to turning the disk and a stepper motor for gimbal turning, Also Control laws are utilized to control gimbal speed and disk speed. Owing to further hardware in the loop test, an Arduino board is utilized as a bridge between PC and CMG. SGCMG hardware in the loop test is implemented by means of this board and real time performance of actuator is assisted with a software model of an attitude control system of a typical satellite.
Keywords: attitude control, satellite actuators, Control Moment Gyro, angular momentum
