A Frame System for Control Moment Gyroscope

Abstract

The invention discloses a frame system for a control moment gyroscope. The frame system can be used as a posture control executing mechanism of large spacecraft like a large satellite and a space station and is composed of a rotary transformer end mechanical bearing, a conducting slide ring, a rotary transformer, a rotary transformer base, a rotary variable shaft, a harmonic shaft, a frame, a motor base, a harmonic reducer, a frame motor stator assembly, a frame motor rotor assembly, a motor end mechanical bearing and the like. A frame core shaft is driven by a frame moment motor to drive a connected gyroscope rotor to rotate to output gyroscope moment, the rotary transformer is in charge of outputting an angular position signal of the frame core shaft to be fed back to a control system ofa moment motor, therefore the moment motor is controlled, an iron core fractional slot structure is adopted by the moment motor to reduce flux leakage, after the moment output by the motor is amplified by the harmonic reducer, the moment is transferred to the gyroscope rotor, and therefore, gyroscope torque is output. The frame system has the advantages that the layout is compact, the size is small, the weight is low, the system noise is small, and the control precision and torque output efficiency of the frame system are high.

Description

technical field [0001] The invention relates to the technical field of inertial actuators for spacecraft attitude control, in particular to a frame system for controlling moment gyroscopes. Background technique [0002] The control moment gyroscope is the key actuator for attitude control of long-running large spacecraft such as the space station. The maneuverability of spacecraft attitude control requires that the control moment gyro frame system can achieve the fastest angular velocity of 14.3° / s and the maximum output torque of 50N.m. The key indicators directly affect the attitude control accuracy, attitude maneuverability and response speed of the spacecraft, and the structure and index performance of the frame system have an important impact on the above indicators. The frame torque motor is the key factor that determines the frame speed control accuracy and output torque. At present, the stators of torque control gyro frame torque motors are mostly iron-less structu...

AI Technical Summary

Problems solved by technology

At present, the stators of torque control gyro frame torque motors are mostly iron-less structure or iron core without cogging structure. Although the torque ripple is reduced, the output torque is affected, and the phenomenon of magnetic flux leakage is also serious. Spacecraft applications that require high torque output are limited

At present, the stator of the control torque gyro frame torque motor with an iron core is prone to flux density saturation, which makes the motor control present nonlinear characteristics, which is not conducive to the high-precision control of the control torque gyro frame torque motor, and is also not conducive to large spacecraft for large torque. output requirements

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