Fully-suspended double-end-supported single-frame control moment gyroscope

Abstract

The invention discloses a fully-suspended double-end-supported single-frame control moment gyroscope. The fully-suspended double-end-supported single-frame control moment gyroscope is mainly composedof a magnetically-suspended frame system and a magnetically-suspended high-speed rotor system; the magnetically-suspended frame system is mainly composed of a frame, frame three-degree-of-freedom magnetic bearings, a frame radial sensor, a frame motor, a frame protection bearing, a frame axial sensor, a left frame shaft, a right frame shaft and the like; the magnetically-suspended high-speed rotorsystem is mainly composed of an upper gyroscopic case, a lower gyroscope case, axial magnetic bearings, high-speed driving motors, a gyroscopic high-speed rotor, radial magnetic bearings, radial displacement sensors, an axial displacement sensor, protection bearings and the like. According to the fully-suspended double-end-supported single-frame control moment gyroscope, the high-speed rotor system supported by the magnetic bearings is adopted, so that the working rotation speeds of the gyroscopic high-speed rotors are greatly improved, and the service lives of the gyroscopic high-speed rotors are greatly prolonged; meanwhile, a magnetic-bearing double-end-supported mode is adopted by the frame system, so that the supporting stiffness is improved, mechanical friction is eliminated, and the control precision of the system is improved.

Description

technical field [0001] The invention relates to the technical field of control moment gyroscopes, in particular to a single-frame control moment gyroscope with full-suspension double-end support, which can be used as an attitude actuator for spacecraft, and can be used for large spacecraft or small spacecraft, such as space stations or agile maneuvers. Satellite attitude control. Background technique [0002] With the development of manned spaceflight, earth observation, and scientific research, corresponding space stations, satellite platforms, or small spacecraft have higher and higher requirements for attitude control, which is specifically reflected in the stability of attitude control and the flexibility of large-angle maneuvering . Existing actuators for attitude control mainly include thrusters, inertial actuators and environmental torque actuators. Compared with the other two types of actuators, the inertial actuator uses the momentum exchange theorem to achieve at...

AI Technical Summary

Problems solved by technology

The main disadvantage of the single-end support type compared with the double-end support type is that only one end support reduces the overall stiffness of the frame, and the modal frequency further decreases, and resonance is prone to occur when a large gyro torque is output. When outputting small torque

[0003] In the patent CN200710065550.1 "Single-end supported single-frame magnetic levitation control torque gyroscope", the rotor supported by magnetic levitation is used, but the frame system adopts the single-end mechanical bearing support method, and the frame axis is affected by the friction torque, which makes the system non-linear and difficult be overcome

Patent CN200710065551.6 "Completely Non-Contact Single Frame Magnetic Suspension Control Moment Gyroscope" adopts the rotor system and frame system supported by magnetic levitation, but the frame adopts single-end support, which is not conducive to the improvement of frame rigidity, which in turn affects the vibration of the whole system characteristic

Patent CN200710304236.4 "Double Frame Magnetic Suspension Control Moment Gyro", Patent CN201410383894.7 "A Four-degree-of-Freedom Single-Frame Magnetic Suspension Control Moment Gyro" and Patent CN201410384117.4 "A Four-Dof Dual-Frame Magnetic Suspension Control Moment Gyro" Magnetic levitation control moment gyro, its frame system adopts double-ended mechanical bearing support, which does not realize the frictionless suspension of the frame

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