Small frame type control moment gyroscope driven by double-stator ultrasonic motor

Abstract

The invention discloses a small frame type control moment gyroscope driven by a double-stator ultrasonic motor. The small frame type control moment gyroscope comprises a frame, a momentum wheel, a high-speed motor, a first bearing, a second bearing, a third bearing, a fourth bearing, a base, an encoder and the double-stator ultrasonic motor. The frame comprises a square frame and a shaft part; thetwo ends of a momentum wheel rotating shaft are correspondingly connected with the square frame through bearings. The high-speed motor and the momentum wheel are coaxially arranged. The two ends of the base are provided with through holes for the shaft part of the frame to pass through. The frame shaft part is connected with the through hole of the base through a bearing. The encoder is mounted at one end of the base for measuring the rotating speed of the frame shaft part. A rotor of the frame motor is connected with the other end of the frame shaft part through a pin connecting piece and used for driving the frame shaft part to rotate. A double-stator ultrasonic motor is used as the frame motor, the output torque of the motor is further improved on the basis of an original single-statorrotating traveling wave type ultrasonic motor, and the response speed is increased. According to the invention, the requirements of a high-precision small space maneuvering platform can be met.

Description

technical field [0001] The invention relates to an aerospace executive mechanism for a space maneuvering platform to realize fast maneuvering tasks, in particular to a small frame type control moment gyroscope. Background technique [0002] Small and medium-sized satellites have the characteristics of light weight, small size, rapid launch, and agile maneuvering in orbit. The small single-frame control moment gyroscope has the advantages of large output torque and low power consumption, and is an ideal aerospace actuator for space maneuvering platforms to achieve fast maneuvering tasks. Due to the strict restrictions on the size and weight of the launch vehicle, and the emergence of single-frame control moment gyros in multiple groups, it is required that the single-frame control moment gyroscopes are small in size, light in weight, and have torque output capabilities that meet the agile and exciting needs of satellites. The frame control moment gyroscope can't meet the req...

AI Technical Summary

Problems solved by technology

[0005] However, the existing control torque gyroscopes are mostly used in large spacecraft, and there are few control torque gyros suitable for micro-sized spacecraft, especially the small output torque control torque gyroscopes required by Pina satellites are less, and the output torque is required to be within Small Control Moment Gyroscope Below 1Nm

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