Control moment gyro driven by parallel type linear ultrasonic motor

A technology for controlling torque gyroscopes and ultrasonic motors, applied to rotating gyroscopes, etc., can solve the problems of complex locking mechanism, poor control accuracy, and slow response, and achieve high response, rapid action, and long service life.

Pending Publication Date: 2018-09-21
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0005] Aiming at the problems of slow response, poor control precision, complicated locking mechanism and heavy weight in the prior art

Method used

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  • Control moment gyro driven by parallel type linear ultrasonic motor
  • Control moment gyro driven by parallel type linear ultrasonic motor
  • Control moment gyro driven by parallel type linear ultrasonic motor

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Embodiment Construction

[0033] In order to make the object, technical solution and effect of the present invention clearer and clearer, the present invention will be further described in detail below with reference to the accompanying drawings and examples. It should be pointed out that the specific implementations described here are only used to explain the present invention, not to limit the present invention.

[0034] Such as Figure 1~2 As shown, the present invention includes a rotating assembly, a fixed assembly, and a fixed assembly. The moment gyroscope is integrally divided into a two-stage structure, the upper end part is a rotating assembly, and the lower end part is a fixed assembly.

[0035] The rotating assembly includes a momentum wheel protection housing 15, and the momentum wheel protection housing 15 includes a momentum wheel 1, a high-speed motor 2, and a first angle encoder 3; the momentum wheel 1 is connected to the high-speed motor 2 stator or is formed by the momentum wheel 1 ...

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Abstract

The invention discloses a control moment gyro driven by a parallel type linear ultrasonic motor and belongs to the technical field of control moment gyros. The control moment gyro comprises a rotatingcomponent and a fixing component and is characterized in that the rotating component provides rotational inertia needed by angular momentum, and power supply and a rotating speed control signal are provided for the rotating component through a slide ring component; the rotation angular speed of the angular momentum is precisely controlled through the parallel type linear ultrasonic motor in the fixing component, and accordingly the magnitude and direction of output torque are controlled precisely; a control circuit is used to drive and control the rotating speed change of the rotating component so as to change the momentum of the rotating component. By using the high-precision and high-response parallel type linear ultrasonic motor, the control moment gyro is long in service life, small in size, lightweight, high in control precision, fast in response, short in action time and especially suitable for the precise control of the posture and rapid maneuver of a small spacecraft.

Description

technical field [0001] The invention belongs to the technical field of torque control gyro, relates to an aerospace executive mechanism for a space maneuvering platform to realize fast maneuvering tasks, and is an ultrasonic motor control torque gyro that can meet the test conditions of satellite mechanical environment, specifically refers to a parallel linear ultrasonic Motor driven control torque gyroscope. Background technique [0002] In order to adjust the attitude of the spacecraft in orbit to achieve specific purposes, such as aligning the observation equipment carried in a certain direction, there are currently two types of implementation methods. Among them, the control moment gyroscope consumes power and has an unlimited working life Based on the quality of fuel carried from the ground, it is widely used in long-term orbital vehicles. [0003] However, the existing torque control gyros are all driven by electromagnetic motors to control the torque of the gyro. Du...

Claims

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Application Information

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IPC IPC(8): G01C19/02
CPCG01C19/02
Inventor 潘松唐洪权陈雷
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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