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Liquid circuit based gyroscopic moment generating device and satellite attitude control method

A gyro torque and generating device technology, which is applied in the direction of aerospace vehicle guidance devices, etc., can solve the problems of poor attitude control effect of the whole star, poor safety of ball bearings, short working life, etc., and achieve long working life, good safety and good effect. Good results

Inactive Publication Date: 2011-06-22
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The present invention aims to solve the problem of poor safety and short working life of the ball bearing and the whole star caused by the poor heat dissipation and poor lubricity of the existing ball bearing method to control the moment gyroscope, and the use of the magnetic levitation bearing method to control the moment gyroscope is easily affected by space radiation. The problem of poor attitude control effect of the whole satellite, thus providing a gyro torque generator and satellite attitude control method based on liquid circuit

Method used

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  • Liquid circuit based gyroscopic moment generating device and satellite attitude control method
  • Liquid circuit based gyroscopic moment generating device and satellite attitude control method
  • Liquid circuit based gyroscopic moment generating device and satellite attitude control method

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specific Embodiment approach 1

[0022] Specific implementation mode 1. Combination figure 1 and figure 2 Describe this specific embodiment, the gyro torque generating device based on the liquid circuit, it includes the annular rigid pipeline 2, the first motor 3, the second motor 4, the connecting pipe 5 and the fluid pump, the annular rigid pipeline 2 surrounds the satellite body 1 , and the center of the annular rigid pipeline 2 coincides with the center of the satellite body 1; the diameter of the annular rigid pipeline 2 is greater than the length of the body diagonal of the satellite body 1;

[0023] With the center of the satellite body 1 as the origin, a three-dimensional Cartesian coordinate system OXYZ is established; the No. 1 motor 3 is located on the positive semi-axis of the OZ axis, and the stator of the No. 1 motor 3 is fixed on the satellite body 1; the No. 1 motor 3 The torque output shaft is used to drive the stator of the No. 2 motor 4 to rotate around the OZ axis, and the axis O`Y` of t...

specific Embodiment approach 2

[0052] Embodiment 2. The difference between this embodiment and the liquid circuit-based gyro torque generating device described in Embodiment 1 is that the fluid pump is a mechanical pump.

[0053] In this embodiment, the fluid pump can be a mechanical pump, or any principle / mechanism that can circulate liquid, such as a device that uses thermoelectric effect combined with magnetic fluid to generate Lorentz force.

specific Embodiment approach 3

[0054] Specific embodiment three, based on the satellite attitude control method of the gyro torque generating device based on the liquid circuit described in specific embodiment one, its method is:

[0055] Fill the annular rigid pipeline 2 with a working medium liquid flow to form a liquid circuit in the annular rigid pipeline 2;

[0056] A fluid pump is used to control the liquid circuit to generate angular momentum along the X-axis direction;

[0057] The second motor 4 is used to drive the ring-shaped rigid pipeline 2 to control the torque gyro to rotate along the Y-axis direction to generate gyro torque along the Z-axis direction;

[0058] Using the No. 1 motor 3 to drive the annular rigid pipeline 2 to control the torque gyro to rotate along the Z-axis direction to generate gyro torque along the -Y direction;

[0059] The second motor 4 is used to drive the annular rigid pipeline 2 to control the torque gyro to rotate along the -Y axis direction to generate gyro torque...

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Abstract

The invention relates to a liquid circuit based gyroscopic moment generating device and a satellite attitude control method, relating to a liquid control moment gyroscope device and the satellite attitude control method and solving the problems of poor safety and short service life of the traditional method and poor integral satellite attitude control effect caused in such a way that the traditional method is easy to influence by cosmic radiation. A device 1 and an annular rigid pipeline surround the outer side of a satellite body, and the annular rigid pipeline rotates along an OY axis and an OZ axis through two motors. The satellite attitude control method comprises the following steps of: generating gyroscopic moments along the directions of the OY axis, the OZ axis, a -OY axis and a -OZ axis by controlling the two motors; and generating the gyroscopic moments along the directions of an OX axis and a -OX axis by controlling fluid pumps, therefore the control of satellite three-axisattitudes is realized. A device 2 and two annular rigid pipelines surround the outer side of a satellite body, and the two annular rigid pipelines respectively rotate along the OY axis and the OZ axis through the two motors. The invention is suitable for the control of moment gyroscopes and the satellite three-axis attitudes.

Description

technical field [0001] The invention relates to a liquid control moment gyroscope device and a satellite attitude control method. Background technique [0002] In existing systems for controlling moment gyroscopes, the gyroscope rotor needs to be installed on the gyroscope frame through a supporting device. The support device bears the high-speed rotation of the gyro rotor, and the gyro torque is transmitted to the carrier through the support device. High-speed rotation, large output torque and working life have high requirements on the gyro support device. Ball bearing is the most common supporting device, but due to the friction between the ball and the bearing frame, good heat dissipation and lubrication cannot be performed in a vacuum environment, which greatly affects the working life of the ball bearing and even the entire star. The magnetic suspension bearing has the advantage of response due to its non-contact, but the control of the magnetic suspension bearing has...

Claims

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Application Information

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IPC IPC(8): B64G1/28
Inventor 耿云海单晓微陈雪芹张世杰曹喜滨孙兆伟
Owner HARBIN INST OF TECH
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