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Device and method for controlling satellite attitudes through liquid circuit valve

A satellite attitude and valve control technology, which is applied in the direction of aerospace vehicle guides, etc., can solve the problems of bearing wear, poor satellite attitude control, heat dissipation and lubrication, etc., to achieve the effect of reducing wear and good effect

Inactive Publication Date: 2012-01-04
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problem of poor effect of satellite attitude control due to serious bearing wear, poor heat dissipation and lubrication in the existing flywheel momentum exchange control satellite attitude, the present invention provides a device and method for controlling satellite attitude with a liquid loop valve

Method used

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  • Device and method for controlling satellite attitudes through liquid circuit valve
  • Device and method for controlling satellite attitudes through liquid circuit valve
  • Device and method for controlling satellite attitudes through liquid circuit valve

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specific Embodiment approach 1

[0023] Specific implementation mode 1. Combination figure 1 Illustrate this specific embodiment, the device that liquid circuit valve controls satellite attitude, it comprises three groups of satellite attitude control units, and the central axis of three groups of satellite attitude control units is respectively connected with the OX axis, OY axis and OZ axis in the three-dimensional Cartesian coordinate system OXYZ Parallel, the origin of the three-dimensional rectangular coordinate system OXYZ is the center of mass of the satellite body; the structures of the three groups of satellite attitude control units are exactly the same, and each group of satellite attitude control units includes forward loop 1, reverse loop 2, and loop control valve 3 , a motor 5 and a fluid pump 6; the forward loop 1 and the reverse loop 2 are arranged symmetrically along the central axis of the satellite attitude control unit where they are located; the output shaft of the motor 5 is connected wit...

specific Embodiment approach 2

[0049] Embodiment 2. The difference between this embodiment and the device for controlling the attitude of a satellite with a liquid loop valve described in Embodiment 1 is that the fluid pump 6 is a mechanical pump.

specific Embodiment approach 3

[0050] Embodiment 3. The difference between this embodiment and the device for controlling the attitude of satellites with liquid circuit valves described in Embodiment 1 is that it also includes radiation fins, which are fixed in each group of satellite attitude control units. The outer side of the forward loop 1 and the outer side of the reverse loop 2.

[0051] The radiating fins in this embodiment are used to radiate the waste heat in the star absorbed during the circulation into the space environment.

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Abstract

The invention relates to a device and method for controlling satellite attitudes through a liquid circuit valve, relating to the device and method for controlling satellite attitudes, and solving the problem of bad effect of control of satellite attitudes caused by serious bearing abrasion and poor heat radiation and lubrication in the traditional device adopting flywheel-type momentum interchange to control the satellite attitudes. In the device provided by the invention, a group of satellite attitude control units are respectively installed in the directions of three axles of a satellite body. The method provided by the invention comprises a step of controlling the quantity of flow entering a forward circuit and a backward circuit through a circuit control valve or a forward / reverse control valve so as to realize the control of the satellite attitudes. The device and method provided by the invention are suitable for the control of the satellite attitudes.

Description

technical field [0001] The invention relates to a device and method for controlling satellite attitude. Background technique [0002] At present, the actuators used for satellite active attitude control can be divided into mass discharge type, momentum exchange type and environmental field type according to the working principle. Among them, the momentum exchange method uses the angular momentum exchange between the momentum generating device inside the satellite and the satellite body to achieve attitude control. It has the advantages of no working fluid consumption, no pollution, and no interference to the movement of the satellite's center of mass. The flywheel is a typical example. The representative momentum exchange attitude control actuator is widely used in micro-satellites, but the high-speed rotation of the flywheel and the working life of the gyro support are very demanding. Ball bearings are the most common support method, but due to the friction between the bal...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
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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