Miniaturized Liquid Buoyant Inertial Attitude Sensor for Microsatellites

An inertial attitude and micro-satellite technology, which is applied to navigation through velocity/acceleration measurement, integrated navigator, etc. The effect of reduction, less number of machined parts and simple assembly process

Active Publication Date: 2015-12-02
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Summary
  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

These three types of inertial attitude sensors contain 3, 6 and 4 heads respectively, with many parts, complex structure, difficult assembly and adjustment, and relatively large weight, volume and power consumption

Method used

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  • Miniaturized Liquid Buoyant Inertial Attitude Sensor for Microsatellites
  • Miniaturized Liquid Buoyant Inertial Attitude Sensor for Microsatellites
  • Miniaturized Liquid Buoyant Inertial Attitude Sensor for Microsatellites

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Embodiment Construction

[0026] Specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0027] Such as figure 1 and combine figure 2 As shown, the present invention discloses a miniaturized liquid-floating inertial attitude sensor suitable for microsatellites. The sensor includes a base 7 arranged on any plane. The base 7 is a flat plate structure, and the upper surface of the base 7 is arranged There is a mounting seat for installing the gyro meter head 10, and the mounting seat is provided with a horizontal gyro mounting hole. The power input of the gyro meter 10 is provided by the power amplifier board 3 , and the signal of the gyro meter 10 is output to the servo board 11 . The gyro gauge 10 is arranged in the gyro mounting hole in series, and the gyro gauge 10 is fixed in the gyro mounting hole by the pressure blocks 8 and screws arranged at the four vertices of the gyro mounting hole.

[0028] A power amplifier board supp...

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Abstract

The invention provides a miniaturized liquid-floated inertial attitude sensor suitable for a microsatellite, and the sensor comprises a seat arranged on an arbitrary plane, a gyro meter fixed on the seat by a pressing block and a screw, a power amplifier board bracket fixed on the seat and with the front side facing to the gyro meter, a power amplifier board vertically fixed on the front side of the power amplifier board bracket with the power amplifier board surface facing to the gyro meter, a miniaturized three-channel power operational amplifier arranged on the power amplifier board, a supporting column vertically arranged on the seat, a servo board erected on the supporting column and arranged above the gyro meter and the power amplifier board, and a modular rebalance circuit arranged on the servo board. The miniaturized liquid-floated inertial attitude sensor has the advantages of simple structure, less parts needing machining, simple assembly process, easiness in processing, assembly, adjustment and repair, low cost, suitability for mass production, substantial reduction of weight and volume, low power consumption, and suitability for the microsatellite with strict requirements on weight, size and power dissipation.

Description

technical field [0001] The invention relates to an inertial attitude sensor, in particular to a miniaturized single-degree-of-freedom liquid-floating inertial attitude sensor for mid-low orbit micro-satellites. Background technique [0002] With the development of aerospace technology, higher and higher requirements are put forward for the weight, volume and power consumption of various satellites, especially microsatellites, and corresponding requirements are also put forward for the supporting stand-alone machines and loads. [0003] At the present stage, liquid-floating inertial attitude sensors are composed of various forms. According to the installation method of the gyro head contained in the sensor, there are mainly three modes: 3 orthogonal, 6 orthogonal and 3+1S. These three types of inertial attitude sensors contain 3, 6 and 4 gauge heads respectively, with many components, complex structures, difficult assembly and adjustment, and relatively large weight, volume a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/16
CPCG01C21/24
Inventor 焦舰徐挺张明举李晓红吴勇应俊
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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