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Redundantly configured hemispherical resonator gyro inertia measurement assembly and method

A technology of hemispherical resonant gyro and inertial measurement components, which is applied in the field of inertial navigation to achieve the effect of light weight, small weight, and optimized performance of precision

Active Publication Date: 2020-04-24
NO 717 INST CHINA MARINE HEAVY IND GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Aiming at the technical problems existing in the prior art, the present invention provides a hemispherical resonant gyro inertial measurement component with redundant configuration and a measurement method, which solves the contradiction between the number of sensor configurations and the volume and weight of the redundantly configured inertial measurement component

Method used

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  • Redundantly configured hemispherical resonator gyro inertia measurement assembly and method
  • Redundantly configured hemispherical resonator gyro inertia measurement assembly and method
  • Redundantly configured hemispherical resonator gyro inertia measurement assembly and method

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Embodiment 1

[0046] Embodiment 1 provided by the present invention is the first embodiment of the sensor unit in a hemispherical resonant gyro inertial measurement component with redundant configuration provided by the present invention, as figure 1 and figure 2 Shown are respectively a disassembled and assembled structural diagram of Embodiment 1 of a sensor unit provided by the present invention.

[0047]In Embodiment 1 of a sensor unit provided by the present invention, the sensor unit is arranged obliquely, specifically, as image 3 Shown is a schematic diagram of the skew principle of Embodiment 1 of a sensor unit provided by the present invention.

[0048] Specifically, by figure 1 , figure 2 and image 3 It can be seen that the sensor unit 2 is arranged on the body 1, and the body 1 adopts a split design, including a left body 11 and a right body 12, and the sensor unit 2 includes a hemispherical resonant gyro 21 and an accelerometer 22, and the number of hemispherical resonan...

Embodiment 2

[0055] Embodiment 2 provided by the present invention is the second embodiment of the sensor unit in a redundantly configured hemispherical resonant gyro inertial measurement component provided by the present invention, as Figure 4 , Figure 5 and Figure 6 Shown are schematic structural diagrams of the first viewing angle, the second viewing angle and the third viewing angle of Embodiment 2 of a sensor unit provided by the present invention, respectively. In Embodiment 2 of a sensor unit provided by the present invention, the sensor units are arranged orthogonally.

[0056] Depend on Figure 4 , Figure 5 and Figure 6 It can be seen that in the second embodiment of a sensor unit provided by the present invention, the sensor unit 2 is arranged on the body 1, the sensor unit 2 includes a hemispherical resonant gyroscope 21 and an accelerometer 22, and the number of the hemispherical resonant gyroscope 21 and the accelerometer 22 is 6. The main body 1 includes gyro mount...

Embodiment 3

[0062] Embodiment 3 provided by the present invention is an embodiment of a redundantly configured hemispherical resonant gyro inertial measurement component provided by the present invention, such as Figure 7 Shown is a principle schematic diagram of a hemispherical resonant gyro inertial measurement component with redundant configuration provided by the present invention.

[0063] Depend on Figure 1-Figure 7 It can be known that the inertial measurement assembly includes a body 1 and a sensor unit 2 arranged on the body 1, a HRG (Hemispherical Resonator Gyro, hemispherical resonant gyro) circuit unit 3, an Acce (accelerometer, accelerometer) circuit unit 4 and a data signal processing unit 5 . The sensor unit 2 includes a hemispherical resonant gyro 21 and an accelerometer 22 . The main body 1 includes gyro mounting surfaces equal in number to the hemispherical resonant gyroscopes 21, and each hemispherical resonant gyroscope 21 is arranged on a corresponding gyroscope m...

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Abstract

The invention relates to a redundantly configured hemispherical resonator gyro inertia measurement assembly and method. The inertia measurement assembly comprises a body and a sensor unit arranged onthe body, and the sensor unit comprises hemispherical resonator gyros and an accelerometer; and the body comprises gyro mounting surfaces whose number equals that of the hemispherical resonant gyros,and each hemispherical resonant gyro is arranged on the corresponding gyro mounting surface. The problems that a traditional dual-redundancy configuration optical gyro inertia measurement assembly istoo large in size and weight and low in fault diagnosis and isolation rate are solved. The inertial measurement assembly is designed by adopting redundant configuration of the hemispherical resonatorgyros; by combining multiple excellent characteristics of small size, light weight and the like of the hemispherical resonator gyros, the inertial measurement assembly is smaller in size, lower in weight and better in fault diagnosis and isolation effects under the condition of the same precision as a mechanical gyro and an optical gyro, and the precision performance of the inertial measurement assembly is optimized and improved.

Description

technical field [0001] The invention relates to the technical field of inertial navigation, in particular to a hemispherical resonant gyro inertial measurement component with redundant configuration. Background technique [0002] The redundant configuration of the inertial navigation system is an effective means to improve the reliability and fault tolerance of the system, especially in long-duration and high-reliability applications such as ocean navigation and satellite attitude measurement, the redundancy design is used to achieve the reliability and service life of the inertial navigation system The substantial improvement has become a general consensus at home and abroad. [0003] The traditional redundancy configuration method of inertial navigation system is mainly to configure two or more sets of inertial navigation subsystems on one platform, and there is no mutual connection between the inertial navigation subsystems. The advantage of this method is that the design...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C19/56
CPCG01C19/56
Inventor 冷悦艾文宇刘和平杜勇张熙
Owner NO 717 INST CHINA MARINE HEAVY IND GRP
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