Single bus design method for space application optical fiber gyroscope assembly

A technology of fiber optic gyroscope and design method, which is applied in the direction of Sagnac effect gyroscope, etc., can solve the problems of weight and reliability reduction, and achieve the effect of improving reliability, strong interchangeability, and improving autonomy

Inactive Publication Date: 2009-09-09
BEIHANG UNIV
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  • Abstract
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  • Claims
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Problems solved by technology

The existing 3 fiber optic gyroscopes have a multi-bus structure, that is, the 3 fiber optic gyroscopes are connected to the electrical system through 3 data buses, so that the weight and reliability of the system are relatively reduced

Method used

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  • Single bus design method for space application optical fiber gyroscope assembly
  • Single bus design method for space application optical fiber gyroscope assembly
  • Single bus design method for space application optical fiber gyroscope assembly

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Embodiment Construction

[0012] Such as figure 1 As shown, the x-axis gyro, y-axis gyro, and z-axis gyro are respectively connected to the bus and connected to the system through the bus. The receiving data lines of the 3 gyroscopes are hung on a bus and connected with the system sending data lines, and the sending data lines of the 3 gyroscopes are hung on a bus and connected with the system receiving data lines. The identification codes of 3 gyroscopes are agreed in advance, and the system sends an identification code to the 3 gyroscopes at the same time. The gyroscopes with matching identification codes occupy the bus and send data to the system, and release the bus after sending data. The identification codes of the x-, y-, and z-axis gyroscopes in the present invention are B1000104, C2000104, and D3000104 respectively.

[0013] The three gyroscopes use three independent interfaces respectively, and the three gyro interface sockets, namely gyro socket 1, gyro socket 2 and gyro socket 3 use J30-25...

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Abstract

A single-bus design method for space application optical fiber gyroscope combination, characterized in that: the system circuit and the gyroscope interface are connected by bus, the receiving data lines of the three gyroscopes are hung on a single bus and connected with the system sending data lines, and the three gyroscopes The sending data line is hung on a bus and connected to the system receiving data line. The system and the gyroscope adopt a master-slave communication method. The system is the calling party. The identification codes of three gyroscopes are agreed in advance, and the system sends an identification code to the three gyroscopes at the same time. , the gyroscope whose identification code matches occupies the bus and sends data to the system, and releases the bus after sending data. The invention can transmit data conveniently, quickly and accurately, and can select the required information according to the requirements of the system, has strong initiative, improves reliability, reduces weight, and each gyroscope can be individually debugged, and the interchangeability is excellent. powerful.

Description

technical field [0001] The invention relates to an interface design for space application of an optical fiber gyroscope, in particular to a single-bus design method for a space application optical fiber gyroscope combination. Background technique [0002] In recent years, fiber optic gyroscope (FOG) has attracted much attention due to its potential advantages and application prospects, and has become the dominant device in the new generation of inertial guidance and measurement systems. With the in-depth study of fiber optic gyroscopes, various key problems of fiber optic gyroscopes have been gradually solved, and the performance of fiber optic gyroscopes has been continuously improved. Now the fiber optic gyroscope has been integrated and digitized. The zero drift of the fiber optic gyroscope developed abroad has reached within 0.001° / h, the stability of the calibration factor is better than several ppm, and the measurement accuracy has reached 0.0003° / h. The fiber optic ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C19/72
Inventor 肖文伊小素刘德文韩艳玲李瑞刘洋魏博
Owner BEIHANG UNIV
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