Light assembling structure for optical fiber gyro-space application
A technology of fiber optic gyroscope and combined structure, applied in the direction of Sagnac effect gyroscope, etc., can solve the problems of low reliability, difficult to maintain volume, etc., and achieve the effect of high reliability, firmness and stability of the instrument, and low power consumption
Inactive Publication Date: 2010-05-12
BEIHANG UNIV
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Problems solved by technology
[0006] The technology of the present invention solves the problem: it overcomes the disadvantages of low reliability, difficult maintenance and large size of the traditional mechanical gyroscope due to the moving parts, and the light fiber optic gyroscope combination provided has compact structure, small size, light weight and low thermal resistance. Small size, high reliability, good heat transfer performance and vibration performance, very suitable for attitude control of space vehicles
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[0021] Such as figure 1 As shown, the x-axis gyro 3 and the y-axis gyro 4 are respectively installed on the outside of the side of the body 5, the z-axis gyro 7 is located under the connector board 1 and installed on the inside of the bottom plate of the body 5, the x-axis gyro 3 and the y-axis gyro 4 , z-axis gyroscopes 7 are perpendicular to each other, forming an orthogonal system, respectively sensitive to the angular velocity of the x-axis, y-axis and z-axis in the orthogonal coordinate system, and the position information of the spacecraft can be obtained by integrating the angular velocity of the three axes, so as to measure the satellite attitude information. The bottom surfaces of the three fiber optic gyroscopes are in full contact with the mounting surface of the main body 5, so as to increase the heat conduction area between the lower surface of the gyroscope and the main body, reduce the thermal resistance, and improve the heat transfer performance; at the same tim...
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Optical fiber peg-top space applied light combination structure has a perpendicular configuration reality and its side faces are vertical with the underside. The outside of two side faces and the inside of underside are the fixing plane to three peg-tops. The rest side faces use to fix the electrical source box and cube mirror. The three peg-tops are perpendicular setting, and the peg-top of x axis and y axis is fixed on the outside of the reality side faces, the peg-top of z axis is fixed on the inside of the reality underside. Their fixing surfaces contact completely to increase the heat exchange area of the peg-top to reduce the heat resistance effectively. The three joining pieces connecting with peg-tops fix on one joining piece plane and put the three joining piece planes into one toconnect with the jack of the reality connecting with system. The three peg-tops can debug alone and this is fit for fixing and maintenance the optical fiber peg-top. It is suitable for the gesture controlling of the space aerocraft with small volume, light weight, little heat resistance, high reliability security, well diathermancy.
Description
technical field [0001] The invention relates to a light fiber optic gyroscope composite structure suitable for space application. 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 gyroscope as a whole can fully meet the needs of various applications in space. [0003] Based ...
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IPC IPC(8): G01C19/72
Inventor 肖文刘德文杜新政韩艳玲李瑞魏博
Owner BEIHANG UNIV