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Upper end cover assembly of flexible strapdown gyroscope

A cover assembly, gyro technology, applied in the direction of electric assemblies, electrical components, chassis/cover/support, etc., can solve the problem of reducing the size of the gyro, the distance between the gyro motor and the signal device, the torque device, the electromagnetic interference of the motor and the heat generation The signal device has a large influence, so as to reduce the assembly workload, reduce the volume, and facilitate the volume.

Inactive Publication Date: 2013-05-08
FLIGHT AUTOMATIC CONTROL RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] For this traditional structure, its shortcomings are: the distance between the gyro motor and the annunciator and torquer is close, and the electromagnetic interference and heat generation of the motor have a greater impact on the annunciator and torquer; on the other hand, it is difficult to effectively reduce the volume of the gyro with this structure

Method used

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  • Upper end cover assembly of flexible strapdown gyroscope
  • Upper end cover assembly of flexible strapdown gyroscope
  • Upper end cover assembly of flexible strapdown gyroscope

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Embodiment Construction

[0012] The present invention will be described in detail below in conjunction with the accompanying drawings. Such as image 3 As shown, a flexible strapdown gyroscope upper end cover assembly includes four sets of signaler cores 1, torquer stator assembly 2, 12 insulators 3, upper end cover 4, and film cable 5. It is characterized in that four sets of U-shaped The signaler core 1 is evenly distributed on the outer ring circumference of the inner plane of the upper end cover 4, and is fixedly connected with the upper end cover 4 of the gyro as a whole and directly processed and formed. The upper end surface of the rotor 13 is used as the armature of the signaler, and the eight signaler coils 6 are sequentially formed. Set at both ends of four sets of U-shaped signal generator cores 1; 12 insulators 3 are evenly sintered in the middle of two adjacent groups of signal device cores 1 in groups of three, serving as the lead wires of signal device coil 6 and torque device coil 9 i...

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Abstract

The invention belongs to the technical field of design and relates to an upper end cover assembly of a flexible strapdown gyroscope. In the invention, the strapdown gyroscope is divided into an upper body and a lower body, so that the influence of electromagnetic interference and heat emission of a gyro motor on an announciator and a torquer is reduced and the upper end cover assembly has an obvious effect of improving the accuracy of a small gyroscope; the processing on an announciator iron core is completed on an upper end cover of the gyroscope, so that the integration of the announciator iron core and the upper end cover is realized, the volume of the gyroscope is effectively shortened, and the number of parts and the assembly workload are reduced; and a torquer assembly is arranged on the upper end cover, so that the influence of heat emission of a large current on the performance of the gyroscope when the gyroscope works under a high angular speed is reduced.

Description

technical field [0001] The invention belongs to the technical field of design and relates to a flexible strapdown gyroscope upper end cover assembly. Background technique [0002] For the flexible strapdown gyroscope, when the shell rotates around the direction perpendicular to the drive shaft, the deflection angle is detected by the angle signal device installed on the shell in the direction of the two coordinate axes perpendicular to each other and an electrical signal is output; the signal is passed through The force feedback amplifier, through the calibration resistor R, is added to the corresponding torque device coil to generate torque to make the rotor precess until the deflection angle is zero; at this time, the torque device current is proportional to the angular velocity, and the voltage value on the calibration resistor reflects The angular velocity of the carrier. Therefore, the structure and performance of the annunciator and torquer directly determine the stru...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H02K5/04H02K15/14
Inventor 许可丰赵永峰杨以才何玮
Owner FLIGHT AUTOMATIC CONTROL RES INST
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