Gyro magnetic compass system test adapter

A technology of a gyro system and an adapter is applied in the experimental field of aircraft navigation system, which can solve the problems of complex operation, heavy workload, and hidden safety hazards of airborne parts, and achieves the effect of simple operation, reduction of failure rate of general assembly, and ease of fault location.

Active Publication Date: 2016-03-30
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This method is complicated to operate and has a large workload. It is directly operated on the aircraft. Once a fault occurs, it is difficult to locate and eliminate the fault, which brings great safety hazards to the airborne components.

Method used

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  • Gyro magnetic compass system test adapter
  • Gyro magnetic compass system test adapter

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0029] The working power supply is composed of DC power supply and AC power supply.

[0030] In the DC power input circuit, the DC power input terminal "28VDC+" is connected to the 101 position of the ammeter calibration switch S03 through the DC power switch S01 and the fuse F013A, and through the protection resistor R01510Ω, the DC power indicator L01 is grounded; the DC power input terminal "28VDC-" is grounded; ammeter M01 with a range of 3A is connected in series between terminals 1 and 2 of switch S03, and the two ends are respectively connected to TEST+ and TEST– calibration terminals; position 201 of switch S03 is connected to T1 terminal of J01 socket and J03 socket The Z3 end is connected with one end of the lighting switch S04; the other end of the switch S04 is connected with the X3 end of the J03 socket.

[0031] When there is 28V DC input, close S01, the indicator light L01 lights up; close S03, the ammeter indicates the working current. The DC 28V power supply ...

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Abstract

The invention belongs to the technical field of experiments of navigation systems of aircrafts, and particularly relates to a test adapter for a gyro magnetic compass system. The adapter comprises a socket (J01), a socket (J02), a socket (J03), a direct current power input circuit and an alternating current power input circuit, wherein the socket (J01) is connected with a directional gyro system; the socket (J02) is connected with a magnetic flux valve; the socket (J03) is connected with a compensation device; the direct current power input circuit and the alternating current power input circuit are used for providing power for the adapter. The test adapter for the gyro magnetic compass system is small in size, easy to operate and high in test precision, and can be used for effectively detecting each performance index of the gyro magnetic compass system; a failure point of a failing finished product can be rapidly positioned in a checking state of a laboratory, finished product manufacturing defects can be timely and effectively discovered, the occurrence of failures in a final assembly process is greatly reduced, and hidden dangers in loading are reduced.

Description

technical field [0001] The invention belongs to the technical field of aircraft navigation system experiments, in particular to a gyro magnetic compass system test adapter. Background technique [0002] The gyro magnetic compass system is a commonly used instrument system for Y12 fixed-wing aircraft. It consists of three parts: azimuth gyro system, magnetic flux valve and compensation device. The system combines the long-term magnetic heading information of the magnetic flux valve and the short-term heading information of the heading gyro in the azimuth gyro system to obtain accurate heading data X, Y, and Z synchronous data for the horizontal position indicator, The use and display of related equipment such as wireless electromagnetic indicators and channel indicators. The compensation device is used to eliminate any detection error of magnetic flux caused by the alternating earth magnetic field to the aircraft. [0003] When installing and debugging the gyro magnetic com...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C17/38
CPCG01C17/38
Inventor 宋巍宁春玲王海涛刘峰栾玉庆
Owner HARBIN
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