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Platform inertial navigation gyro constant drift calibration method

A calibration method and gyro technology, applied in the field of inertial navigation system calibration, can solve the problems of long temperature constant time, affecting the quasi-navigation accuracy of the system, and poor stability of inertial components.

Active Publication Date: 2011-01-05
中国航空工业集团有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In this case, when the initial temperature of the inertial components is low, the system heats them up to the working point temperature and keeps it at 73°C. The temperature is kept constant for a long time, and the inertial components are aligned within 8 minutes. Poor stability makes the gyro constant value drift test inaccurate and affects the system alignment and navigation accuracy

Method used

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  • Platform inertial navigation gyro constant drift calibration method
  • Platform inertial navigation gyro constant drift calibration method
  • Platform inertial navigation gyro constant drift calibration method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0099] Test the inertial navigation system 01, the nose points to the geographical north direction. Use for the first time at room temperature, when the component T0 = 18.2 ℃; stop for 1 hour after shutdown, when the component T0 = 50.6 ℃; stop for 3 hours after shutdown, when the component is at T0 = 28.1 ℃; compass alignment method test and calculation get:

[0100] T0=18.2℃ Ex0=0.451 Ey0=1.024 Ez0=0.892 ΨT=6′

[0101] T0=50.6℃ Ex0=0.452 Ey0=1.033 Ez0=0.925 ΨT=3′

[0102] T0=28.1°C Ex0=0.452Ey0=1.033Ez0=0.925ΨT=-5'

Embodiment 2

[0104] Test the inertial navigation system 02, the nose points to the geographic south direction. Stop using for 10 minutes after shutdown, when component T0=68.1℃; stop using for 1.5h after shutdown, when component T0=30℃; stop using for 30min after shutdown, when component is at T0=56.9℃; compass alignment method test and calculation get:

[0105] T0=68.1℃ Ex0=-0.653 Ey0=0.750 Ez0=-1.456 ΨT=180°1′

[0106] T0=30℃ Ex0=-0.652 Ey0=0.743 Ez0=-1.477 ΨT=180°4′

[0107] T0=56.9℃ Ex0=-0.654 Ey0=0.755 Ez0=-1.441 ΨT=179°56′

Embodiment 3

[0109] Test the inertial navigation system 03, the nose points to the geographic west direction. 4h after shutdown, component T 0 =23.5°C; 5 hours after shutdown, components T 0 =23.1℃; 8h after shutting down, the components are at T 0 =22.9℃; compass alignment method test and calculation:

[0110] T 0 =23.5℃E x0 =0.345E y0 =-0.432E z0 =-0.675 Ψ T =269°55'

[0111] T 0 =23.1℃E x0 =0.345E y0 =-0.432E z0 =-0.675 Ψ T =269°54'

[0112] T 0 =22.9℃E x0 =0.345E y0 =-0.432E z0 =-0.675 Ψ T =270°5'

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Abstract

The invention belongs to an inertial navigation system calibration technology and relates to a platform inertial navigation gyro constant drift calibration method for an inertial navigation system. In the invention, the gyro constant drift cam be accurately calibrated in the use course of system equipment, therefore, the additional work of periodically calibrating gyro constant drift is avoided, and the alignment accuracy and the navigation accuracy of the system are improved. The invention can ensure that the gyro constant drift is accurately tested and revised in the alignment course of an compass of the inertial navigation system; the alignment and the navigation errors because of the incorrect test and revise of the gyro constant drift under the condition of low initial temperature of inertial components can be avoided; the manpower and the material resources for detection and screening are saved; the efficiency and the use survival rate are enhanced; and the use survival rate of the inertial navigation system is enhanced from 50% to above 80% after the method is utilized.

Description

technical field [0001] The invention belongs to the calibration technology of an inertial navigation system, and relates to a method for calibrating constant value drift of a platform inertial navigation gyro of the inertial navigation system. Background technique [0002] When the inertial navigation system is used at a low ambient temperature or for the first time every day, it is difficult to meet the performance index requirements for compass alignment, which has had a negative impact on the delivery and equipment use of the inertial navigation system. In the case of low initial temperature of the inertial components of this type of inertial navigation system, due to its poor fast stability, it affects the compass alignment accuracy and navigation accuracy. [0003] The alignment time of the inertial navigation system is only 8 minutes. The compass alignment scheme is: 1. System startup; Test and correct gyro constant drift in . [0004] In this case, when the initial ...

Claims

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Application Information

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IPC IPC(8): G01C25/00
Inventor 张朝霞
Owner 中国航空工业集团有限公司
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