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An Error Calibration Method for a Single-Axis North Finder

An error calibration and north finder technology, applied in the field of inertial navigation, can solve the problems of incapable error model and calibration method calibration and compensation, etc.

Active Publication Date: 2018-05-22
BEIJING INST OF AEROSPACE CONTROL DEVICES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Different from the traditional inertial navigation system with three gyroscopes and three plus meters, the single-axis north finder is only equipped with a single gyroscope and a single accelerometer, which cannot be calibrated and compensated according to the existing error model and calibration method, so the system must be re-analyzed To establish the error model and error calibration method suitable for single-axis north finder

Method used

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  • An Error Calibration Method for a Single-Axis North Finder
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  • An Error Calibration Method for a Single-Axis North Finder

Examples

Experimental program
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Embodiment

[0131] 1). Install the single-axis north finder on the turntable so that the carrier system coincides with each axis of the turntable. Start the north finder to control the single-axis north finder instrument system OXYZ to rotate around the OZ axis, so that the OY axis is locked at zero. Adjust the three-axis turntable to make the single-axis north finder carrier OX b Y b Z b Stand still at 4 different positions, and sample the average value of the pulse number of the gyroscope at Δt=60s, as shown in Table 1.

[0132] Table 1 Four-position test sampling data

[0133]

[0134] And calculate the instrument system OXYZ and the carrier system OX b Y b Z b The zero deflection angle Δφ=23.441571°;

[0135] 2). Adjust the three-axis turntable so that the instrument system OXYZ of the single-axis north finder is placed at 10 different positions, and collect the pulse numbers of the gyroscope and accelerometer after Δt=60s, as shown in Table 2.

[0136] Table 2 Ten position...

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Abstract

An error calibration method of an uniaxial north seeker comprises the following steps: firstly driving a rotary table to carry out four-position testing, and calibrating control drift angle between an instrument system and a carrier system of the uniaxial north seeker; then using the instrument system of the north seeker as a calibration coordinate system and controlling the rotary table to carry out corresponding position and rate testing; and finally finishing calculation of each error coefficient according to an error model of the uniaxial north seeker. The problem of indeterminate angle relation between the carrier system and the instrument system of the uniaxial north seeker is solved, and by the simple uniaxial north seeker's error compensation model and position and rate calibration method, error calibration of the uniaxial north seeker is realized. The calibration method is less time-consuming, has simple calculation and can be used to rapidly complete calibration test.

Description

technical field [0001] The invention provides an error calibration method for a single-axis north-finder, which is suitable for the occasion of north-seeking by using a single gyroscope and a single accelerometer, and belongs to the technical field of inertial navigation. Background technique [0002] The single-axis north finder is composed of a single gyroscope, a single accelerometer and the corresponding rotating mechanism device. The gyroscope and accelerometer are installed on the north finder body. Encoders and rotating mechanisms are installed at both ends of the body, which are controlled by the control algorithm. The rotating mechanism drives the body to perform multi-position rotation, and then uses the output data of the gyroscope and accelerometer at each position to perform north-seeking calculation. [0003] The single-axis north finder uses the body instrument system as the reference to sample the data of the gyroscope and accelerometer, but the north finding...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 郭涛张浩曾宪超靳猛管伟涛蒋鸿翔纪文涛
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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