Method for calibrating inertial platform system gyroscope torquer coefficient

An inertial platform and calibration method technology, which is applied in the field of inertial platform system calibration, can solve the problems of inability to correctly respond to the rotation angle of the vertical gyroscope, high requirements for the levelness of the platform system base, and torque device calibration errors, etc., to improve environmental adaptation Sex, reduce measurement error, reduce the effect of requirements

Active Publication Date: 2017-08-22
BEIJING INST OF AEROSPACE CONTROL DEVICES
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Problems solved by technology

The disadvantages of this method are: ① When the base of the inertial platform system is not level, the measured value of the frame angle in the vertical direction cannot correctly reflect the rotation angle of the vertical gyroscope, which will cause a calibration error of the torque device, and the level of the base of the platform

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  • Method for calibrating inertial platform system gyroscope torquer coefficient
  • Method for calibrating inertial platform system gyroscope torquer coefficient
  • Method for calibrating inertial platform system gyroscope torquer coefficient

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Example Embodiment

[0020] The specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0021] Such as figure 1 As shown, the inertial platform system torque device calibration system used in the present invention includes an inertial platform system 1, a platform circuit box 3, a platform test cabinet 4, and a placement base 2. The inertial platform system 1 includes a platform, a base, Gyroscope and frame angle sensor; frame angle sensor uses dual-channel multi-pole resolver, the number of pole pairs is generally 32, 64, etc.; place the inertial platform system 1, the platform circuit box 3 on the placement base 2, the platform circuit box 3 is connected to the inertial platform system 1, the platform circuit box 3 is used to supply power to the inertial platform system 1 and to control and monitor the normal operation of the platform body, the platform test cabinet 4 is connected to the platform circuit box 3, and the platform t...

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Abstract

The invention provides a system for calibrating an inertial platform system gyroscope torquer coefficient. The inertial platform system is placed on a placing pedestal, power is on till work is normal, and rotation of a platform body is carried out, so that a calibrated gyroscope is in a vertical position; a platform body horizontal axis is accurately locked and controlled according to a horizontal direction frame angle; start time of a positive direction torque applied to the gyroscope and a negative torque applied to the direction gyroscope is recorded, and stop time of a positive direction torque applied to the gyroscope and a negative torque applied to the direction gyroscope is recorded. The coefficient is obtained by calculating vertical direction framework angle sensor pole pairs. The calibrating method reduces requirements on unlevelness of the platform system placing pedestal, and improves calibrating precision of the torquer coefficient.

Description

technical field [0001] The invention relates to a method for calibrating coefficients of a gyro torquer in an inertial platform system, which can be used in calibrating the coefficients of a gyroscope torquer in a missile or weapon platform system, and belongs to the field of inertial platform system calibration. Background technique [0002] The inertial platform system generally consists of three gyroscopes, and each gyroscope contains a gyroscope torquer. The error coefficient of the inertial platform system needs to be calibrated before the missile or weapon system is launched. The gyroscope calibration generally adopts the force feedback method. The method needs to calibrate the coefficient of the gyroscope torquer first, the calibration accuracy of the gyroscope torquer affects the calibration accuracy of the platform system, and then affects the accuracy of the missile or weapon system landing point. [0003] The current method for calibrating the coefficients of the ...

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 马龙魏宗康余贞宇
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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