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A Closed-loop Compensation Method for Inertial Navigation System Heading Drift Error Applied to Communication in Motion

An inertial navigation system and heading drift technology, applied in the field of satellite communications, can solve problems such as the loss of satellite tracking accuracy of the antenna system in motion, and achieve high-precision solutions, long-term high-precision and stable tracking of satellite signals, and elimination of instrument accumulation. effect of error

Active Publication Date: 2017-11-28
BEIJING INST OF AEROSPACE CONTROL DEVICES
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Problems solved by technology

[0006] The technical problem of the present invention is to overcome the deficiencies of the prior art and provide a closed-loop compensation method for inertial navigation system heading drift error applied to communication in motion, which solves the problem that the inertial navigation system heading angle error accumulates over time and causes the error of communication in motion Antenna System Satellite Tracking Accuracy Compromise Problem

Method used

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  • A Closed-loop Compensation Method for Inertial Navigation System Heading Drift Error Applied to Communication in Motion
  • A Closed-loop Compensation Method for Inertial Navigation System Heading Drift Error Applied to Communication in Motion
  • A Closed-loop Compensation Method for Inertial Navigation System Heading Drift Error Applied to Communication in Motion

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Embodiment

[0057] 1. Set the control navigation period counter M, heading timer SCANFLAG and compensation flag MODIFLAG, the initial value is 0, the preset maximum voltage value XBMAX=4.3V, the step size SAngle=0.01°, the total amount of unilateral scanning ASINGLE=200;

[0058] 2. Control the navigation period counter M and the heading timer SCANFLAG to start counting, and when the navigation period counter M counts to 5ms, enter step (3);

[0059] 3. The inertial navigation system calculates the carrier's current pitch angle P=0.5°, roll angle R=0.5°, and heading angle Y=120.0°, then the antenna pitch angle fPitch=49.057437°, polarization angle fJihua=16.596453° and Antenna azimuth angle fYaw=9.373444°;

[0060] 4. Determine the heading timer SCANFLAG≥2min, if it is satisfied, then the antenna azimuth axis angle fYaw=fYaw+SAngle=9.373444°+0.01°=9.38344°, and drive the azimuth axis to rotate, at this time Sum=0.01°, SCnt=1, The real-time voltage value of the beacon read at the same tim...

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Abstract

A heading drift error closed-loop compensation method applied to communication-in-moving inertial navigation systemcomprises the following steps: first, after the completion of the system satellite alignment, the navigation control cycle is used for navigation solution and antenna tracking drive control; then a beacon signal is used as auxiliary information to obtain heading drift error by scanning, and drive an antenna azimuth shaft to rotate the satellite beacon signal strongest point; and finally heading angle error compensation is performed, and by use of the compensated heading angle, each strap-down matrix of the inertial navigation system is updated, and is introduced to the next time navigation period to achieve heading drift error strap-down navigation algorithm closed loop correction. The method is applicable to vehicle and ship and other communication-in-moving inertial navigation systems which are uninterruptible power in a long time.

Description

technical field [0001] The invention provides a course drift error compensation method of an inertial navigation system applied to communication in motion, which is suitable for occasions requiring the system to maintain the accuracy of antenna tracking satellites for a long time, and belongs to the technical field of satellite communication. Background technique [0002] The satellite tracking control of the "communication in motion" antenna system based on the inertial navigation scheme mainly relies on the inertial navigation system to be able to calculate the pitch, roll and heading angle information of the carrier in real time, and then guide the antenna to isolate the carrier movement through coordinate conversion to keep the antenna always pointing to the target satellite. Due to the drift error of the inertial instrument, the inertial navigation system will cause drift errors in the carrier attitude and heading angle calculated by the solution of the strapdown inerti...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C25/00
CPCG01C25/00G01C25/005
Inventor 郭涛杨明邬江王盛车鹏宇魏宗康
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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