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Compensation method for simulation input signal of navigation system

An input signal, navigation system technology, applied in the field of navigation system simulation, can solve the problems of attitude angle accuracy error, reduce inertial navigation accuracy, etc., to achieve the effect of improving authenticity and high engineering practical value

Active Publication Date: 2018-05-04
JIANGXI HONGDU AVIATION IND GRP
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Problems solved by technology

During the test, it was found that the inaccurate input angular velocity signal would lead to errors in the accuracy of the attitude angle calculated by the inertial navigation system and reduce the accuracy of the inertial navigation

Method used

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  • Compensation method for simulation input signal of navigation system
  • Compensation method for simulation input signal of navigation system
  • Compensation method for simulation input signal of navigation system

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Embodiment Construction

[0026] The present invention will be further described in detail below in conjunction with examples, but the embodiments of the present invention are not limited thereto.

[0027] The navigation system simulation input signal compensation method of the present invention, concrete steps are as follows:

[0028] 1) Design the simulated flight path according to the flight requirements, determine the three-axis angular velocity of the simulated flight path, the heading angle, pitch angle, roll angle, eastward speed, northward speed, and latitude of the simulated flight path;

[0029] 2) Calculate the earth rotation angular velocity component of the simulated flight path:

[0030]

[0031] Among them, ω ie is the angular velocity of the earth's rotation, L is the latitude of continuous change in the simulated flight path, and the coordinate system n represents the eastward, northward, and celestial geographic coordinate system;

[0032] 3) Calculate the angular velocity compon...

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Abstract

The invention relates to a compensation method for a simulation input signal of a navigation system. According to the method, a semi-physical simulation triaxial angular velocity input signal is compensated for an inertial navigation system by simulating a flight trajectory and attitude, velocity and latitude and longitude based on the attitude and latitude and longitude of semi-physical rate table. The method of the invention is suitable for the semi-physical simulation of a navigation calculation function of the navigation system, so that the authenticity of the inertial navigation ground simulation can be improved, and the engineering practical value is higher.

Description

technical field [0001] The invention belongs to the technical field of navigation system simulation, and relates to a navigation system simulation based on a speed turntable. Background technique [0002] When the existing inertial navigation system based on the three-axis rate turntable performs hardware-in-the-loop and physical-in-the-loop simulations, the heading angular velocity, pitch angular velocity, and roll angular velocity of the simulated flight path are mostly input into the turntable to control the rotation of the turntable. In this way, there is a difference between the angular velocity sensed by the inertial navigation system on the turntable and the theoretical value of the angular velocity when simulating the flight path design. During the test, it was found that the inaccurate input angular velocity signal would lead to errors in the attitude angle accuracy calculated by the inertial navigation system and reduce the inertial navigation accuracy. Contents ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00G05B17/02
CPCG01C25/005G05B17/02
Inventor 邱玉芬余聪李宇施成功吴克松邹小霞周学武孙伟星赵志权邹平王茹刘正兴黄桂明万蒋亮
Owner JIANGXI HONGDU AVIATION IND GRP