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Method for testing the influence of vibration reduction device on performance of inertial navigation system

A technology of inertial navigation system and vibration damping device, which can be applied to measurement devices, instruments and other directions, and can solve problems such as affecting the measurement accuracy of inertial devices and changing the motion characteristics of inertial devices.

Pending Publication Date: 2019-11-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

However, it also makes the inertial device no longer fully sensitive to the motion information of the carrier, changes the motion characteristics of the inertial device in a dynamic environment, and thus affects the measurement accuracy of the inertial device

Method used

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  • Method for testing the influence of vibration reduction device on performance of inertial navigation system
  • Method for testing the influence of vibration reduction device on performance of inertial navigation system
  • Method for testing the influence of vibration reduction device on performance of inertial navigation system

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specific Embodiment approach

[0095] 1. Establish the gyro error model before and after installing vibration reduction

[0096] The accuracy of the gyroscope is the decisive factor for the accuracy of the inertial navigation system. For inertial sensor components, its main error sources include non-orthogonal coupling error, scale factor error, zero bias and random error, etc., and its error model is:

[0097]

[0098] In the formula: is the actual output of the gyro, ω b is the error-free gyro output, ε b is the zero bias of the gyroscope, ω s is the scaling factor error, ω θ is the non-orthogonal coupling error, ω G is the acceleration sensitive error, and η is the random noise item.

[0099] 1) Gyro zero bias

[0100]

[0101] In the formula, is the component of the gyroscope zero bias on the three axes of the gyroscope.

[0102] 2) Gyro scaling factor error

[0103]

[0104] In the formula, is the gyroscope scaling factor error coefficient matrix.

[0105] 3) Gyro acceleration s...

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Abstract

The invention relates to a method for testing the influence of a vibration reduction device on the performance of an inertial navigation system and belongs to the technical field of the error calibration of inertial navigation inertial sensors. The method includes the following steps of (1) establishing a conventional gyro error model, wherein gyro errors include a gyro installation error, a scalefactor error and a random drift error, (2) considering the influence generated after the introduction of the vibration reduction device with the three types of errors and establishing a new error model, (3) providing error data for the quantitative evaluation of gyroscope performance by using the two types of error models through a calibration test, and verifying the validity of the gyroscope simulation data, and (4) analyzing the influence of an antenna attitude angle error according to the obtained error data and further analyzing the influence of the addition of a vibration isolation devices on the attitude solution. According to the method, an inertial device error model after adding the vibration reduction device is established, the influence of the vibration reduction device on theprecision of the navigation system is analyzed, and corresponding conclusions are verified through experiments and simulations.

Description

technical field [0001] The invention relates to a method for testing the influence of a vibration reduction device on the performance of an inertial navigation system, and belongs to the technical field of error calibration of inertial navigation inertial sensors. Background technique [0002] Inertial navigation system is the main navigation equipment for many carriers such as aviation, land and water. The inertial device is the main component of the inertial navigation system. The error of the inertial device is an important factor affecting the performance of the inertial navigation system. Its accuracy directly determines the performance of the inertial navigation system. When the carrier is running, the vibration environment of the body will cause the performance of the inertial device to decline, thereby affecting the navigation accuracy. The vibration environment is uncertain and untimely. Under the high-speed flight of the aircraft, it is very likely that the instal...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C25/00
CPCG01C25/005
Inventor 景羿铭熊智赵曜王融许建新熊骏陈明星王铮淳李文龙孙瑶洁徐丽敏
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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