Error processing method for output signal of optic fiber gyroscope component

A fiber optic gyroscope and output signal technology, which is applied in the field of signal processing of inertial sensors, can solve problems such as poor practicability, unsatisfactory error parameter calibration effect, and difficulty in obtaining error models.

Inactive Publication Date: 2008-07-16
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

The conventional fixed error calibration method often does not take into account the sensitivity of the FOG zero bias to temperature, resulting in unsatisfactory calibration of error parameters; the method of using Kalman filtering for random error processing is not practical because it is difficult to obtain a

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  • Error processing method for output signal of optic fiber gyroscope component
  • Error processing method for output signal of optic fiber gyroscope component
  • Error processing method for output signal of optic fiber gyroscope component

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Embodiment Construction

[0128] The main purpose of the present invention is to solve the problem that the conventional static calibration method does not consider the sensitivity of the fiber optic gyroscope zero bias to temperature, resulting in unsatisfactory error parameter calibration results, and to improve the Kalman filter, neural network filter, conventional LMS filter and other methods in the existing literature There are deficiencies in the accuracy, real-time, practicality, and dynamic input range of the random error processing of the fiber optic gyroscope. A complete, effective, high-precision and adaptable error processing process and method are proposed for the output signal of the fiber optic gyroscope component. It plays a very important role in improving the accuracy of inertial sensors and even the accuracy and performance of the entire inertial navigation system, and has guiding significance for the engineering application of fiber optic gyroscope components. In order to achieve thi...

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Abstract

The invention discloses an error processing method of the output signal of an optical-fiber scopperil component and belongs to the error processing methods of the output signal of an optical-fiber scopperil component in an inertial navigation system. The concrete steps of the processing method are that: an output signal model of the optical-fiber scopperil component and an error model thereof are built; the marking and the compensation of the fixed error of the optical-fiber scopperil component are implemented; the self-adaptive filtering of the random error of the optical-fiber scopperil component is implemented. The processing method effectively reduces the zero-offset drift of the optical-fiber scopperil component which is caused by temperature changes, has high marking precision of the fixed error, high marking efficiency and good adaptability; furthermore, the processing method effectively reduces the random error of optical-fiber scopperil, has small amount of computation, and is suitable for real industrial applications.

Description

1. Technical field [0001] The invention relates to a signal processing method of an inertial sensor in an inertial navigation system, in particular to an error processing method for an output signal of an optical fiber gyroscope assembly. 2. Background technology [0002] The inertial navigation system is based on Newton's relative inertial space mechanics law, using inertial sensors (including gyroscopes and accelerometers) to sense the angular velocity and acceleration of the vehicle, and obtain the navigation parameters such as the attitude, speed and position of the vehicle through integral operations. As the core component of the inertial navigation system, the inertial sensor is composed of three gyroscopes (gyroscope components) and three accelerometers (accelerometer components) whose sensitive axes are orthogonal to each other. The output error is an important factor affecting the accuracy of the inertial navigation system. [0003] The fiber optic gyroscope is an a...

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Application Information

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IPC IPC(8): G01C19/72G01C21/18H03H21/00
Inventor 刘建业祝燕华赖际舟曹华李荣冰凌冬于永军谢征
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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