Carrier posture measuring method suitable for optical fiber gyroscope

Abstract

The invention discloses a measuring method for a carrier gesture of an optical fiber gyro, which comprises determining an initial position parameter and an initial speed value of a carrier through an external device, initially aligning strapdown inertial navigation system of the optical fiber gyro, determining an initial gesture of the carrier which is relative to a navigation coordinate system, obtaining an initial value of a gesture hypercomplex number, determining a gesture renewal cycle H = tm-tm-1, calculating a increment delta phi of rotating vector through collecting a carrier which is output by the optical fiber gyro which is corresponded to an angle speed of the inertial coordinate system, obtaining a gesture renewal hypercomplex number q(H) of the gesture renewal cycle H through a relation of the rotating vector and the hypercomplex number, renewing the gesture hypercomplex number through a renewal equation of the gesture hypercomplex number, calculating a strapdown matrix T that a carrier coordinate system b is relative to a navigation coordinate system n, and obtaining a gesture angle of the carrier which is relative to the navigation coordinate system and the like. The invention solves the problem that a cone effect influences a measuring accuracy of the carrier gesture under a high dynamic environment of a carrier or a high-frequency vibration environment.

Description

(1) Technical field [0001] The invention provides a measurement method, specifically a method for measuring attitude parameters of a carrier relative to a navigation coordinate system by using an optical fiber gyroscope. (2) Background technology [0002] In a strapdown inertial navigation system, inertial sensors (gyroscopes and accelerometers) are fixed directly on the carrier. They are sensitive to the attitude change and speed change information of the carrier relative to the inertial coordinate system. These information are processed by the navigation computer to output the navigation parameters, so as to complete the navigation guidance task. Due to the fixed connection of inertial sensors, the inertial sensors will be directly sensitive to the vibration of the carrier and the interference of the environment, which will have a certain impact on the measurement accuracy of the strapdown inertial navigation system. In the strapdown inertial navigation system, a mathemat...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a carrier attitude measurement method suitable for fiber optic gyroscopes that can solve the problem that the cone effect affects the accuracy of carrier attitude measurement in a carrier high dynamic environment or high frequency vibration environment

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