Method for measuring installation error coefficient of strap-down inertial navigation system and alignment prism

Abstract

The invention provides a method for measuring an installation error coefficient of a strap-down inertial navigation system and an alignment prism. Hardware facilities comprise a two-axis turntable, a strap-down inertial navigation system, an alignment prism, an autocollimation theodolite, a main control computer, a display, a keyboard and the like. The method comprises the following steps: changing collimation positions of the strap-down inertial navigation table, the alignment prism and the autocollimation theodolite by rotating the two-axis turntable twice, recording CCD (Charge Coupled Device) misalignment angle reading and horizontal plate reading beta of the autocollimation theodolite, inside and outside frame coded disc reading alpha of the two-axis turntable and strap-down inertial navigation output parameters twice by the main control computer, and resolving the installation error coefficient between the alignment prism and the inertial navigation system after an initial alignment manner of the alignment prism to the strap-down inertial navigation system is changed into a vertical installation manner.

Description

Technical field [0001] The invention belongs to the technical field of precision guidance initial alignment detection compensation for strapdown inertial navigation systems, and specifically relates to a method for measuring the installation deflection angle of strapdown inertial navigation and alignment prisms. Background technique [0002] At present, the strapdown inertial navigation initial alignment aiming prism is usually installed horizontally, but in order to achieve the accurate alignment of the aircraft's horizontal initial azimuth and launch immediately after erection, the strapdown inertial navigation initial alignment aiming prism needs to be installed vertically. The installation angle relationship between the initial alignment prism and the strapdown inertial navigation system has changed, which will inevitably cause the measurement method of the installation deviation angle between the initial alignment prism coordinate system and the strapdown inertial navigation ...

AI Technical Summary

Problems solved by technology

In the actual installation process, it is difficult to achieve absolute coincidence between the strapdown inertial navigation coordinate system and the alignment prism coordinate system, and there will be a certain installation deflection angle. If the installation deflection angle is not accurately measured and soft compensation is performed, the aircraft will have a fixed alignment In this context, a set of technology is proposed to use the normal vector of the inertial navigation alignment prism reflection surface to be equal to the laser alignment vector of the autocollimation theodolite, and calculate the alignment prism and inertial navigation installation deviation between

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