Correction method for relative installation error between seeker and inertial measurement unit system

Abstract

The invention provides a correction method for relative installation errors between a seeker and an inertial measurement unit system. The method comprises: determining an installation angle of an initial antenna, performing flight tests to acquire data, performing image screening to obtain position information of a target in an image, determining coordinate values of the target in an ENU coordinate system with a carrier mass center as an original point, determining coordinate values of the target carrier in a posture coordinate system, and determining an antenna installation error correction value and correcting the installation angle of the initial antenna. The method dynamically and accurately measures under a test state, and comprehensively uses carrier posture information, position information, radar system parameters, and seeker imaging images and other data, and installation error correction precision and test data validity are improved.

Description

technical field [0001] The invention relates to a relative installation error correction method between a seeker head and an inertial group system, and belongs to the technical field of precision guidance. Background technique [0002] In modern warfare, in order to carry out long-range and real-time precise strikes on targets, it is necessary to solve the problem of weapon system platform and target precise detection means, to be able to reach the target area in real time, and to use detection means to accurately detect targets. Therefore, it is required that the weapon system adopts efficient guidance technology. Precise guidance depends on the guidance system. In the development stage, the guidance equipment needs to rely on the hang flight test in the real environment of the field to verify its guidance performance; in today's complex battlefield environment, there are various types of targets and complex environments. Acquisition and cognition of characteristics gradua...

AI Technical Summary

Problems solved by technology

[0003] The flight test generally uses an external pod or hanger to install the seeker on the hanging point outside the cabin through the adapter plate to detect ground or air targets. The control of the guidance system needs to be controlled by the attitude coordinate system of the carrier platform. Coordinate transformation, the attitude angle of the carrier is provided by the inertial group equipment, the guidance system and the inertial group system are installed on different parts of the carrier platform, and it cannot be guaranteed that they are installed on the same datum, and the installation process will cause relative installation errors between the guidance system and the integrated navigation system , ignoring the installation error will often cause a large field of view deviation of the seeker, which will seriously affect the performance of target detection, matching recognition, etc.

[0004] The existing methods for correcting the relative error between the seeker and the integrated navigation system, some use the position of the installation hole on the platform to correct. Due to factors such as insufficient hole position accuracy, this method will superimpose the error of the installation hole itself, and cannot achieve correctness. Effective correction of relative installation errors; some use ground tests to place angle mirrors or lay out optical targets in front of the carrying platform outdoors, and achieve correction by measuring information such as carrier positions and feature point positions. This method does not consider the platform during flight tests The influence of attitude and air environment on the correction accuracy belongs to static measurement. In addition, the situation that the seeker cannot be forward-looking after installation is not considered, which has limitations.

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