Earth rotation correction method and system under laboratory coordinate system

Abstract

The embodiment of the invention discloses an earth rotation correction method and system under a laboratory coordinate system. The method comprises the steps of establishing a laboratory launch coordinate system based on geographic latitude lambda <eT> and launch azimuth A <tT> of a three-axis flight rotary table and a laboratory reference coordinate system through a right-hand rule; establishinga three-axis flight rotary table instruction coordinate system according to the bias condition of the rotary table; establishing a laboratory launch coordinate system based on rotary table bias according to the bias condition of the rotary table to obtain geographic latitude lambda < e > <*> and launch azimuth A < t > <*> under the laboratory launch coordinate system based on rotary table bias; and carrying out earth rotation correction and acceleration compensation under the laboratory launch coordinate system based on rotary table bias through a missile-borne information processor based on the geographic latitude lambda < e > <*> and the launch azimuth A < t > <*> during semi-physical simulation test. According to the method and system, the problem that the distortion occurs when the earth rotation angular velocity is measured through an inertial measurement unit in a laboratory environment is solved, and the earth rotation influence caused by mismatching between a launching site anda laboratory is avoided.

Description

technical field [0001] The embodiments of the present application relate to the field of simulation technology, and in particular to a method and system for correcting the earth's rotation in a laboratory coordinate system. Background technique [0002] Hardware-in-the-loop simulation is an important verification method for missile guidance and control system development, algorithm prediction, parameter optimization and flight test prediction. During the flight of the missile, the inertial measurement device is used to measure the angular velocity information and acceleration information of the missile, and send them to the information processor on the missile for guidance circuit calculation. The on-board information processor constructs a launch coordinate system based on the bound launch location and launch azimuth, and uses the measurement information of the inertial measurement device to perform earth rotation correction and acceleration compensation. [0003] In the h...

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Problems solved by technology

[0004] For this reason, the embodiment of the present application provides a method and system for correcting the earth's rotation in the laboratory coordinate system, which considers the inconsistency of the earth's rotation between the hardware-in-the-loop simulation and the actual flight of the missile, and solves the problem of inertial measurement device measurement in the laboratory environment. Earth rotation angular velocity distortion issue, corrected for Earth rotation effects where the launch location and lab didn't match

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