Method and device for estimating line-of-sight angle zero error by using active radar seeker

Abstract

The invention provides a method and a device for estimating line-of-sight angle zero error by using an active radar seeker. The method comprises the steps of: calculating inertial navigation accordingto signals collected in real time by an inertial measurement unit in strap-down inertial navigation system to obtain flight path information of a missile in the strap-down inertial navigation system;in a case that every preset time is a sampling point, collecting beam signals during the search, interception and tracking of a target point by the active radar seeker, and calculating a first ballistic target line-of-sight angle of the missile relative to the target point in real time; collecting output data of a gyro and an accelerometer in the inertial measurement unit at each sampling point,and calculating a second ballistic target line-of-sight angle of the missile relative to the target point in real time according to the strap-down inertial navigation system principle; establishing astate equation, wherein the state variables in the state equation comprises the line-of-sight angle zero error; establishing a observation equation by using the ballistic target line-of-sight angle based on a observed value of the second ballistic target line-of-sight angle as observed quantity; and estimating the line-of-sight angle zero error according to a Kalman filtering method based on the state equation and the observation equation.

Description

technical field [0001] The invention relates to the technical field of inertial navigation, in particular to a method and device for estimating the line-of-sight angle zero error of an active radar seeker. Background technique [0002] The active radar seeker (Active Radar Seeker, ARS) is often used to track targets, and can also provide relatively stable bullet-to-eye line-of-sight angle, missile-to-eye relative distance, and relative speed information. This information has the potential to assist inertial navigation, and radar direction It transmits beams to the ground, has good autonomy and is not easily disturbed, and has a good prospect for combined applications. ARS can be used for single-mode guidance, compound guidance, etc. In missile guidance, combining SINS and ARS to form an integrated navigation system can improve the performance of ARS and the accuracy of SINS, thereby reducing the technical indicators of related components and reducing system costs. [0003]...

AI Technical Summary

Problems solved by technology

[0004] The embodiment of the present invention provides a method and device for estimating the zero error of the line of sight angle of the ac

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