Multi-aircraft cooperative detection and guidance integrated method and system

An aircraft and measurement technology, which is applied in the field of target tracking and can solve the problems of low adaptability of multi-modal motion modes and large error of target state estimation accuracy.

Pending Publication Date: 2020-10-27
中国人民解放军火箭军工程大学
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Problems solved by technology

In addition, for the traditional KF/SF method of estimating the target state, its adaptability to the multi-moda...

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  • Multi-aircraft cooperative detection and guidance integrated method and system
  • Multi-aircraft cooperative detection and guidance integrated method and system
  • Multi-aircraft cooperative detection and guidance integrated method and system

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Embodiment Construction

[0067] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0068] The purpose of the present invention is to provide an integrated method and system for multi-aircraft cooperative detection and guidance. By modulating the line-of-sight separation angle of two interceptors, the accuracy of target detection can be enhanced, and target tracking and interception can be realized.

[0069] In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention will be f...

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Abstract

The invention discloses a multi-aircraft cooperative detection and guidance integrated method and system. The method comprises the steps of obtaining the initial lateral distance between an interceptor and a maneuvering target, the initial lateral relative speed between the interceptor and the maneuvering target, the initial acceleration of the maneuvering target and the initial acceleration of the interceptor; determining an initial state vector according to the initial lateral distance, the lateral relative speed, the initial acceleration of the maneuvering target and the initial acceleration of the interceptor; determining measurement information according to the initial state vector and interceptor noise; based on the measurement information, obtaining an estimated state vector throughinteractive multi-model filtering; determining optimal control input according to the estimated state vector; and controlling the sight angles of the two interceptors according to the optimal controlinput to realize tracking interception of the target. Interactive multi-model filtering is introduced to recognize the switching time and state of target maneuvering, the sight separation angle of the two interceptors is modulated, the target detection precision is enhanced, and target tracking and interception are achieved.

Description

technical field [0001] The invention relates to the field of target tracking, in particular to an integrated method and system for multi-aircraft cooperative detection and guidance. Background technique [0002] For the situation where two interceptors intercept an enemy target capable of performing a bang-bang optimal evasion maneuver. The traditional cooperative guidance law that considers that two interceptors arrive at the target at the same time often does not consider the influence of the relative detection configuration on the accuracy of the intercepted target, because when the multi-aircraft cooperative angle measurement method is used to further estimate the distance information, if the multi-aircraft and the target share It is impossible to estimate the relative distance when they are collinear, and the estimation error is larger when they are approximately collinear. Therefore, it is necessary to consider the influence of the relative detection configuration of ...

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Application Information

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IPC IPC(8): G06F30/15G06F30/20
CPCG06F30/15G06F30/20Y02T90/00
Inventor 郭杨王少博王仕成席建祥刘志国于传强张帅宋海涛杜文正程洪杰邓飙陶雁华
Owner 中国人民解放军火箭军工程大学
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