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Guidance tool error distinguishing method based on experiment design and evolutionary optimization

A technology of test design and identification method, which is applied in the field of aerospace and aviation, can solve the problems of inability to effectively separate error coefficients, inability to provide sufficient support for missile weapon system accuracy assessment, inability to effectively comprehensively utilize, etc., to achieve global optimization, large coverage, high The effect of search efficiency

Active Publication Date: 2018-11-16
NAT UNIV OF DEFENSE TECH
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

However, these methods either cannot effectively comprehensively utilize various information, or cannot effectively separate error coefficients, and often can only roughly separate some main tool error items, and the separation results cannot provide sufficient support for the accuracy assessment of missile weapon systems

Method used

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  • Guidance tool error distinguishing method based on experiment design and evolutionary optimization
  • Guidance tool error distinguishing method based on experiment design and evolutionary optimization
  • Guidance tool error distinguishing method based on experiment design and evolutionary optimization

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Embodiment 1

[0062] A guidance tool error identification method based on experimental design and evolution optimization, comprising the following steps:

[0063] The first step is to obtain data information. The data information includes flight test ballistic data, missile launch point information, error coefficient ground calibration information, star sensor installation angle, star sensor measurement data and missile drop point deviation data. In this case Preferably: the flight test ballistic data includes the external measurement data and the measurement accuracy information of the external measurement data during the flight of the missile, and the external measurement data includes time, speed and position; the missile launch point information includes the geographical longitude, latitude and elevation of the launch point and the launch orientation angle; the error coefficient ground calibration information includes the initial alignment error term and the ground calibration value and ...

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Abstract

The invention provides a guidance tool error distinguishing method based on experiment design and evolutionary optimization. The guidance tool error distinguishing method comprises the following steps: S1: obtaining data information; S2: preprocessing the data information; S3: setting parameters: setting a target function, setting a constrain condition, setting a search space, setting a populationrange, and setting an evolution algebra; S4: according to an experiment design method, finishing multiple-time error coefficient distinguishing, and carrying out statistics on analysis results. According to the guidance tool error distinguishing method, under a condition of inertia / starlight combined guidance, multi-source measurement information is used, a ballistic trajectory recurrence methodbased on evolutionary optimization is adopted to carry out distinguishing on error coefficient, meanwhile, an experiment design scheme of multiple-time optimization is put forward, the optimization effect of a genetic evaluative algorithm is improved, and guidance tool error coefficients can be effectively separated. Compared with a traditional tool error distinguishing method, the guidance toolerror distinguishing method disclosed by the invention has obvious advantages.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a guidance tool error identification method based on experimental design and evolution optimization. Background technique [0002] In long-range ballistic missiles, inertial / star-light composite guidance is a guidance method based on pure platform inertial guidance using star sensor measurement information for correction. By establishing an inertial guidance coordinate system and correcting and compensating the misalignment angle of the platform through control instructions, the missile can finally hit the target point accurately; at the same time, the star-sensitive measurement data can well reflect the actual situation of the tool error, and it is the guidance tool error. Identify important sources of information. [0003] At present, there are many mathematical methods for the separation of error coefficients, one is based on the linear matrix theory, and the other is the ...

Claims

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Application Information

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IPC IPC(8): G01C25/00G01C21/16G06N3/12
CPCG01C21/165G01C25/00G06N3/126
Inventor 孟云鹤王子鉴蒋小勇吴杰陈琪锋
Owner NAT UNIV OF DEFENSE TECH
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