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Aircraft modeling method based on adjustable parameter maximum information criterion

A technology with the largest amount of information and modeling methods, applied in the field of aircraft modeling, can solve problems such as poor accuracy of aerodynamic models and parameters

Inactive Publication Date: 2013-02-20
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] In order to overcome the deficiency that the existing maximum information criterion leads to poor correctness of the aerodynamic model and parameters given by the flight test, the present invention provides an aircraft modeling method based on the adjustable parameter maximum information criterion

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  • Aircraft modeling method based on adjustable parameter maximum information criterion
  • Aircraft modeling method based on adjustable parameter maximum information criterion

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Embodiment Construction

[0039] The specific steps of the aircraft modeling method based on the maximum amount of information criterion of adjustable parameters in the present invention are as follows:

[0040] 1. The commonly used candidate model forms for many aircraft when the angle of attack is less than 60 degrees are:

[0041] x · ( t ) = Φ ( Ω 0 ) f 0 [ x ( t ) ] + θ 1 f 1 [ x ( t ) ] + . . . + θ q f q [ x ...

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Abstract

The invention discloses an aircraft modeling method based on an adjustable parameter maximum information criterion. The method is used for solving a technical problem that an aerodynamic model and parameters given by a flight test are poor in correction due to the existing maximum information criterion. The technical scheme of the invention is as follows: introducing an adjustable parameter through a maximum information criterion, and correcting a modeling criterion according to flight test factors of different aircrafts; and carrying out U-D factorization on measurement variance estimations Rj and R(j+1) to acquire a scalar model selection discriminant. The aircraft modeling method is convenient to directly establish aerodynamic and moment models according to the flight test data, thus avoiding a technical problem that the aerodynamic model and parameters acquired by the flight test are incorrect based on the maximum information criterion due to increased fixed parameters.

Description

technical field [0001] The invention relates to an aircraft modeling method, in particular to an aircraft modeling method based on an adjustable parameter maximum information amount criterion. Background technique [0002] According to the aircraft aerodynamic model and parameters, it can not only determine the handling stability of the aircraft, but also provide the correct mathematical model for ground and air simulators; verify the wind tunnel experiments and theoretical calculation results of aircraft aerodynamic parameters; provide support for the design and improvement of aircraft control systems Provide basic data; identify the flight quality of finalized aircraft; study the flight quality of high-performance aircraft; conduct accident analysis of aircraft crashes, etc.; the problem of accurately establishing a mathematical model of an aircraft is completely different from the theoretical method of modeling through basic laws, theorems, etc. , the model is mainly esta...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 史忠科
Owner NORTHWESTERN POLYTECHNICAL UNIV
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