Method for analyzing influences of wing deformation and vibration on aircraft transfer alignment

A technology for delivering alignment and analysis methods, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as high cost and long time, and achieve the effect of improving combat capability

Inactive Publication Date: 2014-08-20
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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  • Abstract
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  • Application Information

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Problems solved by technology

However, this method of actual measurement is time-consuming and expensive, and it is impossible for every model to adopt

Method used

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  • Method for analyzing influences of wing deformation and vibration on aircraft transfer alignment
  • Method for analyzing influences of wing deformation and vibration on aircraft transfer alignment
  • Method for analyzing influences of wing deformation and vibration on aircraft transfer alignment

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Embodiment Construction

[0039] This patent will be further described in detail through specific implementation below.

[0040] First, establish a dynamic model of the whole machine structure

[0041] The aerial dynamic platform model is based on the static model of the whole aircraft of a certain type,

[0042] The mass distribution is adjusted to obtain the structural dynamics calculation model of the whole machine.

[0043] The theoretically calculated mass of the whole machine is 498.435kg; the position of the center of gravity is X=3.7762m, Y=-0.1m, Z=0. After inspection, the mass of the modal calculation model of the whole machine is 497.55kg; the position of the center of gravity is X=3.77662m, Y=-0.1m, Z=1.0E-4m.

[0044] Second, the unsteady aerodynamic model of the whole machine

[0045] The unsteady aerodynamic model is divided into 30 aerodynamic units. Among them, there are 14 units for the fuselage, 8 units for the wings, 4 units for the wingtips, and 4 units for the empennage.

[0...

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Abstract

The invention belongs to the field of aircraft structural dynamics, and relates to a method for analyzing influences of wing deformation and vibration on aircraft transfer alignment. The method is characterized by including the following steps: (1) building a full-aircraft structure dynamical model, (2) building a full-aircraft unsteady aerodynamic model, (3) building a transfer relationship between plug-ins and inertial navigation, and (4) obtaining a primary-secondary inertial navigation error fitting empirical formula. The method has the advantages that speed errors and angular speed errors generated between the primary inertial navigation and the secondary inertial navigation of an aerial movable platform are analyzed through the built aircraft structure dynamical model, then the errors are eliminated through filtering, and in this way, the transfer alignment time of the primary inertial navigation and the secondary inertial navigation during guided missile launching can be shortened to a great degree.

Description

technical field [0001] This patent belongs to the field of aircraft structural dynamics and relates to an analysis method for the influence of wing deformation and vibration on aircraft transfer alignment. Background technique [0002] The inertial navigation system of the guided weapon carried by the aerial platform must first perform initial alignment before starting work, the purpose of which is to enable the inertial navigation system to establish a suitable navigation coordinate system. The accuracy of the initial alignment is directly related to the combat performance of the weapon system, so the initial alignment is one of the most important key technologies of the inertial navigation system. In order to eliminate the error between the main and sub-inertial navigation, the method of flight measurement was used before. This method is to use a high-speed camera to take pictures of the displacement and vibration of the wing deformation under a certain Mach number, altitu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 冯世宁陈忠明
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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