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Circular arc front-and-back edge of aviation blade reconstruction method based on error control

An aviation blade and error control technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve problems such as poor anti-noise performance, achieve good anti-noise performance, and improve the effect of reconstruction quality

Inactive Publication Date: 2013-05-08
NORTHWESTERN POLYTECHNICAL UNIV
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AI Technical Summary

Problems solved by technology

[0004] In order to overcome the deficiency of poor anti-noise performance of the existing method for extracting characteristic parameters of the blade section based on measurement data, the present invention provides a method for reconstructing the arc-shaped leading and trailing edges of aviation blades based on error control

Method used

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  • Circular arc front-and-back edge of aviation blade reconstruction method based on error control
  • Circular arc front-and-back edge of aviation blade reconstruction method based on error control
  • Circular arc front-and-back edge of aviation blade reconstruction method based on error control

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Embodiment Construction

[0026] refer to Figure 1~5 . The specific steps of the method for reconstructing the arc-shaped leading and trailing edges of aviation blades based on error control in the present invention are as follows:

[0027] (1) Read in the profile line discrete measurement data of the aeronautical blade, and select the area points covering the leading edge or trailing edge of the blade;

[0028] (2) Sort the area points;

[0029] (3) Cubic spline fitting is carried out to the sorted regional points;

[0030] (4) Encrypt and discretize the fitted spline curve with equal arc length, and record the start and end discrete points as P 0i ,P 1i ;

[0031] (5) Use the least squares method for P 0i P 1i segment discrete points for fitting, and P 0i P 1i The discrete points at the intersection of the segment and the fitting circle are denoted as P 0(i+1) ,P 1(i+1) ;The circle fitting method is as follows:

[0032] ①Establish the objective function of circle fitting:

[0033] For a...

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Abstract

The invention discloses a circular arc front-and-back edge of an aviation blade reconstruction method based on error control, and is used for solving the technical problem that anti-noise performance of the existing blade section characteristic parameters extraction method based on the measured data is poor. The circular arc front-and-back edge of the aviation blade reconstruction method based on the error control is composed of selecting region points covering the front-and-back edge of the aviation blade, arranging the region points, and matching the arranged region points with a cubic spline so as to gain a curve L0. The method carries out discretion and encryption on the matched spline curve L0 in an arc equal-length mode, respectively marks the head discrete point as P0i and the end discrete point as P1i, utilizes the least square method to carry out a circular matching for the discrete points between P0i and P1i containing P0i and P1i, calculating the average error epsilon i from the discrete points to an ith matching circle, and setting the iteration control error as epsilon until the epsilon i is less than or equal to the epsilon, the iteration ends. Based on the error control based on the matching of the least square method for fitting, utilizing the iterative matching method based on the error control, the circular arc front-and-back edge of the aviation blade reconstruction method reconstructs blade circular arc front-and-back edge, avoids that the points in the selected area involve the matching, wherein the points are not on the circular arc, and improves the anti-noise performance.

Description

technical field [0001] The invention relates to a method for reconstructing the arc-shaped front and rear edges of an aviation blade, in particular to a method for reconstructing the arc-shaped front and rear edges of an aviation blade based on error control. Background technique [0002] The shape of leading and trailing edges of aviation blades has an important influence on the aerodynamic performance of the engine. The generation of leading and trailing edge curves based on measurement data is a key task in blade measurement modeling. The leading and trailing edges of the existing blades are mostly arcs or elliptical arcs. During the reconstruction of the arc-shaped leading and trailing edges of the blade, it is necessary to avoid as much as possible the measurement data points belonging to the blade pot and the blade back in the blade measurement data from participating in the fitting of the leading and trailing edge arcs, so as to ensure a high reconstruction accuracy ...

Claims

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Application Information

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IPC IPC(8): G06F19/00
Inventor 程云勇朱真真汪文虎王增强王丽雅李维亮李向欣郑佳杨杰
Owner NORTHWESTERN POLYTECHNICAL UNIV
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