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Surface Element Correction and Mesh Pre-adaptive Calculation Method

A self-adaptive computing, surface element technology, applied in computing, special data processing applications, instruments, etc., can solve problems such as poor accuracy, and achieve the effect of improving accuracy, improving computing efficiency, and high computing efficiency

Active Publication Date: 2018-07-27
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0005] In order to overcome the shortcomings of the poor precision improvement effect of modern binning correction methods, the present invention proposes a binning correction and mesh pre-adaptive calculation method

Method used

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Embodiment Construction

[0039] This embodiment is a method for surface element correction and grid pre-adaptive calculation of an M6 wing with NACA0012 symmetrical airfoil.

[0040] The M6 ​​wing root of the NACA0012 symmetrical airfoil is completely fixed. The wing parameters are as follows: wing root chord length is 0.8139m, wing tip chord length is 0.4573m, span length is 1.1963m, leading edge sweep angle is 30°, trailing edge sweep angle is 15.8°, no twist angle, Mongolian The thickness of the skin is 0.002m, the thickness of the beam web is 0.0015m, the thickness of the wing rib is 0.0015m, the material is aluminum alloy, the elastic modulus E=70GPa, Poisson’s ratio μ=0.30, and the density is ρ=2.7×10 3 kg / m 3 . image 3 is the overall finite element model of the wing, where (a) represents the span direction from wing root to wing tip, and (b) represents the chord direction from wing leading edge to trailing edge. Figure 4 is the finite element model of the wing front spar web 11, rear spar ...

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Abstract

A method of surface element correction and mesh pre-adaptive calculation, which uses multiple sets of CFD aerodynamic load data under different angles of attack to perform segmented line correction on the low-order surface element method, and uses adaptive simulated annealing algorithm to calculate the surface elements The grid distribution is optimized. The accuracy of the modified panel method is improved through the adaptive optimization of the panel grid, which makes up for the shortcomings of the traditional modified panel method depending on the grid distribution. When the optimized grid is applied to the modified panel method, it not only maintains the advantages of the high calculation efficiency of the panel method, but also ensures that the overall force of the wing is close to the accuracy of the CFD data, effectively improving the accuracy of the aeroelastic optimization iterative design process and efficiency. The accuracy error between the aerodynamic load data obtained by the invention and the CFD calculation result is within 2%, and effectively extends to the nonlinear section where the aerodynamic load varies with the angle of attack, thereby improving the efficiency of aerodynamic load calculation in the process of structural stiffness parameter change.

Description

technical field [0001] The present invention relates to a numerical calculation problem of constant aerodynamic load on the lifting surface in the structural design of an aircraft, and proposes a surface element correction and grid pre-adaptive optimization algorithm technology, so that the obtained aerodynamic load distribution can reach CFD ( Computational Fluid Dynamics) numerical accuracy, and the calculation efficiency is much higher than that of the CFD method when applied to the structural static aeroelastic weight analysis and optimal design. Background technique [0002] In the numerical optimization design of the aircraft structure under static aeroelastic constraints, a large number of numerical calculations of coupled aerodynamic loads and structural deformation are required, and high-precision and high-efficiency static aeroelastic coupling numerical algorithms have become one of the key technologies. Two methods are often used to calculate aerodynamic loads in ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50G06T17/30
Inventor 孙秦刘祥刘琳颖贾欢
Owner NORTHWESTERN POLYTECHNICAL UNIV