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Surface element correction and grid beforehand self-adaption calculation method

An adaptive computing and grid technology, which is applied in computing, special data processing applications, image data processing, etc., can solve problems such as poor accuracy, and achieve the effects of improving accuracy, improving computing efficiency, and high computing efficiency

Active Publication Date: 2015-12-23
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

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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

The invention relates to a surface element correction and grid beforehand self-adaption calculation method. According to the method, segmented linearizing correction is carried out on a low-order surface element method with multiple groups of CFD aerodynamic force load data under different attack angles, and distribution of surface element calculation grids is optimized by adopting a self-adaption simulated annealing algorithm. By means of self-adaption optimization of the surface element grids, the accuracy of the surface element correction method is improved, and the defect that a traditional surface element correction method depends on grid distribution is overcome. When the optimized grids are applied to the surface element correction method, the advantage of high calculation efficiency of the surface element method is kept, the accuracy of overall wing stress close to the CFD data can be ensured, and the accuracy and efficiency in the aeroelasticity optimal iteration design process are effectively improved. The accuracy error between the obtained aerodynamic load data and CFD calculation results is within 2% and effectively extends to the non-linear segment in which aerodynamic loads change along with the attack angle, and the aerodynamic load calculation efficiency in the changing process of structural rigidity parameters is improved.

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 ( ComputationalFluidDynamics) 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 mo...

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Application Information

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