Forward fixture profile optimization design method

A technology for optimizing design and shape, which is applied in the field of forward frame shape optimization design, and can solve problems such as long time spent

Active Publication Date: 2015-12-02
BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC +1
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  • Application Information

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Problems solved by technology

The main feature of this method is that it can consider process and manufacturing constraints through design parameters. The disadvantage is that it needs rich engineering experience when establishing the shape database of the frame. Compared with the direct reverse frame shape design method, this method takes longer

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Embodiment Construction

[0035] The technical solutions of the present invention will be further described below in conjunction with the accompanying drawings and through specific implementation methods.

[0036] like figure 1 A method for optimizing the shape of a positive frame is shown, including the following steps:

[0037] (1). First, based on the cruise shape, establish the corresponding parametric aerodynamic model and structural model, calculate the pressure coefficient distribution under the cruise condition and take it as the optimal design goal;

[0038] (2). Define the anhedral deformation Δα of the airfoil torsion center point at different spanwise positions i and airfoil torsion angle deformation Δθ i For the design variables, select a variable combination, and use the hybrid algorithm of genetic algorithm and gradient method as the optimization algorithm to perform optimization calculations to obtain the corresponding frame shape; where different design variable combinations corresp...

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Abstract

The present invention discloses a forward fixture profile optimization method. The method comprises the following steps: (1) using a parametric method to establish an aerodynamic model and a structural model of a cruising profile; (2) designing a fixture profile by using an optimization algorithm; (3) calculating an aerodynamic model and a structural model of the fixture profile, and performing modal analysis on the obtained structural model; (4) calculating a profile after static aeroelastic deformation and corresponding pressure coefficient distribution; (5) verifying whether the fixtures profile is an optimal fixtures profile; if no, executing step (6); and (6) repeating steps (2) to (5) until an optimal fixture profile is obtained. According to the method provided by the present invention, the fixture profile is designed with the concept of optimization design, that is, firstly the fixture profile is defined by using a parametric method; then, the fixture profile is obtained by changing a parameter value; then, automatic optimization is performed by using an optimization algorithm until an optimal fixture profile is obtained, so as to ensure the fixture profile after deformation and to ensure that the aerodynamic performance thereof is closest to that of the designed cruising profile.

Description

technical field [0001] The invention relates to the field of aeronautical design, in particular to a method for optimizing the shape of a forward frame suitable for civil aircraft. Background technique [0002] The cruising shape of a large civil aircraft is mainly based on the assumption that the aircraft is a rigid body, and according to the aerodynamic performance requirements in the cruising state, such as lift coefficient, lift-to-drag ratio and other parameters are designed. However, when the aircraft is in real cruising flight, due to the influence of structural static aeroelasticity, structural deformation will occur and aerodynamic loads will be redistributed, resulting in the loss of flight performance of the aircraft, and even catastrophic accidents. This effect is very important for Dazhan The chord ratio is more pronounced for civil aircraft. Therefore, in the process of aircraft design, it is necessary to analyze and study the aeroelastic characteristics of th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 孙明哲曾杰徐吉峰
Owner BEIJING AERONAUTIC SCI & TECH RES INST OF COMAC
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