Optimization method for subsonic flutter of aircraft wing skin

An optimization method, subsonic technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of insufficient software and hardware resources, long genetic algorithm time, etc. Effects of excessively long, high-performance computing power

Active Publication Date: 2011-11-30
中国航空工业集团公司科学技术委员会 +1
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Problems solved by technology

The method is integrated in the grid platform, on the one hand, it can solve the problem of insufficient hardware and software resources, and at the same time, it can solve the problem of too long time of genetic algorithm through parallel computing

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  • Optimization method for subsonic flutter of aircraft wing skin
  • Optimization method for subsonic flutter of aircraft wing skin
  • Optimization method for subsonic flutter of aircraft wing skin

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Embodiment Construction

[0060] The technical scheme of the present invention will be described in further detail below in conjunction with accompanying drawing and embodiment:

[0061] The steps of the subsonic flutter optimization method for this kind of aircraft wing skin are:

[0062] (1) Use Catia software to build a three-dimensional model of the aircraft wing, including skin 1, stringer 2, beam 3, and wing rib 4, save the model file in .igs format, and import the file in .igs format to MSC Patran software. Use the existing shape to build the structure finite element model, see attached figure 1 . When modeling, the skin adopts the CQUAD4 unit, the truss and beam adopt the CROD unit, and the mass of the airfoil structure is discretized into a lumped mass acting on node 11 of the skin unit, and the scalar mass unit CMASS2 is used. boundary conditions. The plate element on the skin 1 on the main load-bearing structure is used as the design element 12, see the attached figure 2 . When buildi...

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Abstract

The invention provides a method for optimizing skins of an airplane airfoil by a subsonic flutter based on a network computing platform. The method provided by the invention can take elements of each skin of the airfoil as objects to be optimized and also selects layering angles, layering thickness increment and layering positions as design variables; and a search which guarantees a genetic algorithm is processed in a space area comprising all possible solutions. The process of optimizing utilizes a double-circulation flow so that a decoupling problem of great design variables (more than 1000) is solved and also utilizes a 'small increment valley-filling method' to effectively avoid the oscillation of the algorithm so that a high repeatability of the algorithm is assured. The method provided by the invention is integrated into a gridding platform so that the method not only can solve the problem that the hardware-software resource is not enough, but also can solve the problem that thetime of the genetic algorithm is too long through a parallel computing.

Description

technical field [0001] The invention relates to a subsonic flutter optimization method for aircraft wing skin, which belongs to the field of aeroelastic tailoring of aircraft composite wing surfaces, and is used for subsonic flutter speed optimization in the design of aircraft composite wing surfaces. Background technique [0002] The flutter problem is a serious case of aircraft wing design, especially one of the main design constraints of the empennage. The wing surface often limits the flight envelope due to insufficient flutter speed, which becomes the key to the design. The application of composite material structure in aircraft design provides a new development field for aircraft structure technology. That is to make full use of the designability of composite materials, while satisfying the optimization of strength design, "aeroelastic tailoring design" can be carried out. The aeroelastic tailoring method is to use the anisotropy of composite materials and its variou...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50G06N3/12
Inventor 崔德刚张睿杜海熊青岳程文渊
Owner 中国航空工业集团公司科学技术委员会
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