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Aircraft fire numerical simulation calculating method

A numerical simulation and calculation method technology, applied in calculation, electrical digital data processing, design optimization/simulation, etc., to achieve the effect of avoiding danger and pollution, and saving costs

Active Publication Date: 2017-08-04
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

[0004] The object of the present invention is to provide a kind of aircraft fire numerical simulation calculation method, to at least solve at least one problem existing in the existing aircraft fire research method

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  • Aircraft fire numerical simulation calculating method
  • Aircraft fire numerical simulation calculating method

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Embodiment Construction

[0026] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention relates to aircraft safety performance design, in particular to an aircraft fire numerical simulation calculating method. The numerical simulation calculating method comprises the steps of firstly, simplifying an aircraft geometric model, and building a corresponding mathematic model; secondly, selecting a constraint condition, wherein the constraint condition comprises the position of an ignition point, the varieties, number and distribution of combustible materials, and external environments; thirdly, conducting grid division on the mathematic model in the first step; fourthly, according to the results of the second step and the third step, conducting analogue simulation through a turbulent combustion model method, a heat radiation model method and a vaporous cloud explosion overpressure calculation TNT equivalent method so as to obtain a smog site, a temperature site and a fuel oil vapor explosion situation when an aircraft fire occurs. According to the aircraft fire numerical simulation calculating method, reliable data can be quickly obtained through simulation calculating, a guiding suggestion is put forward about the influence and prevention of the aircraft fire, the cost is saved, and the danger and pollution can be avoided at the same time.

Description

technical field [0001] The invention relates to aircraft safety performance design, in particular to an aircraft fire numerical simulation calculation method. Background technique [0002] Considering that once a fire breaks out on an aircraft, it will cause a catastrophic accident if the fire cannot be effectively extinguished or the spread of the fire cannot be controlled. Therefore, in order to find out the fire data such as the temperature field distribution of the fire in different states and different fire extinguishing conditions of the aircraft, and provide design input for the high temperature protection of some important systems, it is necessary to carry out analysis and research on the aircraft fire situation. [0003] Most of the current aircraft fire research is laboratory experiments. However, this fire test is only for some areas of the aircraft (such as the engine compartment), and has not done a fire test for the whole machine; in addition, a large-scale fi...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 王凯李玉芳刘康
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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