Analyzing method for temperature field of integral fuel tank

An integrated fuel tank and analysis method technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of high cost and long cycle, and achieve the effect of short design cycle, easy promotion and application, and great practical value

Inactive Publication Date: 2017-03-22
SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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Problems solved by technology

Usually this kind of influence is reflected by test simulation, but the period of test means is longer and the cost is higher

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  • Analyzing method for temperature field of integral fuel tank
  • Analyzing method for temperature field of integral fuel tank
  • Analyzing method for temperature field of integral fuel tank

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[0027] 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 discloses an analyzing method for a temperature field of an integral fuel tank, and belongs to the technical field of aircraft designs. The method includes the following steps: step 1, establishing a simulation model of an integral fuel tank structure, and determining a fuel space area inside the integral fuel tank structure; step 2, filling the fuel space area with simulation fuel so that the fuel space area is full of fuel; step 3, further dividing the simulation fuel in the fuel space area into n layers; step 4, applying aerodynamic heating data, changing along with the time, on the aerodynamic surface of the integral fuel tank structure; step 5, carrying out fuel consumption and filling gas simulation through a ladder simulation method; and step 6, obtaining a change result of the temperature of the integral fuel tank structure along with the time after the fuel consumption simulation through the ladder simulation structure. According to the method, temperature field changes of the structure can be effectively obtained without being limited by test equipment or test environments, the product design period is short, and the design efficiency is improved. The analyzing method is easy to promote and apply, and has great practical values.

Description

technical field [0001] The invention belongs to the technical field of aircraft design, and in particular relates to an analysis method for the temperature field of an integral fuel tank. Background technique [0002] At present, the overall fuel tank structure is generally used in civil aviation airliners. Due to the low flight speed (less than Mach 2), the problem of aerodynamic heating can be ignored in structural design. However, for high Mach number (more than 2 Mach number) aircraft, it is necessary to consider the impact of aerodynamic heating on the overall fuel tank structure. Usually this kind of influence is reflected through test simulation, but the cycle of taking test means is longer and the cost is higher. [0003] Therefore, it is desirable to have a technical solution to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art. Contents of the invention [0004] Purpose of the present invention: In order to solve the ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20Y02T90/00
Inventor 张铁亮王德刚王美琦毕世权刘利阳
Owner SHENYANG AIRCRAFT DESIGN INST AVIATION IND CORP OF CHINA
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