Numerical simulation method for an aircraft hot air anti-icing component temperature field
A temperature field and component technology, applied in the direction of electrical digital data processing, computer-aided design, special data processing applications, etc., can solve problems such as large temperature workload, uncoordinated structural finite element mesh, etc., to meet the needs of engineering precision , improve modeling and update efficiency, and implement easy effects
Active Publication Date: 2019-04-05
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology
In the prior art, some temperature field calculations are not loaded, and only the performance reduction of materials at high temperatures is considered; some consider the temperature field loading, but the temperature field of aircraft hot gas anti-icing components is generally calculated by CFD software through aerodynamic grids It is found that it is not compatible with the structural finite element grid, and the manual structure search for the corresponding temperature of the finite element element is a huge workload, and there is an urgent need for an equivalent simulation method for the temperature field that is simple, fast and meets the accuracy requirements
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[0014] Referring to the accompanying drawings, the present application takes an aircraft hot gas anti-icing leading edge slat component as an example to further illustrate the numerical simulation method of the temperature field. Given the structural finite element grid of the leading edge slat component and the temperature field data of the aerodynamic grid of the component, when it is necessary to load the temperature field on the structural finite element grid for calculation, follow the steps below, 1) According to the leading edge slit The temperature field of the aerodynamic grid of the wing is obviously strip-shaped, and the part is divided into multiple temperature similar sections along the lengthwise direction; 2) In each temperature similar section, a middle section is selected as a typical section, and the length The percentage is the horizontal axis, and the temperature value is the vertical axis. Read a sufficient number of temperature data points and draw the pro...
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The invention discloses a numerical simulation method for an aircraft hot air anti-icing component temperature field. The method comprises the following steps: dividing the part into a plurality of temperature similar sections along an extension direction according to a pneumatic grid temperature field; Selecting a middle section from each temperature similar section as a typical section, and drawing a temperature distribution curve of the typical section; Temperature distribution curve, dividing into a plurality of temperature sections; according to the average temperature value of each temperature section, simplifying a typical section temperature distribution curve into a piecewise function curve, compared with known pneumatic grid temperature field data of parts, calcuating an error ofa temperature mean value and an error of a temperature variance and loading a simplified piecewise function meeting engineering error requirements to a structure finite element grid for calculation.
Description
technical field [0001] The invention belongs to the field of aircraft structure design and strength analysis, in particular to a numerical simulation method for the temperature field of an aircraft hot gas anti-icing component. Background technique [0002] The main parts of the wing ice include the leading edge of the wing and the upper and lower surfaces of the wing. When an aircraft passes through a cloud layer containing supercooled water droplets, if the surface temperature of the wing is lower than 0°C, the supercooled water droplets will collide with the wing and gather on the surface of the wing to form an ice layer, resulting in icing. [0003] Since the wing is an important part of the aircraft to generate lift, icing on the surface of the wing will greatly reduce the aerodynamic quality and handling performance. Most of the aircraft currently in operation have taken hot gas anti-icing (or de-icing) measures to the wings. When the aircraft enters the icing area w...
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Login to View More IPC IPC(8): G06F17/50
CPCG06F2119/08G06F30/23G06F30/15Y02T90/00
Inventor 朱江李刚袁波
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA