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Multi-gradient radiation heat flow field simulation method in aerospace aircraft test

A technology of aerospace aircraft and simulation method, which is applied in the direction of aircraft component testing, machine/structural component testing, measuring devices, etc., and can solve the problem of larger space occupied by the supporting frame of the heating device, boundary control error of the radiation heat flow field, heat flow, etc. Density cannot be adjusted and other problems, to achieve the effect of reducing the cost of a single test, the overall device is compact, and the occupied space is saved

Active Publication Date: 2022-07-05
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the heating device composed of different module heaters has the following problems: 1) The heat flux density at the connection boundary of each module heater cannot be adjusted, which will lead to boundary control errors in the radiation heat flow field; 2) Each module heater requires a controller Unified adjustment parameters, due to the limitations of the actual process, there will be time coordination errors
[0005] Not only that, for a single modular heater (modular quartz lamp, modular graphite heater), the minimum area of ​​the thermal flow field that can be simulated is limited and the shape is fixed, but with the upgrading of the process, the size of the radiant heating element is reduced , the shape of the element is diversified, and the space occupied by the supporting frame of the heating device becomes larger, and the existing single modular heater cannot independently meet the test requirements of simulating the multi-gradient heat flow field

Method used

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  • Multi-gradient radiation heat flow field simulation method in aerospace aircraft test
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  • Multi-gradient radiation heat flow field simulation method in aerospace aircraft test

Examples

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Embodiment 1

[0065] The main purpose of embodiment 1 is to illustrate the scheme design of the present invention under specific parameters, and the specific steps are as follows:

[0066] S1. Design radiant heating device

[0067] In this example, see figure 1 , the aircraft aileron is selected as the test component, and the area of ​​the heated surface of the test component used to test the structure is 0.32 m 2 ;

[0068] Based on the relevant parameters of the above test components, a single modular quartz lamp is used as the radiant heating device. The 40 quartz lamps on the modular quartz lamp are arranged on the same plane, and the size of the heating area is 1 m. 2 , the total rated power is 400 kW, and the distance between the heating surface of the modular quartz lamp and the heating surface of the aircraft aileron is 50 mm;

[0069] The heating filament of each quartz lamp tube of the single modular quartz lamp is 1000 mm long, the voltage is 380V, and the electric power is 10...

Embodiment 2

[0089] The main purpose of embodiment 2 is to illustrate the scheme design when the present invention simulates the radiant heat flow field of regular contour shape, and the contents are as follows:

[0090] S1. Design radiant heating device

[0091] In this example, see figure 1 , the aircraft flap is selected as the test component, and the area of ​​the heated surface of the aircraft flap used to test the structure is 0.15 m 2 ;

[0092] Based on the relevant parameters of the above test components, a single modular quartz lamp is used as the radiant heating device. The 40 quartz lamps on the modular quartz lamp are arranged on the same plane, and the size of the heating area is 1 m. 2 , the total rated power is 400 kW, and the distance between the heating surface of the modular quartz lamp and the heating surface of the aircraft aileron is 80 mm;

[0093] The heating filament of each quartz lamp tube of the single modular quartz lamp is 1000 mm long, the voltage is 380V,...

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Abstract

The invention relates to the technical field of aircraft testing, in particular to a multi-gradient radiation heat flow field simulation method in aerospace aircraft testing. The method comprises the steps of designing a radiation type heating device, dividing a temperature area n of a heated surface, dividing a projection area n of each temperature area n, calculating setting parameters of a multi-gradient radiation heat flow field, and simulating the multi-gradient radiation heat flow field. A radiation heat flow field with an irregular contour shape and a radiation heat flow field with a regular contour shape are respectively simulated by using an integrated projection plate and a module projection plate, so that a multi-gradient radiation heat flow field is simulated within a heating range smaller than that of a single radiation heating device; boundary control errors and time coordination errors occurring when a multi-module heating device is used for simulating different gradient heating flow fields in the prior art are avoided.

Description

technical field [0001] The invention relates to the technical field of aircraft testing, in particular to a method for simulating a multi-gradient radiation heat flow field in aerospace aircraft testing. Background technique [0002] When an aerospace vehicle is in hypersonic flight, its structural surface is subjected to severe aerodynamic heating, which brings great challenges to the structural strength. Therefore, the thermal strength test verification on the ground is an indispensable link in the testing of high-speed aircraft. [0003] Radiant heating has been widely used in ground thermal strength tests because of its good electrical control performance, which can simulate the fast time-varying aerothermal environment of high-speed aircraft. Radiant heat heaters currently in use include modular quartz lamps, modular quartz lamp groups, modular graphite heaters, and modular graphite heater groups. [0004] Among them, the modular quartz lamp group and the modular graph...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M99/00B64F5/60C03C17/245G06F30/15G06F30/28
CPCG01M99/002B64F5/60C03C17/2456G06F30/15G06F30/28C03C2218/156C03C2217/212G06F2119/08Y02T90/00
Inventor 王彬文王振亚秦强李世平
Owner CHINA AIRPLANT STRENGTH RES INST
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