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High-temperature thermal intensity experiment method of curved surface structure under complex thermal field for aerospace plane test

A technology for aerospace planes and curved surface structures, which is applied in aircraft component testing, mechanical component testing, and machine/structural component testing. It can solve problems such as temperature control interference, and achieve the effect of improving accuracy and control performance.

Pending Publication Date: 2022-06-28
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The invention solves the problem of multi-temperature zone and multi-variable temperature control interfering with each other, realizes the precise control of the heat flux density of the heated aircraft curved surface components, and improves the accuracy of the high-temperature thermal strength experiment of the curved surface structure in the aerospace aircraft test under the complex thermal field. sex

Method used

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  • High-temperature thermal intensity experiment method of curved surface structure under complex thermal field for aerospace plane test
  • High-temperature thermal intensity experiment method of curved surface structure under complex thermal field for aerospace plane test
  • High-temperature thermal intensity experiment method of curved surface structure under complex thermal field for aerospace plane test

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0054] like figure 1 The shown experimental method for high temperature thermal strength of curved structures under complex thermal fields for aerospace aircraft testing includes the following steps:

[0055] S1. Temperature and heat flow detection in each temperature zone

[0056] Fix the aircraft surface part in the multi-temperature zone extreme high temperature heating device, and set up the temperature sensor and heat flow sensor on the aircraft surface part according to the temperature zone division; Full equation heat flux control system;

[0057] S2, enter the hypoxic environment

[0058] The inert gas is continuously injected into the extremely high temperature heating device in the multi-temperature zone through the protective gas input system until the oxygen content monitoring system shows that the oxygen content is less than 1%;

[0059] S3. The heating element is preheated and the load is applied

[0060] The heating element of the extreme high temperature he...

Embodiment 2

[0087] The difference from Example 1 is:

[0088] In step S4-2, intelligent amplitude limiting control is also performed on the heating element;

[0089] The method of intelligent limit control is: when the heating element starts to heat, use high power to preheat for 3s;

[0090] When the control curve rises to the set curve, the heating element overheats, and when the temperature rise is greater than 6°C, the electric power adjustment device automatically reduces the power output;

[0091] When the control curve drops to the set curve, the heating element appears under-heating, and the temperature rise is less than -9°C.

Embodiment 3

[0093] The difference from Example 1 is:

[0094] In step S4-2, intelligent amplitude limiting control is also performed on the heating element;

[0095] The method of intelligent limit control is: when the heating element starts to heat, use high power to preheat for 8s;

[0096] When the control curve rises to the set curve, the heating element is overheated, and when the temperature rise is greater than 9°C, the electric power adjustment device automatically reduces the power output;

[0097] When the control curve drops to the set curve, the heating element is under-heated, and the temperature rise is less than -6°C.

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Abstract

The invention relates to the technical field of aircraft testing, and discloses a complex thermal field curved surface structure high-temperature thermal intensity experiment method for aerospace aircraft testing. Comprising the following steps: S1, detecting the temperature and heat flow of each temperature zone; s2, entering a low-oxygen environment; s3, preheating the heating element and applying a load; s4, full-equation heat flux density control; s4-1, full-equation heat flux density calculation is carried out; s4-2, controlling the heat flux density; according to the method, the problem of mutual interference of multi-temperature-zone and multivariable temperature control can be solved, accurate control is realized, and the accuracy of the high-temperature thermal intensity experiment of the curved surface structure under the complex thermal field is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft testing, in particular to an experimental method for high temperature thermal strength of a curved surface structure under a complex thermal field for aerospace aircraft testing. Background technique [0002] When an aerospace plane flies at hypersonic speed in the atmosphere, the surface of its structure is subjected to severe aerodynamic heating. The aerodynamic heating temperature peak is high, the temperature change rate is large, and the thermal field is extremely complex, which makes the thermal strength experiment and evaluation of the aerospace plane structure very difficult. . [0003] The structural thermal experiment of the aircraft surface component in the aircraft strength test is based on the simulation of the energy exchange process. In the theoretical experiment, it is necessary to ensure that the thermal energy absorbed by the surface of the structure at each instant is the same ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00B64F5/60G05D23/20
CPCG01M13/00B64F5/60G05D23/20
Inventor 王彬文王铁军秦强王振亚李军鹏
Owner CHINA AIRPLANT STRENGTH RES INST