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Heat flow control method, device and system for aerothermodynamic experiment of aircraft

A heat flow control and aircraft technology, which is applied in the field of ground simulation tests, can solve problems such as complex calculation models, difficult calculation of heat flow given curves, inability to use heat flow control, etc., and achieve the effect of improving accuracy

Inactive Publication Date: 2016-05-04
BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If the heat transfer calculation model of the specimen is complicated, it is necessary to consider the coupling problem of aerodynamic force and thermal field and the change of thermophysical parameters, it is difficult to calculate the given heat flow curve, and it is impossible to use heat flow control

Method used

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  • Heat flow control method, device and system for aerothermodynamic experiment of aircraft
  • Heat flow control method, device and system for aerothermodynamic experiment of aircraft
  • Heat flow control method, device and system for aerothermodynamic experiment of aircraft

Examples

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Embodiment 1

[0029] refer to figure 1 , the present embodiment provides a heat flow control method for an aircraft aerothermal test, including:

[0030] Step S101, obtaining preset flying height information and preset flying speed information of the aircraft;

[0031] Step S102, collecting the surface temperature of the aircraft test piece in real time;

[0032] Step S103, calculating the target heat flux value according to the preset flying height information, preset flying speed information and surface temperature;

[0033] Step S104, collecting the heat flux value on the surface of the aircraft test piece in real time;

[0034] Step S105 , performing feedback control according to the heat flux value and the target heat flux value, and controlling the heat flux heating device to heat the aircraft test piece so as to reach the target heat flux value.

[0035] Specifically, refer to figure 2 , first obtain preset flight altitude information and preset flight speed information, the pre...

Embodiment 2

[0058] refer to image 3 , the present embodiment provides a heat flow control device for an aircraft aerothermal test, comprising:

[0059] An information acquisition module 201, configured to acquire preset flying height information and preset flying speed information of the aircraft;

[0060] The temperature acquisition module 202 is used to control the surface temperature of the real-time acquisition of the aircraft test piece;

[0061] A target heat flux calculation module 203, configured to calculate a target heat flux value according to the preset flight height information, preset flight speed information and surface temperature;

[0062] The heat flow collection module 204 is used to control the real-time collection of the heat flux value on the surface of the aircraft test piece;

[0063] The heating control module 205 is configured to perform feedback control according to the heat flux value and the target heat flux value, and control the heat flux heating device t...

Embodiment 3

[0068] refer to Figure 4 In this embodiment, a heat flow control system for an aircraft aerothermal test, a heat flow control device 301 for an aircraft aerothermal test, also includes:

[0069] A temperature sensor 302 for collecting the surface temperature of the aircraft test piece;

[0070] A heat flux sensor 303 for collecting the heat flux density value on the surface of the aircraft test piece;

[0071] A heat flow heating device 304 for heating the aircraft test piece.

[0072] For the structure and working principle of the heat flow control device 301 for the aircraft aerothermal test, please refer to Embodiment 1 and Embodiment 2, and details are not repeated here.

[0073] The temperature sensor 302 , the heat flow sensor 303 and the heat flow heating device 304 are respectively connected to the heat flow control device 301 of the aircraft aerodynamic thermal test.

[0074] The aircraft aerothermal test control system provided in this embodiment has a simple str...

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Abstract

The invention provides a heat flow control method, device and system for an aerothermodynamic experiment of an aircraft. The method comprises the steps that preset flying height information and preset flying speed information of the aircraft are acquired; the surface temperature of an aircraft experiment sample is collected in real time; a target heat flow density value is calculated according to the preset flying height information, the preset flying speed information and the surface temperature; a heat flow density value of the aircraft experiment sample is collected in real time; feedback control is performed according to the heat flow density value and the target heat flow density value, and a heat flow heating device is controlled to heat the aircraft experiment sample to reach the target heat flow density value. The simulation accuracy of an aerodynamic heating environment of the aircraft is effectively improved.

Description

technical field [0001] The invention relates to the technical field of ground simulation tests of an aircraft aerodynamic heating environment, in particular to a heat flow control method, device and system for an aircraft aerodynamic thermal test. Background technique [0002] The temperature control algorithm or heat flow control algorithm is usually used in the thermal environment ground simulation test. The temperature control algorithm takes the surface temperature of the specimen as the control object, and according to the set temperature-time curve, adjusts the output and output of the heating device by introducing temperature feedback, and simulates the surface temperature of the specimen throughout the process. However, it is difficult to obtain accurate thermophysical parameters for some specimens, and it is difficult to give a temperature curve, and it is impossible to use temperature control. The heat flow control algorithm takes the heat flow on the surface of t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N25/20
CPCG01N25/20
Inventor 刘鹏严超庞传和
Owner BEIJING RES INST OF MECHANICAL & ELECTRICAL TECH
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