Heating and cooling control device and method for aircraft aerodynamic thermal environment simulation test

Abstract

The invention discloses a heating and cooling control device and method for an aerodynamic thermal environment simulation test of an airplane, and the device comprises an air homogenizing box, an air transmission mechanism which is disposed at the upper part of the air homogenizing box and is used for providing cold air, and a heating mechanism which is disposed at the lower part of the air homogenizing box and is used for heating a tested piece. The tested piece is provided with the first temperature sensor used for collecting the temperature of the tested piece, so that the tested piece is heated and cooled, the surface temperature of the tested piece can be repeatedly and rapidly changed, and a real aerodynamic thermal environment of an airplane during hypersonic flight is conveniently simulated. The method comprises the following steps: 1, determining a heating and cooling control target curve of an aircraft aerodynamic thermal environment simulation test; 2, carrying out an aircraft aerodynamic thermal environment simulation test; 3, heating operation; and 4, cooling operation is carried out, so that the surface temperature of the tested piece is repeatedly adjusted and collected, and the accuracy and the flexibility of the aerodynamic thermal environment simulation test of the airplane are enhanced.

Description

technical field [0001] The invention belongs to the technical field of aircraft aerodynamic thermal environment simulation test, and particularly relates to a temperature rise and fall control device and method for aircraft aerodynamic thermal environment simulation test. Background technique [0002] When the aircraft flies at hypersonic speed in the atmosphere, the air is severely compressed and viscous, and the airflow in the boundary layer of the aircraft surface will generate strong friction, the airflow speed will drop to the wall, and the kinetic energy will be irreversibly turned into heat energy. As a result, the temperature in the boundary layer rises rapidly, and the surface temperature of the aircraft also increases. This is the aerodynamic heating phenomenon of high-speed aircraft. Therefore, the research on aerodynamic heating of high-speed aircraft is a problem that must be paid attention to in the thermal protection design of high-speed aircraft. [0003] In ...

AI Technical Summary

Problems solved by technology

[0003] In the process of simulating the aerodynamic thermal environment of high-speed aircraft in the ground test, the temperature rise stage of the object under test can be well simulated at present, but the cooling stage of the simulated object under test mainly relies on natural cooling. When the actual cooling rate of the aircraft is too fast, the ground The natural cooling rate in the test is not enough to simulate the actual situation, and it is impossible to conduct an effective test, and the test results are prone to incompleteness, so it is impossible to determine whether the tested object will fail in the real service state

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