Test method for simulating thermal environment in aircraft flight process

Abstract

The invention discloses a test method for simulating a thermal environment in an aircraft flight process. The simulation of the thermal environment is realized through an arc tunnel test, and comprises the following steps: (1) a curve of heat flow density, changed along with the time, of an aircraft trajectory is fitted to a curve of heat flow density changed along with time in the arc tunnel test; (2) multiple time periods on the curve of heat flow density changed along with time in the arc tunnel test are read; each time period is corresponding to a heat flow density; and input parameters of laminated type arc heaters are set according to the time periods and the heat flow densities corresponding to the time periods; and (3) the input parameters corresponding to the multiple time periods are set in a controller in sequence to control the completion of the simulation test of the thermal environment in the aircraft flight process. The test method, provided by the invention, uses a computer for controlling, operates the thermal environment changed in the aircraft flight process in primary test process, and can simulate the thermal environment of an aircraft in the flight process more really.

Description

technical field [0001] The invention relates to a test method for simulating the thermal environment during flight of an aircraft. More specifically, the present invention relates to a test method for simulating a variable thermal environment during flight of an aircraft through one test. Background technique [0002] When the spacecraft flies through the atmosphere at a very high speed, a complex flow field is formed around it. Due to its compression of the air in front and friction with the surrounding air, most of its kinetic energy will be consumed in the form of shock waves and wake vortices. Dissipated in the atmosphere, the remaining part of the kinetic energy is converted into heat energy of the air. This thermal energy heats the surface of the spacecraft in two forms: boundary layer convective heating and shock radiation. The thermal environment of the spacecraft flying in the atmosphere will be the main basis for the design of the heat protection system, includin...

AI Technical Summary

Problems solved by technology

[0007] The thermal assessment test of the heat-proof structure is generally carried out in the arc wind tunnel. For the arc heater, it is impossible to completely simulate the heating of the aircraft during the entire flight process.

[0008] The laminated arc heater has become one of the main heaters for aerodynamic thermal tests in various countries around the world due to its low pressure, high enthalpy, pollution-free and long-term stable operation. However, due to the complicated air intake structure of this heater, the international Most countries use laminated arc heaters for some simple single-state high-enthalpy experiments

But for aircraft or missiles, each launch must fly along a specific orbit, and with the change of flight altitude and Mach number during the flight, the thermal environment experienced by the aircraft is also changing all the time. The test state cannot meet the needs of thermal environment simulation during the entire flight, so it is particularly important to use the stacked arc heater wind tunnel test to realize the simulation ability of variable thermal environment through one test.

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