Parameter resembling method for aerodynamic thermal environment experimental simulation conditions

A technology for simulating conditions and environmental tests, applied in the aerospace field, can solve problems such as high test costs and large deviations in flight status, and achieve the effect of broadening test simulation conditions

Active Publication Date: 2018-12-18
DALIAN UNIV OF TECH
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Problems solved by technology

[0007] To sum up, the current ground test devices for hypersonic aerodynamic thermal environment simulation generally use the two parameters of cold wall heat flow and recovery enthalpy as similar parameters; Carry out a simulation test, but the cost of this test is very high; for the recovery enthalpy value below 4000kJ / kg, the simulation test can be carried out in a combustion wind tunnel; other test devices only simulate the heat flow of the cold wall without considering the effect of the recovery enthalpy, Big deviation from flight status

Method used

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  • Parameter resembling method for aerodynamic thermal environment experimental simulation conditions
  • Parameter resembling method for aerodynamic thermal environment experimental simulation conditions
  • Parameter resembling method for aerodynamic thermal environment experimental simulation conditions

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Embodiment 1

[0029] Embodiment 1: Simulate the aerodynamic thermal environment with high enthalpy and low heat flow faced by an aircraft flying at an altitude of 75km and a Mach number of 10Ma.

[0030] (1) Consult the atmospheric parameter table, the airflow temperature T at an altitude of 75km ∞ =208.399K, density ρ=3.992×10 -5 kg / m 3 . According to the Mach number Ma ∞ =10, specific heat ratio of air γ=1.4, temperature recovery coefficient r=0.89, calculate recovery temperature of airflow enthalpy of recovery

[0031] (2) Calculate the convective heat transfer coefficient on the surface of the aircraft structure in the flight state

[0032] alpha 1 =0.0296(Re 1 * ) -1 / 2 (Pr 1 * ) -2 / 3 (ρυ) ∞ c p =2.8W / m 2 · K.

[0033] (3) Calculate the cold wall heat flow q 01 = α 1 (T r1 -T 0 )=9.69kW / m 2 .

[0034] (4) Obtain the wall surface temperature T of the aircraft structural material through heat transfer calculation w1 = 638K.

[0035] (5) Assume that the total air...

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Abstract

The invention belongs to the technical field of aerospace, and relates to a parameter resembling method for aerodynamic thermal environment experimental simulation conditions. According to the requirement of equivalence of recovery enthalpy and cold wall heatflow in an aerodynamic thermal environment experiment, a method of guaranteeing ground test parameters being similar to flight parameters without recovery enthalpy equivalence, and the problems at the present stage that experimental simulation method depends on recovery enthalpy equivalence and accurate simulation of the real aerodynamic heat environment is difficult are solved. A guarantee for heat transfer and ablation experimental study of thermal shielding/insulation material in the high temperature aerodynamic thermal environmentis provided. The parameter resembling method has the beneficial effects that experimental conditions are not affected by recovery enthalpy value; most test equipment can simulate the high enthalpy aerodynamic thermal environment; a new way of parameter adjustment for high enthalpy wind tunnel testing is provided; and the experimental simulation conditions are broadened.

Description

technical field [0001] The invention belongs to the field of aerospace technology, and relates to a test simulation method for the aerodynamic thermal environment of an anti / heat insulation material, in particular to a parameter similar method for high-temperature aerodynamic thermal environment simulation test conditions when it is difficult to ensure that the recovery enthalpy and cold wall heat flow are equal at the same time. Background technique [0002] When the aircraft flies at supersonic speed and hypersonic speed, it will face extremely harsh aerothermal environment and be subjected to strong aerodynamic heat and aerodynamic force. In order to study the working state of the aircraft's external heat protection structure in a complex aerodynamic and thermal environment, it is necessary to simulate the real aerodynamic and thermal environment of the aircraft through ground tests, and to evaluate the performance indicators of the thermal protection structure materials, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06G01M9/02
CPCG01M9/02G01M9/065G01N25/18G01M9/04G01M99/002
Inventor 孙得川卢明
Owner DALIAN UNIV OF TECH
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