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Hypersonic aircraft thermal protection material ground simulation test system and method

A thermal protection material and ground simulation technology, applied in the field of laser technology and application, can solve the problems of lack of hot air flow conditions, low test cost, and inability to truly simulate the oxidation and ablation effect of re-entry environment, so as to avoid long preparation time Effect

Active Publication Date: 2019-10-18
NORTHWEST INST OF NUCLEAR TECH
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  • Summary
  • Abstract
  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

The advantage of this equipment is that the size of the test piece can be large, the test cost is low, and multiple tests can be carried out in a short period of time. The disadvantage is that the radiation heating test lacks the flow conditions of the hot air flow and cannot truly simulate the oxidation ablation of the re-entry environment. function, and the temperature is generally below 1700°C

Method used

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  • Hypersonic aircraft thermal protection material ground simulation test system and method
  • Hypersonic aircraft thermal protection material ground simulation test system and method
  • Hypersonic aircraft thermal protection material ground simulation test system and method

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Embodiment

[0078] see figure 1 and figure 2 , a ground simulation test system for thermal protection materials for hypersonic aircraft, including a laser 1, a laser beam 2, a microlens array 3, a collimating lens 4, a graphite diaphragm 5, a thermal imager 6, an electronic universal testing machine 7, and a test piece 8. Down suction device 9, oxygen cylinder 10, nitrogen cylinder 11, mixing container 12, oxygen flow control valve 13, nitrogen flow control valve 14, mixed gas flow control valve 15, air flow nozzle 16, pitot tube 17 , barometer 18 and mechanical loading rod 19;

[0079] The test piece 8 is installed on the electronic universal testing machine 7;

[0080] The laser beam 2 generated by the laser 1 passes through the microlens array 3, the collimator lens 4 and the graphite diaphragm 5 in sequence, and then the laser beam emitted from the small hole of the graphite diaphragm 5 covers the test piece 8 completely;

[0081] The thermal imager 6 is used to monitor the temper...

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Abstract

The invention discloses a hypersonic aircraft thermal protection material ground simulation test system and method. In a ground test process, a laser is used for heating a test piece, simulated airflow is loaded on the surface of the test piece, and an external force is loaded on the test piece through an electronic universal testing machine. Therefore, the material mechanical properties of the hypersonic aircraft thermal protection material in a real environment are simulated and evaluated, and finally, the thermal protection properties of the hypersonic aircraft material and the structure are inspected. The method has the characteristics of simple equipment, low test cost, high heating rate, high test temperature and wide application range.

Description

technical field [0001] The invention belongs to the field of laser technology and application, and relates to a simulation test system, in particular to a thermal protection material for a hypersonic aircraft which uses a high-energy continuous laser to simulate aerodynamic heating, surface airflow to simulate high-speed airflow oxidation and erosion, and a mechanical loading system to simulate aerodynamic load Ground simulation test system and method. Background technique [0002] A hypersonic vehicle will be subjected to intense aerodynamic heating during reentry, and a thermal protection system is essential. Before it is actually put into use, hypersonic vehicles must undergo thermal protection and thermal structural test assessments. At present, there are three general testing methods: one is to use a plasma arc wind tunnel to generate a high-pressure airflow with high enthalpy, high heat flow, and long time to simulate the process of aerodynamic heating, such as the Ge...

Claims

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Application Information

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IPC IPC(8): G01N25/20
CPCG01N25/20
Inventor 王家伟张冉朱永祥韦成华马志亮吴丽雄王立君
Owner NORTHWEST INST OF NUCLEAR TECH
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