A heat flow identification device and design method on the surface of a hypersonic vehicle

Abstract

The invention provides a hypersonic vehicle surface heat flow identification device and a design method, belonging to the technical field of hypersonic vehicle thermal parameter measurement. The device includes: heat conduction sensitive element, sensitive element heat insulation sleeve, sensitive element pressure plate, temperature sensor, the heat conduction sensitive element is a columnar structure, the sensitive element heat insulation sleeve is a columnar structure with through holes, and the heat conduction sensitive element is located in the sensitive element heat insulation sleeve In the through hole, it is matched with the thermal insulation sleeve of the sensitive element. One side of the sensitive element is flush with the outer surface of the thermal insulation sleeve to form a measuring end face. The bottom of the other side is equipped with a temperature sensor. The pressure plate of the sensitive element presses the heat conduction sensitive element. The heat insulation sleeve of the element is installed with gap fit, and the heat insulation sleeve of the sensitive element, the gap between the sensitive element and the heat insulation sleeve of the sensitive element, and the pressure plate of the sensitive element jointly block the heat exchange between the part of the heat conduction sensitive element except the measuring end face and the external environment. The invention overcomes the problems of poor adaptability of the traditional heat flow sensor for long-time high heat flow measurement, large sensor size, heavy weight, large installation restriction, and difficulty in realizing dense measurement.

Description

technical field [0001] The invention relates to an identification device for heat flow on the surface of a hypersonic vehicle and a design method thereof, especially suitable for intensive measurement of long-term high heat flow, and belongs to the technical field of thermal parameter measurement of a hypersonic vehicle. Background technique [0002] During high-speed flight, a hypersonic vehicle generates severe friction with the surrounding atmosphere, and the vehicle faces a severe aerodynamic heating environment. On the other hand, especially for hypersonic vehicles that perform gliding maneuvers, their aerodynamic shape is relatively complex, and flow phenomena such as shock wave interference between components and local separation and reattachment lead to complex distribution characteristics of the thermal environment on the surface of the vehicle. At present, it is still difficult to accurately predict the complex aerodynamic and thermal environment of hypersonic vehi...

AI Technical Summary

Problems solved by technology

[0005] The technical problem of the present invention is: in view of the poor adaptability of the traditional heat flow sensor to the long-term high heat flow measurement of the hypersonic aircraft and the problem that the large sensor size makes it difficult to perform intensive measurements, the present invention proposes an indirect measurement of the surface of the hypersonic aircraft The heat flow identification scheme and device are suitable for long-term high heat flow measurement, and overcome the problems of traditional heat flow sensors, such as large size, heavy weight, large installation restrictions, and difficulty in achieving intensive measurement

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