Identification apparatus for surface heat flux of hypersonic flight vehicle and design method thereof

Abstract

The invention, which belongs to the technical field of thermal parameter measurement of a hypersonic flight vehicle, provides an identification apparatus for a surface heat flux of a hypersonic flightvehicle and a design method thereof. The apparatus is composed of a thermal-conduction sensitive element, a sensitive element insulating sleeve, a sensing element pressing plate, and a temperature sensor. The thermal-conduction sensitive element has a cylindrical structure. The sensitive element insulating sleeve has a cylindrical structure with a through hole. The thermal-conduction sensitive element is arranged in the through hole of the sensitive element insulating sleeve and is in a clearance fit with the sensitive element insulating sleeve. One side of the sensitive element is flush withthe outer surface of the insulating sleeve to form a measuring end surface and the temperature sensor is installed at the bottom of the other side of the sensitive element. The sensing element pressing plate presses the thermal-conduction sensitive element and is in a clearance fit with the sensitive element insulating sleeve; the sensitive element insulating sleeve, the gap between the sensitiveelement and the sensitive element insulating sleeve, and the sensing element pressing plate prevent the parts, except the measuring end surface, of the thermal-conduction sensitive element from carryout heat exchange with an external environment. Therefore, problems that the traditional heat flux sensor has the poor adaptability to the long-term high heat-flux measurement, the sensor size is large, the sensor is heavy, the installation difficulty is high, and intensive measurement can not be realized easily can be solved.

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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