Heat-flow meter for measuring heat flux of aluminium oxide inside solid rocket engine dynamically in real-time

Abstract

The invention discloses a heat-flow meter for measuring heat flux of aluminium oxide inside a solid rocket engine dynamically in real-time. The heat-flow meter comprises a heat-flow meter body including a cylindrical heat-sink copper piece and a constantan piece that are arranged coaxially. A thermal-insulation ceramic plate that is used for cooling high-temperature heat flux at the surface of the constantan piece is arranged at the top of the constantan piece coaxially; and the outer sides of the thermal-insulation ceramic plate, the constantan piece, and the heat-sink copper piece are coated with a beryllium-oxide ceramic housing and the thermal-insulation ceramic plate is fixed at the top of the constantan piece by the beryllium-oxide ceramic housing. The beryllium-oxide ceramic housing is used for guiding one part of heat flux to the matrix of the heat-sink copper piece. A heat-sink copper hole is formed along the axis direction inside the heat-sink copper piece; and a thermocouple for measuring the top temperature of the heat-sink copper piece is installed approaching the constantan piece inside the heat-sink copper hole. Therefore, a problem that condensed-phase particle washing or density measurement of disposition heat flux inside a solid rocket engine can not be realized on the high-temperature, high-pressure, and high-heat-flux conditions can be solved.

Description

[0001] 【Technical field】 [0002] The invention belongs to the technical field of solid rocket motors, in particular to a heat flow meter for dynamically and real-time measuring the heat flux density of alumina in the solid rocket motor. [0003] 【Background technique】 [0004] During the working process of the solid rocket motor, the violent combustion of the propellant will generate a high-temperature and high-speed gas flow of 2500-3900K, and the heat flow generated by the high-temperature gas will seriously ablate the thermal protection material of the engine. At the same time, the condensed phase particles in the combustion products will cause serious erosion and erosion to the submerged section and the convergent section of the nozzle, thereby greatly increasing the thermal load of the engine. In order to ensure that the rocket engine can maintain normal work under harsh thermal environmental conditions, and that the spacecraft will not be burned due to the external heati...

AI Technical Summary

Problems solved by technology

[0011] The purpose of the present invention is to provide a heat flow meter for dynamic and real-time measurement of alumina heat flux in solid rocket motors, so as to overcome the problem of being unable to measure condensed phase particle erosion or deposition heat flux under high temperature, high pressure and high heat flow conditions in solid rocket motors

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