Infrared radiation heat flow density reinforcement device for high temperature pneumatic thermal simulating test of missile

Abstract

The invention relates to an infrared radiation heat flow density reinforcement device for a high temperature pneumatic thermal simulating test of a missile, comprising a quartz lamp heating array, a blower, a variable frequency speed controller, a quartz glass airflow isolation board, a high temperature radiation test piece, a water cooling box, a heat flux sensor, a temperature sensor and a computer. A one-way airflow guiding isolation channel is formed by the quartz glass airflow isolation board, and flow guiding blades are driven to rotate at high speed by a motor of the blower to form a one-way strong airflow; and in the high temperature transient pneumatic thermal test of simulating the hypersonic speed flying of the missile, the strong airflow flows the surface of the quartz lamp heating array in the isolation channel such that the temperature is reduced below the softening temperature of the quartz glass. Because the heat flow density received by the surface of the high temperature radiation test piece of the missile in a heat intensity experiment exceeds the limit of 1 Mw / m<2> when the wind cooling is not carried out, the transient heat flow density can reach 2 Mw / m<2>. The invention provides a more efficient dynamic thermal radiation high temperature testing means for developing the hypersonic speed missile with faster flying speed.

Description

technical field [0001] The invention relates to an infrared radiation heat flux enhancement device for a high-temperature aerodynamic heat simulation test of a missile. Especially when simulating the aerodynamic heating environment of the missile hypersonic flight test, the test device increases the instantaneous radiation heat flux to 2Mw / m2. Provide effective high-temperature test means for the development of faster-flying hypersonic missiles. Background technique [0002] Due to the needs of defense penetration, anti-missile, high-altitude and high-speed reconnaissance, missiles and other aircraft are flying faster and faster. The flight Mach number of air defense missiles and air-to-air missiles has exceeded 6 Mach numbers. And the instantaneous heat flux density of the cone of the radome at the front end of the missile is as high as 1.2Mw / m2, and the stagnation point temperature will exceed 1200°C. The high temperature generated by serious aerodynamic heating will red...

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Problems solved by technology

Therefore, when the surface temperature of the test piece 50-100mm away from the heater reaches 1100°C, the surface temperature of the heater as a heat source will be close to the softening temperature of quartz glass at 1600°C, causing the vacuum seal of the quartz heater to leak, which in turn causes Tungsten filament burnt by high temperature oxidation

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