A self-adaptive thermal protection method for aircraft head

Abstract

The invention provides an aircraft head self-adaptive thermal protection method and relates to the field of high-speed pneumatic thermal protection and the field of high-speed aerodynamics. The aircraft head self-adaptive thermal protection method comprises the steps of determining a head temperature increasing part, mounting a thermocouple and presetting desired flow and pressure of the gas sprayed by an aerospike during the flying of an aircraft; and adjusting the flow and pressure of the gas sprayed by the aerospike in time, wherein the adjusting process is continuously repeated in circulation until the surface temperature is reduced and thermal ablation of the surface is prevented. According to the aircraft head self-adaptive thermal protection method, as the thermocouple is mounted at the part, where the head temperature rise can be sensed, on the inner wall surface of a supersonic speed or hypersonic speed aircraft, the opening of a valve is adjusted according to the temperature measured by the thermocouple; meanwhile, by controlling the pressure of the gas sprayed by the aerospike, the turbulent flow situation of an incoming flow on the head of the aircraft can be finally changed to reduce the surface temperature and prevent thermal ablation of the surface; and therefore, a thermal protection effect on the head of the aircraft is achieved.

Description

technical field [0001] The invention relates to the field of high-speed aerodynamic thermal protection and the field of high-speed aerodynamics, in particular to an adaptive thermal protection method for the head of an aircraft. Background technique [0002] Aircraft, especially blunt-nosed aircraft, will form a bow-shaped appendage shock wave on the warhead during high-speed flight, which will have a strong compression effect on the incoming flow, and at the same time, the head will produce severe friction with the incoming flow, resulting in a sharp rise in air temperature. Therefore, during the flight, the warhead experiences high-speed, high-pressure, and high-temperature environments, which will seriously ablate the surface materials of the warhead, destroy the structure of the aircraft, or cause the internal temperature of the aircraft to rise, posing a threat to the safety analysis of the aircraft. [0003] In order to prevent the head of the aircraft from being burne...

AI Technical Summary

Problems solved by technology

[0002] Aircraft, especially blunt-nosed aircraft, will form a bow-shaped appendage shock wave on the warhead during high-speed flight, which will have a strong compression effect on the incoming flow, and at the same time, the head will produce severe friction with the incoming flow, resulting in a sharp rise in air temperature. Therefore, during the flight, the warhead experiences high-speed, high-pressure, and high-temperature environments, which will seriously ablate the surface materials of the warhead, destroy the structure of the aircraft or cause the internal temperature of the aircraft to rise, posing a threat to the safety analysis of the aircraft.

[0003] In order to prevent the head of the aircraft from being burned, thermal protection measures are required. The current existing methods mainly include the following three aspects: first, add an anti\heat insulation surface layer outside the aircraft to prevent structural ablation damage and isolate external heat. The method increases the weight of the aircraft, reduces the capacity of the aircraft, and the cost of heat insulation materials is high, so it cannot be reused; the second method is to install a shock needle on the head of the aircraft to push the shock wave away from the warhead, and at the same time form a low pressure on the surface of the warhead area, lower the surface temperature, but the shock wave is attached to the front of the shock needle during the flight, causing the shock needle to be easily ablated and damaged, reducing the thermal protection effect, and it needs to be replaced in time, otherwise there will be thermal ablation of the aircraft head Question; the third method is to use energy delivery (such as shock wave, low light) at the head of the projectile to push the shock wave away from the projectile, but the research is still in progress and it is not yet mature

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