CN110318878B

CN110318878B - Aerospace plane active cooling system based on magnetofluid energy bypass

Info

Publication number: CN110318878B
Application number: CN201910508508.5A
Authority: CN
Inventors: 王浩然; 尹顺华; 边磊; 付春楠; 沈杰
Original assignee: Inner Mongolia Power Machinery Research Institute
Current assignee: Inner Mongolia Power Machinery Research Institute
Priority date: 2019-06-13
Filing date: 2019-06-13
Publication date: 2022-08-09
Anticipated expiration: 2039-06-13
Also published as: CN110318878A

Abstract

The invention relates to a magnetic fluid energy bypass-based active cooling system for an aerospace plane, which comprises an aircraft active cooling wave carrier and an aircraft active cooling lip, wherein the aircraft active cooling wave carrier is arranged at the front edge of the aircraft, the aircraft active cooling lip is arranged at the front edge of an air inlet of a ramjet engine, the aircraft active cooling wave carrier and the aircraft active cooling lip respectively comprise a high-temperature alloy heat pipe and an aircraft skin, the high-temperature alloy heat pipe is positioned at the inner side of the aircraft skin, an internal flow channel of the high-temperature alloy heat pipe corresponds to the thermal environment of the aircraft determined by a flight envelope, and a liquid alkali metal coolant is introduced into the internal flow channel of the high-temperature alloy heat pipe. The invention adopts the magnetohydrodynamic principle, collects the total temperature in high-speed incoming flow by utilizing the magnetohydrodynamic power generation technology, can effectively expand the working range of the ramjet, postpones the modal start of the rocket engine and improves the fuel efficiency of the aerospace plane.

Description

Aerospace plane active cooling system based on magnetofluid energy bypass

Technical Field

The invention relates to a cooling system, in particular to an aerospace plane active cooling system based on a magnetofluid energy bypass.

Background

The space plane is a reusable aircraft which can automatically glide and land back after taking off from the ground (launching) and entering a space orbit to execute a load launching task. The process of entering the orbit needs to go through a series of complex flight states such as static, subsonic flight, supersonic flight, hypersonic flight, extraatmospheric flight and the like. The aircraft power system needs to adopt a combined power technology integrating a ram engine and a rocket engine and carries out power system mode conversion according to the flying height and the flying speed. Currently, the more studied Combined power technologies include Rocket-Based Combined Cycle (Rocket-Based Combined Cycle), Turbine-Based Combined Cycle (turbo-Based Combined Cycle), precooled engine and the like. The aircraft is accelerated to a first cosmic speed of 7.9km/s for realizing the orbit entering, and the flight speed is about 25Ma in the atmosphere. In order to reduce the structural weight of the aircraft and improve the carrying efficiency, the use of an oxidant carried by the aircraft is reduced as much as possible in the flight process, the air is captured through a ram air inlet channel as much as possible to organize the combustion, and the starting of a rocket engine mode is delayed. But when the flying speed exceeds 7Ma, the inflow stagnation temperature exceeds 3300K; after 12Ma is exceeded, when the air inlet channel is pressurized to 1.5Ma, the static temperature of the combustion chamber reaches 5000K, and the limit of the current non-ablative thermal protection material is exceeded. Meanwhile, when the inlet temperature of the combustion chamber is more than 1670K, the engine cannot work normally due to the fact that the heat value added by combustion cannot effectively generate thrust. Because the engine is switched to a rocket engine mode when the flying speed is higher, the realization of the air inlet cooling technology of the 7-12 Ma incoming flow down-thrust engine is a key technology for realizing combined power circulation. The invention realizes the artificial auxiliary ionization of the incoming air flow by means of alkali metal or electron beams and the like, and realizes the high-speed incoming flow power extraction, the energy supply of the aircraft and the exhaust acceleration by Magnetohydrodynamics (MHD).

The combined power technology integrates advanced technologies of a ramjet engine and a rocket engine, and is suitable for large-range flight envelope. The aircraft such as a carrier rocket, a space shuttle and the like adopts a rocket engine to lift off in a vertical launching mode. The working time of more than 7Ma in the flight process in the atmosphere is relatively short, and the passive thermal protection is basically carried out by adopting an ablation-resistant material. The carrier rocket is mostly disposable, and passive thermal protection is carried out by adopting an anti-ablation material. The space shuttle has certain repeated use capability, but detection and replacement of high-temperature parts such as heat-proof tiles, high-pressure turbines of engines and the like are required after the space shuttle returns, and the high use cost and the long use preparation period directly cause the retirement of the space shuttle. Meanwhile, the sub-combustion ramjet technology and the liquid rocket engine technology are relatively mature, the super-combustion ramjet has already completed multiple tests, the flight speed of over 5Ma is broken through, higher flight speed test research is actively carried out in various countries, and key technologies such as power system mode conversion are preliminarily verified.

The most advanced air-breathing hypersonic aircraft at present adopts a scramjet engine. The cruising speed in the atmosphere of the aircraft is difficult to break through 8Ma under the influence of high-speed incoming flow pneumatic heating and other environments. Meanwhile, because the aircraft does not carry rotating parts such as a turbine and the like, long-time energy supply of aircraft instruments and equipment cannot be realized.

Disclosure of Invention

The invention aims to provide an aerospace plane active cooling system based on a magnetofluid energy bypass, and aims to solve the problems of structural cooling and aircraft energy management and control in the flight process of an aerospace plane adopting combined power.

In order to solve the existing technical problems, the technical scheme adopted by the invention is as follows: the aerospace plane active cooling system based on the magnetic fluid energy bypass comprises an aircraft active cooling wave carrier and an aircraft active cooling lip, wherein the aircraft active cooling wave carrier is arranged on the front edge of the aircraft, the aircraft active cooling lip is arranged on the front edge of an air inlet of a ramjet engine, the aircraft active cooling wave carrier and the aircraft active cooling lip comprise a high-temperature alloy heat pipe and a high-temperature-resistant aircraft skin, the high-temperature alloy heat pipe is located on the inner side of the aircraft skin, an internal flow channel of the high-temperature alloy heat pipe corresponds to the thermal environment of the aircraft determined by a flight envelope, a liquid alkali metal coolant is introduced into the internal flow channel of the high-temperature alloy heat pipe, and when the alkali metal coolant flows in the internal flow channel of the high-temperature alloy heat pipe, the heat of the structure is absorbed in the forced convection heat exchange process, and the aircraft is actively cooled.

In order to improve the ionization capacity of high-temperature high-speed incoming flow gas of an air inlet, the aircraft active cooling wave multiplier (11) further comprises an alkali metal coolant injector (12), the alkali metal coolant injector (12) is located below the aircraft active cooling wave multiplier (11) and embedded on the surface of the air inlet on the skin (23) of the aircraft, and the alkali metal coolant injector (12) injects part of alkali metal in the high-temperature alloy heat pipe (22) into the air flow in the air inlet. In addition, the aircraft active cooling lip (17) also comprises an alkali metal coolant injector (12), the alkali metal coolant injector (12) is positioned above the aircraft active cooling lip (17) and embedded on the surface of an air inlet on the skin (23) of the aircraft, and the alkali metal coolant injector (12) injects part of alkali metal in the high-temperature alloy heat pipe (22) into the air flow in the air inlet.

In order to further reduce the temperature of air flow in the ramjet air inlet, the aerospace plane active cooling system further comprises an annular magnetofluid power generation channel, wherein the annular magnetofluid power generation channel is positioned at the outer ring of the ramjet air inlet, is a Faraday type magnetofluid generator and is prepared by surrounding the ramjet air inlet by a metal coil.

In order to better accelerate and vector control magnetofluid fuel gas, the aerospace plane active cooling system can further comprise an annular electromagnetic accelerating channel, wherein the annular magnetofluid power generation channel is located on the outer ring of the ramjet nozzle and is prepared by surrounding the ramjet nozzle with a metal coil.

The alkali metal injection device can adopt a mechanism or an electronic control valve and the like, and particularly, the invention also discloses the alkali metal injection device which consists of a composite material laminated valve plate and a shape memory alloy valve plate, wherein the composite material laminated valve plate is positioned outside the injection device and is contacted with incoming air; the shape memory alloy valve plate is positioned at the inner side of the injection device and is contacted with an incoming alkali metal coolant, when the temperature rises, the shape memory alloy valve plate is formed to drag the composite material laminated valve plate to open, and the alkali metal coolant flows out along the opening gap and is injected into the air inlet.

In general, the alkali metal coolant, the high-temperature alloy heat pipe and the aircraft skin can be made of any existing material suitable for the invention, and particularly, the alkali metal coolant is preferably made of an alloy material consisting of lithium sodium potassium; the high-temperature alloy heat pipe preferably adopts nickel-based high-temperature alloy or rhenium-molybdenum high-temperature alloy; the aircraft skin is preferably made of ultra-high temperature ceramic materials.

The invention is suitable for the active cooling of the air inlet of the aerospace plane, the power extraction of high-temperature airflow and the control of high-temperature fuel gas. After the aircraft takes off, the aircraft is carried to the flying speed of more than 3Ma by a boosting rocket or a carrier, and after the supersonic air inlet channel is started, the ramjet starts to work, so that the flying speed is greatly improved. And (3) actively cooling high-temperature parts such as the front edge, the lip and the like of the air inlet of the aircraft by using the alkali metal high-temperature heat pipe. When the flying speed exceeds more than 8Ma, a control valve on the supersonic air inlet channel for actively cooling the high-temperature heat pipe is opened, and fuel containing alkali metal is sprayed into the air inlet channel to realize the artificial auxiliary ionization of the incoming air flow. The charged gas flow enters a magnetic fluid power generation channel to cut magnetic induction lines to generate electric energy, and the fuel-air mixed gas enters a combustion chamber to be combusted after speed reduction, diffusion and power generation. A magnetic fluid accelerating channel is arranged behind a Laval nozzle of the aircraft to accelerate high-temperature and high-speed fuel gas containing alkali metal ionization seeds, so that the exhaust speed of the aircraft is improved. The electric energy generated in the magnetohydrodynamic electricity generation process is mainly used for gas acceleration besides supplying power to aircraft equipment. The energy which cannot be taken by the air inlet channel is utilized through the electromagnetic bypass.

The invention realizes the active convection cooling of the high-temperature area of the air inlet by using the alkali metal high-temperature heat pipe; the ionization of the intake air flow is realized by utilizing alkali metal vaporization mixing, the kinetic energy and the internal energy of the charged air flow are converted into electric energy through the intake duct magnetohydrodynamic generator, and the temperature of the intake air flow is reduced while the power is supplied to the aircraft; the magnetic fluid accelerator is arranged near the engine spray pipe to control the flow of the charged fuel gas containing alkali metal components, and three working effects of fuel gas acceleration, thrust vector control and the like are realized.

Advantageous effects

When the temperature of the inlet gas of the combustion chamber of the air-breathing engine is more than 1670K, the fuel is rapidly cracked after being injected, and the added heat value of the combustion cannot effectively generate thrust, so that the engine cannot normally work. When the flying speed exceeds 7Ma, the stagnation temperature of the high-speed airflow exceeds 3300K; after 12Ma is exceeded, when the air inlet channel is pressurized to 1.5Ma, the static temperature of the combustion chamber reaches 5000K, and the limit of the current non-ablative thermal protection material is exceeded. Therefore, the cruising flight limit speed of the current ramjet engine is less than 7Ma and can only be maintained for a short time at higher flight speed. The invention adopts the magnetohydrodynamic principle, collects the total temperature in high-speed incoming flow by utilizing the magnetohydrodynamic power generation technology, can effectively expand the working range of the ramjet, postpones the modal start of the rocket engine and improves the fuel efficiency of the aerospace plane.

Drawings

FIG. 1 is a schematic representation of a cross-sectional view of the operation of an integrated engine aircraft, including: the aircraft active cooling wave multiplier 11, an alkali metal coolant injector 12, an annular magnetohydrodynamic power generation channel 13, an alkali metal-containing fuel injection hole 14, an electromagnetic energy controller 15, an annular electromagnetic acceleration channel 16 and an aircraft active cooling lip 17;

FIG. 2 is a schematic view of an integrated engine aircraft leading edge, including: an alkali metal coolant 21, a superalloy heat pipe 22, an aircraft skin 23;

FIG. 3 is a schematic view of the alkali metal injector 12, including: a composite material laminated valve plate 32 and a shape memory alloy valve plate 33;

fig. 4 is a schematic view showing the opening of the alkali metal injector 12.

Detailed Description

The invention is further described with reference to the following figures and specific embodiments.

As shown in FIG. 1, the aircraft working section with integrated engines comprises an aircraft active cooling wave multiplier 11, an alkali metal coolant injector 12, an annular magnetofluid power generation channel 13, an alkali metal-containing fuel injection hole 14, an electromagnetic energy control system 15, an annular electromagnetic acceleration channel 16 and an aircraft active cooling lip 17.

The aircraft active cooling wave rider 11 is arranged at the front edge of the aircraft, and the structural form is shown in figure 2, and the aircraft active cooling wave rider consists of a high-temperature alloy heat pipe 22, an alkali metal alloy coolant 21, an aircraft skin 23 and an alkali metal injection device 12.

The alkali metal coolant injector 12 is located below the aircraft active cooling wave multiplier 11, a shape memory alloy temperature control valve is adopted to open an injection hole, the alkali metal coolant injector is arranged inside an air inlet channel, the gas flow rate at a corresponding position is about 3-4 Ma, the arrangement form is shown in figure 2, the specific arrangement form can be selected according to actual needs, the structure form is shown in figure 3, and the alkali metal coolant injector is formed by bonding a composite material laminated valve plate 32 and a shape memory alloy valve plate 33.

The annular magnetic fluid power generation channel 13 adopts a segmented Faraday type magnetic fluid generator on the outer wall of the air inlet channel supporting structure; the annular magnetic fluid power generation channel 13 is positioned at the outer ring of the air inlet channel of the ramjet and is a Faraday type magnetic fluid generator which is prepared by surrounding the air inlet channel of the ramjet by a metal coil.

The alkali metal-containing fuel injection holes 14 are located between the integrated aircraft intake and the combustion chamber for injecting hydrocarbon fuel containing alkali metal components.

The electromagnetic energy control system 15 is positioned in the integrated engine aircraft body and is used for collecting electric energy generated by the annular magnetic fluid power generation channel 13 and transmitting the electric energy to aircraft electromechanical equipment.

The annular electromagnetic accelerating channel 16 is positioned on the outer ring of the ramjet nozzle, is prepared by surrounding the ramjet nozzle with a metal coil, and is used for accelerating and vector controlling the magnetofluid fuel gas.

The aircraft active cooling lip 17 is arranged at the front edge of the stamping air inlet, and the structural form is shown in figure 2, and the aircraft active cooling lip is composed of a high-temperature alloy heat pipe 22, an alkali metal coolant 21, an aircraft skin 23 and an alkali metal injection device 12.

The whole system working process is as follows: the high-speed airflow above 7Ma stagnates at the positions of the active cooling wave-rider 11 of the aircraft and the active cooling lip 17 of the aircraft, the static temperature of the airflow exceeds 2500K, and the active cooling is carried out by utilizing the alkali metal high-temperature alloy heat pipe 22. The air flow is decelerated and pressurized by the oblique shock wave of the air inlet channel below the front edge, and the static temperature of the fuel gas is increased along with the flow of the gas. The liquid alkali metal coolant 21 flows in the direction shown by the arrow in fig. 1 and 2, and active cooling is performed by forcing the heat of the absorption structure during the heat convection process, and a small amount of alkali metal is sprayed out of the alkali metal coolant injector 12 after cooling. After the high-temperature high-speed incoming flow gas is added into the alkali metal seeds, the ionization capacity is greatly improved. The high-speed electrified airflow cuts the magnetic induction lines of the annular magnetohydrodynamic power generation channel 13 to generate electric energy, and the kinetic energy of the flowing gas is converted into the electric energy. After the kinetic energy of the gas is converted into electric energy, the total temperature is reduced, the hydrocarbon fuel is fully mixed with the liquid alkali metal after the alkali metal coolant injection hole 12, and the hydrocarbon fuel continuously flows in the arrow direction and is injected into the combustion chamber through the alkali metal fuel injection hole 14 to be combusted. The fuel gas containing alkali metal components is fully combusted in a combustion chamber of the ramjet engine and then is discharged out of the engine through a spray pipe. The annular electromagnetic accelerating channel 16 generates a high-intensity magnetic field to accelerate and deviate ions of the electrified high-temperature fuel gas, so that the thrust increase and the vector control are realized. The electric energy generated by the annular magnetic fluid power generation channel 13 supplies power to aircraft equipment through the electromagnetic energy controller 15, and the rest energy is transmitted to the annular electromagnetic acceleration channel 16 to generate an outlet high-intensity magnetic field. The process that energy flows through the annular magnetic fluid power generation channel 13 from high temperature and is transferred to the annular electromagnetic acceleration channel 16 by the electromagnetic energy controller 15 is a magnetic fluid energy bypass system.

FIG. 2 shows an integrated engine-aircraft waverider, lip leading edge, consisting of an alkali coolant 21, a superalloy heat pipe 22, an aircraft skin 23, and an alkali coolant injector 12.

The alkali metal coolant 21 is formed by components such as lithium, sodium, potassium and the like, and the melting point of the alloy is adjusted by adjusting the distribution ratio of the components, so that the temperature change region in the flight envelope of the aircraft is adapted.

The high-temperature alloy heat pipe 22 is positioned on the inner side of an aircraft skin 23, and is made of high-temperature resistant metal matrix composite materials such as nickel-based high-temperature alloy or rhenium-molybdenum high-temperature alloy, and the internal flow channel is designed specifically according to the thermal environment of the aircraft determined by the flight envelope.

The aircraft skin 23 is located on the outermost side of the aircraft and is made of ultra-high temperature ceramics and the like, and the surface of the air inlet channel is embedded with the alkali metal coolant injector 12.

The alkali metal coolant 21 mainly adopts components such as lithium, sodium, potassium and the like to form an alloy, and the proportion of each component is adjusted so as to adjust the melting point of the alloy, thereby adapting to the temperature change region in the flight envelope of the aircraft. The superalloy heat pipe 22 is made of a high temperature resistant metal matrix composite material such as a nickel-based superalloy or a rhenium-molybdenum superalloy, and the internal flow channel is designed according to the thermal environment of the aircraft determined by the flight envelope. The aircraft skin 23 is made of ultrahigh-temperature ceramics and other materials, and the surface of the air inlet channel is embedded with the alkali metal coolant injector 12. The alkali coolant injector 12 functions as an ion injection in the overall system to inject alkali seeds into the high velocity gas stream to enhance its ionization characteristics.

FIG. 3 is a schematic view of the structure of the alkali metal injector 12, which is composed of a composite laminated valve sheet 32 and a shape memory alloy valve sheet 33.

The composite material laminated valve plate 32 is positioned outside the injection device, is contacted with the incoming air, and has lower thermal expansion coefficient and better extension flexibility

The shape memory alloy valve plate 33 is positioned at the inner side of the injection device, is contacted with an incoming alkali metal coolant, and can generate larger restoring force under the heated condition.

The high temperature alkali metal alloy liquid flows through the surface of the memory alloy valve plate along the arrow direction, when the temperature rises to a certain degree, the shape memory alloy valve plate 33 generates large contraction pulling force, the composite material laminated valve plate 32 is dragged to open, the alkali metal alloy flows out along the open gap and is injected into the air inlet channel, as shown in figure 4.

The method can be used for energy management and control and structure active cooling of the hypersonic combined power aircraft.

Claims

1. Aerospace plane active cooling system based on magnetic current body energy bypass, including aircraft active cooling wave body (11) and aircraft active cooling lip (17), aircraft active cooling wave body (11) set up in the aircraft leading edge, and aircraft active cooling lip (17) set up in ramjet inlet leading edge, its characterized in that:

the aircraft active cooling wave rider (11) and the aircraft active cooling lip (17) respectively comprise a high-temperature alloy heat pipe (22) and an aircraft skin (23), the high-temperature alloy heat pipe (22) is located on the inner side of the aircraft skin (23), an internal flow channel of the high-temperature alloy heat pipe (22) corresponds to an aircraft thermal environment determined by a flight envelope, a liquid alkali metal coolant (21) is introduced into the internal flow channel of the high-temperature alloy heat pipe (22), and when the alkali metal coolant (21) flows in the internal flow channel of the high-temperature alloy heat pipe (22), structural heat is absorbed in the forced convection heat exchange process to actively cool the aircraft;

the aircraft active cooling wave carrier (11) further comprises an alkali metal coolant injector (12), the alkali metal coolant injector (12) is located below the aircraft active cooling wave carrier (11) and embedded in the surface of an air inlet channel on an aircraft skin (23), and the alkali metal coolant injector (12) injects part of alkali metal in the high-temperature alloy heat pipe (22) into air flow in the air inlet channel.

2. The aerospace vehicle active cooling system of claim 1, wherein: the aircraft active cooling lip (17) further comprises an alkali metal coolant injector (12), the alkali metal coolant injector (12) is located above the aircraft active cooling lip (17) and embedded on the surface of an air inlet channel on an aircraft skin (23), and the alkali metal coolant injector (12) injects part of alkali metal in the high-temperature alloy heat pipe (22) into air flow in the air inlet channel.

3. The aerospace aircraft active cooling system of claim 1 or 2, wherein: the aerospace plane active cooling system further comprises an annular magnetofluid power generation channel (13), the annular magnetofluid power generation channel (13) is located on the outer ring of the air inlet channel of the ramjet and is a Faraday type magnetofluid generator, the annular magnetofluid power generation channel is prepared by surrounding the air inlet channel of the ramjet by a metal coil, and generated electric energy is collected by an electromagnetic energy control system (15).

4. The aerospace vehicle active cooling system of claim 3, wherein: the aerospace plane active cooling system further comprises an annular electromagnetic acceleration channel (16), wherein the annular electromagnetic acceleration channel (16) is located on the outer ring of the ramjet nozzle, is formed by surrounding the ramjet nozzle with a metal coil, and is used for accelerating and vector controlling magnetofluid fuel gas.

5. The aerospace aircraft active cooling system of claim 1 or 2, wherein: the alkali metal coolant injector (12) consists of a composite material laminated valve plate (32) and a shape memory alloy valve plate (33), wherein the composite material laminated valve plate (32) is positioned outside the injection device and is contacted with incoming air; the shape memory alloy valve plate (33) is positioned on the inner side of the injection device and is in contact with an incoming alkali metal coolant (21), when the temperature rises, the shape memory alloy valve plate (33) drags the composite material laminated valve plate (32) to be opened, and the alkali metal coolant (21) flows out along the opened gap and is injected into the air inlet channel.

6. The aerospace vehicle active cooling system of claim 1, wherein: the alkali metal coolant (21) is made of an alloy material composed of lithium sodium potassium; the high-temperature alloy heat pipe (22) adopts nickel-based high-temperature alloy or rhenium-molybdenum high-temperature alloy; the aircraft skin (23) is made of ultra-high temperature ceramic materials.