CN112829951A

CN112829951A - Zero-emission aviation aircraft navigation process and power device thereof

Info

Publication number: CN112829951A
Application number: CN201910165742.2A
Authority: CN
Inventors: 易元明
Original assignee: Wu Huanxun
Current assignee: Wu Huanxun
Priority date: 2019-03-01
Filing date: 2019-03-01
Publication date: 2021-05-25

Abstract

The invention relates to a zero-emission aviation aircraft navigation process method and a power device thereof. The method is technically characterized in that a variable-frequency electric winch is adopted to accelerate and pull an airplane to take off on an airport runway by using a cable, and an airborne power device adopts airborne and airborne liquid air to absorb heat and vaporize from compressed air generated by the aircraft to form high-pressure air to be sprayed out to the aircraft on the basis of generating the highest ground speed, so that the existing airplane is replaced by a turbine engine to burn oil and spray air to generate recoil force to drive the airplane to realize air flight overcoming resistance; therefore, the aviation aircraft can sail with zero pollution, zero emission, high efficiency and low cost.

Description

Zero-emission aviation aircraft navigation process and power device thereof

Technical Field

The invention relates to an aviation aircraft navigation process method and a power device thereof, in particular to a zero-emission aviation aircraft navigation process method and a power device thereof, which can obviously improve the efficiency and the effective load of aviation engineering machinery and greatly reduce the engineering cost.

Background

The current aviation craft method and its power device, according to F.T ═ m.V momentum principle, through adopting the turbine engine fuel oil to drive, jet out the gas to the aircraft after the machine and produce the recoil force and promote the aircraft to overcome the friction between ground and the tire and fly to the air on the runway of the airport; in the navigation process, the quantity of aviation fuel consumed is huge particularly in the takeoff and acceleration stages, and meanwhile, the aviation fuel becomes invalid load in the navigation of the airplane; the waste gas generated by the turbine engine carried by the existing airplane is completely discharged to the sky, and becomes the most main industrial pollution source in the sky; therefore, the cost of the existing aviation industry is high, and the pollution is serious.

Disclosure of Invention

The invention aims to provide a novel zero-emission aviation aircraft navigation process method and a power device thereof, which are used for remarkably improving the mechanical efficiency of aviation engineering, greatly reducing the navigation cost of the aviation engineering, improving the effective load of an aviation aircraft by multiple times, completely adopting clean energy to drive in various navigation working conditions of short range, middle range and long range, realizing zero emission and fundamentally eliminating the pollution of tail gas of the aircraft to the natural environment.

The technical scheme of the invention is as follows:

the zero-emission aviation aircraft navigation process method is characterized by that according to the physical principle of that "the physical condition for determining object movement speed is mechanical work, kinetic energy and non-momentum", it directly utilizes the mechanical work formed from force and force action distance to pull aircraft to lift off and take off, and can raise the above-ground speed of aircraft to maximum extent, on the basis of said physical condition, the aircraft-mounted power device can make the machine-mounted and machine-produced liquid air be absorbed by heat and vaporized from the machine-produced compressed air, and become high-pressure air and spray out toward the aircraft, and can produce recoil thrust to push aircraft to overcome resistance to fly in the air.

The method is that the prior aviation aircraft utilizes the fuel oil of an airborne turbine engine to jet outwards to drive the aircraft to advance at high speed on an airport runway by overcoming the friction force between an airborne tire and the ground, and the aircraft wings generate lift force to realize take-off; the improvement comprises that a steel rail is arranged on an airport runway, a flat car is arranged on the steel rail, an airplane is arranged on the flat car, a variable frequency electric winch arranged below the airport runway uses a cable to pull the flat car and the airplane to advance on the steel rail at a high speed, after the airplane reaches a set maximum speed on the flat car, the lift force of the wings of the airplane is adjusted to reach the maximum value, and meanwhile, an ejector and a buckling device arranged between the airplane and the flat car are opened, so that the airplane generates the flying speed off the ground as high as possible.

Meanwhile, under the condition of not influencing the visual field of an aircraft driver, a metal housing is arranged at the front end of an aircraft body to block high-heat thermal barrier air at the front end of the aircraft, and a thermal evaporation metal pipe network is arranged at the back of the metal housing; applying high pressure to liquid air stored in an airplane cabin by using a pneumatic working medium pump, pumping the liquid air into a thermal evaporation metal pipe network on the back of a metal housing, enabling the liquid air in the thermal evaporation metal pipe network to absorb heat from thermal barrier air at the front end of the airplane through the metal housing and vaporize the heat into high-pressure air, and finally spraying the high-pressure air to the rear of the airplane from a high-pressure air spray pipe arranged at the edge of the metal housing to form airplane advancing thrust; during landing, the high-pressure air jet pipe jets air towards the traveling direction of the airplane, so that resistance for decelerating and stopping the airplane is formed.

In the working condition that the airplane flies in a short voyage, the airplane does not carry fuel and is not provided with a turbine engine, and after the maximum ground-off voyage speed is generated to the maximum extent in the process of pulling a cable of the variable-frequency electric winch and ejecting the catapult, the airplane glides and flies after penetrating through a sky air dense layer; when the aircraft needs to advance in the air in an accelerating way, liquid air carried by the aircraft absorbs heat from thermal barrier air at the front end of an aircraft body through a thermal evaporation metal pipe network and is vaporized to form high-pressure air, and finally, the high-pressure air is sprayed to the aircraft from a high-pressure air spray pipe arranged at the edge of a metal housing at the front end of the aircraft to push the aircraft to sail in the air against resistance.

In the working condition that the airplane flies in the middle flight range, fuel oil is not carried, and a turbine engine is not arranged; in order to multiply enlarge the flight range of the airplane under the premise of a set amount of liquid air carried by the airplane, on the basis of the short-range power device, a turbo air compressor and a high-pressure air spray pipe are arranged at the lower part of the wing of the existing airplane provided with a turbine engine, and meanwhile, an opposite convection heat exchanger and a pneumatic working medium pump are arranged in the wing; the turbo air compressor sucks a large amount of natural air from the advancing direction of the airplane, the natural air is pressurized by the turbine blades to form compressed air, and the compressed air is input into the opposite convection heat exchanger through the metal pipe; the opposite convection heat exchanger is composed of a high-pressure inner pipe and a medium-pressure outer pipe in a composite mode, compressed air is input into the medium-pressure outer pipe at the middle and hot ends of the opposite convection heat exchanger, a pneumatic working medium pump applies high pressure to liquid air stored in the machine cabin and pumps the liquid air into the high-pressure inner pipe at the cold end of the opposite convection heat exchange pipe, and the compressed air in the medium-pressure outer pipe and the liquid air in the high-pressure inner pipe perform opposite convection heat exchange; the compressed air is condensed into low-temperature liquid air in the cold end outer pipe of the opposite convection heat exchanger, so that the liquid air is continuously produced in the air; after high pressure is applied to liquid air by a pneumatic working medium pump, the liquid air is pumped into a cold end high-pressure inner pipe in the opposite convection heat exchanger and then exchanges heat with compressed air in a medium-pressure outer pipe in the opposite convection heat exchanger to finally become high-pressure air; inputting a small amount of the high-pressure air into a turbine expansion machine at the rear part of the turbo air compressor to do work, enabling the high-pressure air to become power for driving the turbo air compressor to continuously operate, and discharging clean tail gas to a natural space; the rest high-pressure air is sprayed out from the high-pressure air spray pipe arranged below the wing to the rear direction of the airplane and becomes the advancing power for driving the airplane to fly in the air against the resistance; liquid air formed by condensing and liquefying compressed air through the opposite convection heat exchanger is divided into a part and is injected into a thermal evaporation metal pipe network in a metal cover at the front end of the engine body after high pressure is applied to the part, so that the part absorbs heat and is vaporized, and then the part is sprayed out towards the engine from a high-pressure air spray pipe arranged at the edge of the metal cover; therefore, airborne liquid air is enabled to provide cold energy supplement required by heat exchange temperature difference for maintaining set low temperature at the cold end of the opposite convection heat exchanger.

In the working condition that the airplane carries out long-range flight, fuel oil is not carried, a turbine engine is not arranged, on the basis of arranging the middle-range power device, a storage battery, an electric heater, a throttle valve and a low-temperature high-pressure air throttling chamber are additionally arranged in the wing, and a generator is additionally arranged below the wing; before the airplane takes off, a ground power supply is used for supplying power to the storage battery; in the air gliding stage of the airplane, starting a generator which coaxially operates with the turbo air compressor to generate electricity and supplement the electric power of a storage battery, and occasionally utilizing a low-temperature high-pressure air throttling chamber to produce and store liquid air in the air gliding stage of the airplane; when the airplane needs strong air acceleration, the input amount of liquid air in a high-pressure inner pipe at the cold end of the opposite convection heat exchanger is increased, high-pressure air flowing out of a high-pressure pipe at the hot end of the opposite convection heat exchanger is introduced into an electric heater through a metal pipe for heating, a storage battery supplies power to the electric heater, the high-pressure air realizes equal-pressure volume-increasing expansion and heat absorption in the electric heater to become high-temperature high-pressure air, and finally the high-pressure air is sprayed out to the rear direction of the airplane from a high-pressure air spray pipe arranged below wings, so that the airplane is driven to accelerate.

The steel rails are arranged on the airport runway, and the flat car is placed on the steel rails, namely steel wheels below the flat car can roll on the steel rails to move, or a magnetic suspension device is arranged between the flat car and the steel rails, so that the flat car can move without friction under the working condition of suspension on the steel rails.

The utility model provides a zero release aviation aircraft power device, it includes aviation aircraft organism, airport lift runway, still includes frequency conversion electric winch, hawser, the rail, the flatbed, organism and flatbed withhold device, the catapult, organism front end metal casing, heating power evaporation metal pipe network, turbo air compressor machine, liquid air storage storehouse, convection current heat exchanger in opposite directions, low temperature high-pressure air throttle chamber, choke valve, pneumatic working medium pump, high-pressure air spray tube, the generator, the battery, electric heater and a plurality of metal connecting pipe.

The frequency conversion electric winch is arranged in a basement at an airport runway terminal, the flat car is provided with the ejector, the airport take-off runway is provided with a steel rail, the steel rail and the ground of the airport runway are fastened and installed, the flat car is placed on the steel rail, the flat car and the frequency conversion electric winch are connected through a cable, the aviation aircraft is placed on the flat car, the electric buckling and pressing device is arranged between the flat car and an aircraft body, the rear end of the flat car is provided with the ejector, and the ejector abuts against the rear end of the aircraft body.

The front end of an aircraft body is provided with a metal housing for resisting heat expansion air, the back of the metal housing is provided with a thermal evaporation metal pipe network, and the left and right positions of the edge of the metal housing are symmetrically provided with high-pressure air spray pipes; the cold end liquid inlet pipe orifice in the thermal power evaporation metal pipe network is connected with a pneumatic working medium pump arranged in the machine cabin through a metal pipe, and the hot end air outlet pipe orifice is connected with a high-pressure air spray pipe.

The inner cabin of the airplane body is provided with a liquid air storage cabin and a pneumatic working medium pump; in the short voyage working condition, the liquid air storage bin and the pneumatic working medium pump are connected with the thermal evaporation metal pipe network through metal pipes; in the middle-range working condition, the heat exchanger is also connected with the opposite convection heat exchanger through a metal pipe; in the long-range working condition, the liquid air storage bin is also connected with the low-temperature high-pressure air throttling chamber through the metal pipe.

On the basis of the arrangement of the airborne power device, the power device of the medium range aviation aircraft is additionally provided with the following components: turbine air compressors are symmetrically arranged on the left and right of the position where a turbine engine is arranged on the lower portion of a wing of an existing airplane, the front portion of each turbine air compressor is provided with an air compressor, the rear portion of each turbine air compressor is provided with a turbine expander, a compressed air chamber in each air compressor is connected with an outer pipe at the hot end of an opposite convection heat exchanger through a metal pipe, and a high-pressure air chamber of each turbine expander is connected with a high-pressure inner pipe at the hot; the wing is also internally provided with an opposite convection heat exchanger and a pneumatic working medium pump, and the pneumatic working medium pump is respectively connected with a high-pressure inner pipe and a medium-pressure outer pipe at the cold end of the opposite convection heat exchanger through metal pipes; the opposite convection heat exchanger is composed of composite pipes, the inner pipe is a high-pressure pipe, and the outer pipe is a medium-pressure pipe; and meanwhile, a high-pressure air spray pipe is arranged at the bottom of the wing and is connected with a hot-end high-pressure inner pipe of the opposite convection heat exchanger through a metal pipe.

The power device of the long-range aviation aircraft is additionally provided with the following components on the basis of the power device of the long-range aviation aircraft: a generator is arranged at the lower part of the wing, and the generator and the turbine air compressor run coaxially and are driven by the turbine expander; a storage battery, an electric heater and a low-temperature high-pressure air throttling chamber are additionally arranged in the wing; a throttle valve is arranged above the low-temperature high-pressure air throttling chamber, the throttle valve is connected with a high-pressure inner pipe in the middle of the opposite convection heat exchanger through a metal pipe, and the lower part of the low-temperature high-pressure air throttling chamber is connected with a liquid air storage bin in the machine bin through the metal pipe.

In the present invention, the ejector may be a powerful spring ejector, an electromagnetic ejector, or a compressed air ejector.

In the invention, the turbo air compressor is formed by coaxially assembling an air compressor consisting of turbine blades and a turbo expander, and the air compressor at the front part of the turbo air compressor is responsible for compressing air at normal temperature and normal pressure into medium-pressure air and low-pressure air with set pressure; the turbine expander at the rear part of the air compressor provides mechanical power for the front-end air compressor and the coaxially operated generator under the drive of the high-pressure air turbine; compressed air generated by an air compressor at the front end part is input into a hot end outer pipe of the opposite convection heat exchanger arranged in the wing through a metal pipeline; the high pressure air required by the rear-end turboexpander is provided by a hot-end high pressure pipe in the counter-flow heat exchanger, and the clean tail gas is discharged to the natural space.

In the present invention, the placing of the flatbed on the rails may be supported by steel wheels of the flatbed and may be performed on the rails, or the flatbed may be suspended on the rails by a magnetic levitation device provided between the flatbed and the rails.

In the invention, the pneumatic working medium pump is a working medium pump which takes high-pressure air generated in a front-end thermal evaporation metal pipe network and a high-pressure pipe in an opposite convection heat exchanger as driving power.

Drawings

The present invention will be described in detail below with reference to the accompanying drawings.

Fig. 1 is a schematic structural diagram of a zero-emission airborne aircraft lift-off device.

Fig. 2 is a schematic structural diagram of a short-range zero-emission aircraft power plant.

Fig. 3 is a schematic structural diagram of additional components of the medium-range zero-emission aircraft power plant.

Fig. 4 is a schematic structural diagram of an additional component of the long-range zero-emission aircraft power plant.

Detailed Description

Referring to the attached

drawings

1, 2, 3 and 4, the zero-emission aviation aircraft navigation process method and the device thereof directly utilize the mechanical power formed by the action distance of force and force to pull the aircraft to lift off and take off according to the physical principle that the physical condition for determining the motion speed of an object is mechanical power, kinetic energy and non-momentum, and then utilize the onboard power device to absorb heat and vaporize onboard and onboard liquid air from the generated compressed air to become high-pressure air to be sprayed out to the aircraft and generate recoil impulse force to push the aircraft to overcome resistance to fly in the air on the basis of improving the ground-off speed of the aviation aircraft to the maximum extent, thereby realizing the high-efficiency zero-emission and navigation of the aviation aircraft.

The zero-emission aviation aircraft navigation process method is characterized by comprising the following steps: according to the physical principle that the physical condition for determining the movement speed of an object is mechanical work, kinetic energy and momentum, the mechanical work formed by the action distance of force and force is directly utilized to pull the airplane to lift off and take off, and on the basis of improving the ground-off speed of the airplane to the maximum extent, the onboard power device is utilized to absorb heat and vaporize onboard and onboard liquid air from the generated compressed air to become high-pressure air which is sprayed out to the airplane and generate recoil thrust to push the airplane to fly against resistance in the air; the method comprises the steps of arranging steel rails on the ground of an airport runway, placing a flat car on the steel rails, placing an airplane on the flat car, and using a variable-frequency electric winch to pull an airplane body placed on the flat car to advance at a high speed by using a cable at an accelerated speed; an electric opening buckling device is arranged between the airplane body and the flat car to ensure that the airplane obtains the set maximum liftoff speed before liftoff take-off; the lift force device of the airplane wing is timely adjusted to be minimum before the airplane is pulled to move, the lift force of the airplane wing is adjusted to be maximum at the moment before the airplane is lifted off and takes off, the operation of the variable-frequency electric winch is stopped, meanwhile, the electric buckling device arranged between the airplane body and the flat car is started, the ejector arranged at the rear end of the flat car is started, the elastic potential energy stored by the ejector is instantly released between the flat car and the airplane body, and the ejection force of the ejector can efficiently push the airplane body to fly away from the ground while preventing the flat car from continuously moving at a high speed; under the condition of not influencing the visual field of an aircraft driver, a metal housing for blocking thermal barrier air is arranged at the front end of an aircraft body, liquid air in a metal pipe network is vaporized by heat generated by the thermal barrier air on the metal housing to form high-pressure air, the high-pressure air is sprayed out from a high-pressure air spray pipe in the rear direction of the aircraft to push the aircraft to fly against resistance in the air, and meanwhile, the air resistance of the aircraft in high-speed running is effectively reduced, so that a power device under the short-range working condition is formed. In the power device of the medium-range aircraft, on the basis of keeping the short-range power device, a turbo air compressor, an opposite convection heat exchanger, a pneumatic working medium pump and a high-pressure air spray pipe are additionally arranged, so that compressed air is produced in large quantity, and high-temperature compressed air and liquid air are condensed and liquefied in the opposite convection heat exchanger, thereby realizing the continuous production of liquid air in the air; and applying high pressure by a pneumatic working medium pump, pumping the liquid air into a cold-end high-pressure pipe in the opposite convection heat exchanger again, exchanging heat with compressed air in a medium-pressure outer pipe to form continuous high-pressure air, and finally spraying the high-pressure air to the aircraft through a high-pressure air spray pipe arranged below the wing to drive the aircraft to fly in the air to overcome resistance, thereby forming the medium-range aircraft power device. In the power device of the long-range airplane, on the basis of the power device of the middle-range airplane, a generator, a storage battery and an electric heater are additionally arranged, the power is supplied to the storage battery on the ground before the airplane takes off, and the generator which coaxially operates with a turbo air compressor is started to generate power in the air gliding stage so as to supplement the power to the storage battery; meanwhile, a low-temperature high-pressure air throttling chamber is additionally arranged, and in the air gliding stage of the airplane, low-temperature high-pressure air in a high-pressure inner pipe of the opposite convection heat exchanger is input into the low-temperature high-pressure air throttling chamber to be automatically condensed and liquefied in the large-pressure-difference throttling process and then input into a liquid air storage bin for storage and standby; when the airplane needs to be accelerated strongly in the air, the input quantity of liquid air in a high-pressure inner pipe at the cold end of the opposite convection heat exchanger is increased, the high-pressure air flowing out of a high-pressure pipe at the hot end of the opposite convection heat exchanger is introduced into an electric heater through a metal pipe for heating, a storage battery supplies power to the electric heater, the high-pressure air realizes equal-pressure capacity expansion and heat absorption in the electric heater to become high-temperature high-pressure air, and finally the high-pressure air is sprayed out of the airplane through a high-pressure air spray pipe to become strong driving power for accelerating the long-range; the air flight range can become infinite range because the onboard low-temperature high-pressure air throttling chamber is used for producing liquid air which can be stored for later use during the gliding of the airplane.

In the various working conditions, the high-pressure air spray pipe can be changed into a mode of spraying air to the advancing direction of the airplane in the landing process of the airplane on the runway of the airport, so that the deceleration resistance is generated. When the airplane needs to turn to navigate in the air, the air injection amount of the high-pressure air injection pipe arranged in the left and right directions of the edge of the front-end metal cover casing is adjusted to enable one side of the air injection amount to be large and the other side of the air injection amount to be small, so that the airplane turns to navigate.

The zero-emission aviation aircraft power device is implemented by the method.

As shown in fig. 1, a zero-emission aircraft lift-off device includes: the device comprises a variable-frequency electric winch 1, a cable 2, a steel rail 3, an airport runway 4, a flat car 5, an ejector 6, an airplane body 7, an airplane wing lift regulator 8 and an electric opening buckling and pressing device 9 arranged between the airplane body and the flat car.

As shown in fig. 2, a short-range zero-emission aircraft power plant comprises: the aircraft comprises an aircraft body 7, a metal housing 12 for resisting thermal barrier air at the front end of the aircraft body, a thermal evaporation metal pipe network 13, a liquid air storage bin 14, a pneumatic working medium pump 15, a high-pressure air spray pipe 16 and a metal connecting pipe 10.

As shown in fig. 2 and 3, a medium-range zero-emission aircraft power plant includes: a turbo air compressor 17, a counter-flow heat exchanger 18, a high-pressure air spray pipe 16 and a pneumatic working medium pump 15; meanwhile, the aircraft comprises an aircraft body 7 shown in figure 2, a heat barrier air resisting metal housing 12 at the front end of the aircraft body, a thermal evaporation metal pipe network 13, a liquid air storage bin 14, a pneumatic working medium pump 15, a high-pressure air spray pipe 16 and a metal connecting pipe 10.

As shown in fig. 2 and 4, a long-range zero-emission aircraft power plant includes: the system comprises a pneumatic working medium pump 15, a high-pressure air spray pipe 16, a turbo air compressor 17, a counter-flow heat exchanger 18, a storage battery 19, a generator 20, an electric heater 21, a low-temperature high-pressure air throttling chamber 22 and a throttling valve 23; meanwhile, the aircraft comprises an aircraft body 7 shown in figure 2, a heat barrier air resisting metal housing 12 at the front end of the aircraft body, a thermal evaporation metal pipe network 13, a liquid air storage bin 14, a pneumatic working medium pump 15, a high-pressure air spray pipe 16 and a metal connecting pipe 10.

Referring to the attached figure 1, the use and operation procedures of the zero-emission aviation aircraft lift-off device are as follows:

1. as shown in the figure, an airplane body 7 is placed above the flat car 5, an ejector 6 arranged at the rear end of the flat car 5 is used for storing energy, and an electric opening buckling and pressing device 9 is arranged between the flat car 5 and the airplane body 7.

2. The lift regulating device 8 on the aircraft wing is adjusted to the lift minimum position.

3. The flat car 5 is pushed to the starting point position of the steel rail 3 on the airport take-off runway 4, and the frequency conversion electric winch 1 is connected with the flat car 5 by the cable 2.

4. And starting the variable-frequency electric winch 1, and using the cable 2 to pull the flat car 5 at an accelerated speed to enable the flat car 5 and the airplane body 7 to advance on the steel rail 3 at an accelerated speed.

5. And when the traveling speeds of the flat car 5 and the airplane body 7 reach a set value, stopping the electric drive of the variable-frequency electric winch.

6. Adjusting the wing lift regulator 8 of the airplane to adjust the wing lift to the maximum value; opening an electric withholding device 9 arranged between the flat car 5 and the airplane body 7; starting an ejector 6 at the rear end of the flat car 5, wherein the ejector 6 pushes the flat car 5 in the reverse direction to rapidly decelerate, and simultaneously pushes the airplane body 7 in the forward direction to obtain huge propulsion kinetic energy; the aircraft flies away from the flat car 5 under the effect of the lift of the wings to fly to the sky at the set lift speed.

Referring to fig. 2, the application and operation procedure of the short-range zero-emission aircraft power plant according to the invention is as follows:

1. before the airplane body 7 is pulled by the mooring rope 2 on the variable-frequency electric winch 1, the pneumatic working medium pump 15 is started, liquid air in the liquid air storage bin 14 is applied with high pressure and pumped into the thermal evaporation metal pipe network 13 at the front end of the airplane body to block the thermal barrier air metal housing 12, and the liquid air absorbs heat from the normal-temperature environment and is vaporized into high-pressure air.

2. In the process that the aircraft body 7 is pulled by the cable 2 on the variable-frequency electric winch 1 with the flat car 5 in an accelerating way, air at the front end of the aircraft body is quickly extruded, the temperature of the air is quickly increased, and an air thermal barrier is formed; the heat is absorbed by a heat evaporation metal pipe network 13 arranged at the back of the metal casing 12, and low-temperature high-pressure air in the pipe is quickly absorbed by heat and vaporized into high-temperature high-pressure air.

3. After the airplane body 7 is lifted off the ground, the high-pressure air spray pipe 16 arranged at the edge of the metal casing 12 at the front end of the airplane body is opened to spray air to the back of the airplane body, and the recoil force of the high-pressure air spray pipe pushes the airplane body to sail efficiently on the basis that the airplane body has the maximum speed of the airplane to the ground.

4. In the process of high-speed navigation of the airplane body 7, the high-pressure air spray pipes 16 are intermittently opened, and the propelling kinetic energy efficiently generated by the high-pressure air spray pipes is utilized to overcome the flight resistance, so that the airplane is ensured to continuously fly.

5. When the airplane needs to be decelerated for emergency flight, especially during landing and gliding on a runway, the high-pressure air nozzle 16 is adjusted to spray air to the advancing direction of the airplane, and the recoil force of the high-pressure air nozzle is used for forcing the airplane to be decelerated and stopped rapidly.

6. When the airplane needs to turn to navigate in the navigation process, the jet volume of the high-pressure air jet pipe 16 arranged in the left and right directions of the edge of the metal cover shell at the front end of the airplane is adjusted to enable one side of the jet volume to be large and the other side of the jet volume to be small, so that the airplane can turn to navigate.

Referring to fig. 2 and 3, the medium-range zero-emission aircraft power plant according to the present invention is formed by combining the short-range zero-emission aircraft power plant shown in fig. 2 and the added part of the medium-range aircraft power plant shown in fig. 3, and the operating procedures are as follows:

1. as shown in the attached figure 2, before a steel rail 3 laid on an airport runway 4 by an airplane body 7 is pulled by a cable 2 on a variable frequency electric winch 1, a pneumatic working medium pump 15 is started to apply high pressure to liquid air in a liquid air storage bin 14, the liquid air is pumped into a thermal evaporation metal pipe network 13 arranged at the front end of the airplane body and behind a metal housing 12 resisting thermal barrier air, and meanwhile, high-pressure inner pipes arranged at cold ends of opposite convection heat exchangers 18 inside left and right wings of the airplane are pumped to absorb heat from a normal temperature environment and vaporize the heat into normal temperature high-pressure air.

2. As shown in fig. 3, after the aircraft body 7 takes off from the ground, the high-pressure air in the hot-end high-pressure pipe of the opposite-direction heat exchanger 18 shown in fig. 3 is input into the turbo expander arranged at the rear part of the turbo air compressor 17 below the wing, the turbo expander is driven to operate, the air compressor is coaxially driven to rotate at high speed, and the air in the natural space continuously enters the turbo air compressor 17 from the front of the aircraft and is compressed into high-temperature compressed air.

3. As shown in fig. 3, the high-heat compressed air generated by the turbo air compressor 17 is input into the medium-pressure outer tube of the counter-flow heat exchanger 18 arranged in the aircraft wing through the metal tube, the high-heat compressed air and the low-temperature high-pressure liquid air in the inner tube perform counter-flow heat exchange, and finally the outer tube at the cold end is cooled, condensed and liquefied.

4. As shown in fig. 3, the pneumatic working medium pump 15 disposed in the wing is started to apply high pressure to the medium-pressure liquid air in the cold-end medium-pressure outer tube in the opposite convection heat exchanger 18, so that the medium-pressure liquid air reenters the cold-end high-pressure inner tube in the opposite convection heat exchanger 18, and then carries out opposite convection heat exchange with the high-heat compressed air entering from the hot-end medium-pressure outer tube, and is re-vaporized into high-pressure air.

5. As shown in fig. 3, a small amount of high-pressure air generated by the high-pressure inner pipe at the hot end of the counter-flow heat exchanger 18 is input into the rear turbo expander in the turbo air compressor 17 to coaxially drive the turbo air compressor 17 to continuously work, and the clean exhaust gas is discharged to the rear of the machine.

6. As shown in fig. 3, the high-pressure air nozzles 16 arranged below the left and right wings of the airplane are opened, so that the high-pressure air in the high-pressure pipes at the hot end of the opposite convection heat exchanger 18 is sprayed out to the back of the airplane in a large amount through the high-pressure air nozzles 16, and the airplane is pushed to sail by using the recoil thrust of the high-pressure air.

7. As shown in fig. 2, the pneumatic working medium pump 15 arranged in the cabin of the aircraft body 7 is intermittently started, and liquid air in the liquid air storage cabin 14 is intermittently applied with high pressure and pumped into the high-pressure pipe arranged at the cold end of the opposite convection heat exchange pipe 18 in the aircraft wing in a small amount, so that low-temperature cold energy required for maintaining the heat exchange temperature difference in the opposite convection heat exchanger 18 is supplemented, and the cold end of the opposite convection heat exchanger 18 is ensured to continuously maintain the set low-temperature.

8. As shown in fig. 2, a small amount of liquid air in the high-pressure inner tube at the cold end of the counter-flow heat exchanger 18 is input into the thermal evaporation metal pipe network 13 arranged at the front end of the aircraft body 7 behind the metal casing 12 resisting the thermal barrier air, so that the liquid air is absorbed by the thermal barrier air and vaporized into high-pressure air, and finally the high-pressure air is sprayed out from the rear of the aircraft through the high-pressure air spray pipe 16 to push the aircraft to move, thereby reducing the consumption of the liquid air in the liquid air storage bin 14.

9. When the airplane needs to be decelerated emergently and glides on the landing runway of the airport, the high-pressure air spray pipes 16 arranged below the wings and at the edge of the metal casing 12 are changed into spraying air in the advancing direction of the airplane, and the deceleration is realized by using the positive impact force of the high-pressure air spray pipes.

10. When the airplane needs to turn to navigate in the navigation process, the jet volume of the high-pressure air jet pipe 16 arranged in the left and right directions of the edge of the metal cover shell at the front end of the airplane is adjusted to enable one side of the jet volume to be large and the other side of the jet volume to be small, so that the airplane can turn to navigate.

Referring to the attached

drawings

2 and 4, the long-range zero-emission aircraft power device is formed by combining a short-range zero-emission aircraft power device shown in the attached drawing 2 and an additional component of the long-range zero-emission aircraft power device shown in the attached drawing 4, and the using and operating procedures are as follows:

1. as shown in attached figures 2 and 4, before an airplane body 7 is pulled on a steel rail 3 by a mooring rope 2 on a variable-frequency electric winch 1, a pneumatic working medium pump 15 is started to apply high pressure to liquid air in a liquid air storage bin 14, the liquid air is pumped into a thermal evaporation metal pipe network 13 arranged at the back of a metal housing 12 which is arranged at the front end of the airplane body and resists thermal barrier air, and meanwhile, opposite convection heat exchangers 18 arranged inside left and right wings of the airplane are pumped to absorb heat from a normal temperature environment and vaporize the heat into normal temperature high-pressure air; while charging the on-board battery 19 from a ground power supply to keep its charge sufficient.

2. As shown in fig. 4, after the aircraft body 7 takes off from the ground, the high-pressure air in the hot-end high-pressure pipe of the opposite convection heat exchange pipe 18 is input into the turbo expander arranged at the rear part of the turbo air compressor 17 below the wing, the turbo expander is driven to operate, the air compressor is coaxially driven to rotate at high speed, and the air in the natural space continuously enters the turbo air compressor 17 from the front of the aircraft and is compressed into high-temperature compressed air.

3. As shown in fig. 4, the high-heat compressed air generated by the turbo air compressor 17 is input into the hot-end medium-pressure outer tube of the convection heat exchanger 18 arranged in the aircraft wing, and the high-heat compressed air and the low-temperature high-pressure liquid air in the high-pressure inner tube perform the convection heat exchange in opposite directions, and are finally condensed and liquefied in the cold-end outer tube.

4. As shown in fig. 4, the pneumatic working medium pump 15 disposed in the wing is started to apply high pressure to the medium-pressure liquid air in the cold-end medium-pressure outer tube in the opposite convection heat exchanger 18, so that the medium-pressure liquid air reenters the high-pressure inner tube at the cold end in the opposite convection heat exchanger 18, and then carries out opposite convection heat exchange with the high-heat compressed air entering from the hot end thereof, and the high-pressure liquid air is re-absorbed and vaporized into high-pressure air.

5. As shown in fig. 4, a small amount of high-pressure air generated by the high-pressure inner pipe at the hot end of the counter-flow heat exchanger 18 is input into the rear turbo expander in the turbo air compressor 17 to coaxially drive the turbo air compressor 17 to continuously work, and the clean exhaust gas is discharged to the rear of the machine.

6. As shown in fig. 2, the pneumatic working medium pump 15 disposed in the cabin of the aircraft body 7 is intermittently started to apply high pressure to the liquid air in the liquid air storage cabin 14 and pump the liquid air into the high-pressure pipe disposed at the cold end of the opposite convection heat exchange pipe 18 in the aircraft wing, so as to supplement the low-temperature cold energy required for maintaining the heat exchange temperature difference between the inner pipe and the outer pipe of the opposite convection heat exchanger 18, thereby ensuring that the cold end of the opposite convection heat exchanger 18 continuously maintains the set low-temperature.

7. As shown in fig. 2 and 4, a small amount of liquid air in the high-pressure inner pipe of the counter-flow heat exchanger 18 is input into a thermal evaporation metal pipe network 13 arranged at the front end of the aircraft body 7 and behind the metal casing 12 resisting thermal barrier air, so that the liquid air is vaporized by absorbing heat from the thermal barrier air, and finally the liquid air is sprayed out of the aircraft by a high-pressure air spray pipe 16 arranged at the edge of the metal casing to push the aircraft to move, thereby reducing the consumption of the liquid air in the liquid air storage bin 14.

8. As shown in fig. 4, in the air gliding flight phase of the airplane, the air injection of the high-pressure air nozzle 16 arranged below the wing is stopped; the high-pressure air generated by the hot end high-pressure pipe of the counter-flow heat exchanger 18 is all input into the turbo expander at the rear part of the turbo air compressor 17 to operate and work, the generator 20 is coaxially driven to generate electricity, and the electricity is input into the storage battery 19 to be stored.

9. As shown in fig. 4, in the air gliding flight phase of the airplane, the high-pressure air nozzle 16 is stopped to inject air, and the generator 20 is stopped to generate electricity, so that the low-temperature high-pressure air generated in the high-pressure pipe in the middle of the counter-flow heat exchanger 18 is input into the low-temperature high-pressure air throttling chamber 22 through the throttling valve 23, and the throttling and the automatic condensation liquefaction with large pressure difference are realized.

10. The liquid air formed in the low-temperature high-pressure air throttling chamber 22 is led into the liquid air storage bin 14 in the machine bin to be stored for standby.

11. When the airplane needs strong acceleration, stopping the power generation working condition of the generator 20 and the working condition of producing liquid air by the low-temperature high-pressure air throttling chamber 22; and starting the pneumatic working medium pump 15 in the cabin, and simultaneously starting the pneumatic working medium pump 15 in the wing, so as to increase the pumping amount of liquid air in the high-pressure inner pipe at the cold end of the opposite convection heat exchanger 18.

12. In the case of an aircraft requiring powerful air acceleration, the high-pressure air in the hot-side high-pressure pipe of the counter-flow heat exchanger 18 shown in fig. 4 is introduced into the electric heater 21 through the metal pipe, and the electric power in the battery 19 is supplied to the electric heater 21.

13. As shown in FIG. 4, the high-temperature and high-pressure air which absorbs heat in the electric heater 21 and rapidly realizes isobaric compatibilization is input into the high-temperature and high-pressure air nozzle 16 arranged below the wing and is sprayed out towards the rear direction of the airplane, so that the airplane is strongly pushed to accelerate in the air.

14. Under the working condition that the airplane needs emergency deceleration and emergency landing, the high-pressure air spray pipes 16 arranged below the wings and at the edge of the metal casing 12 at the front end of the airplane spray high-pressure air towards the advancing direction of the airplane, and the airplane is decelerated and stopped by utilizing the positive impact force of the high-pressure air spray pipes.

15. When the airplane needs to turn to navigate in the navigation process, the air injection amount of the high-pressure air injection pipe 16 arranged in the left and right directions of the edge of the front-end metal housing 12 is adjusted, so that one side of the air injection amount is large, and the other side of the air injection amount is small, and the airplane turns to navigate.

The invention adopts a method of accelerating pulling and launching by using a cable through a variable frequency electric winch on a runway steel rail of an airport to realize the lift-off and take-off of an airplane, and simultaneously, on the basis that the airplane has the highest ground-off speed as much as possible, a power device arranged on the airplane adopts onboard and onboard liquid air to absorb heat from the produced compressed air and vaporize into high-pressure air to be sprayed out to the airplane, so that recoil force is generated to push the airplane to fly in the air against resistance; meanwhile, a metal housing and a thermal evaporation metal pipe network are arranged at the front end of the machine body, and airborne liquid air is utilized to absorb heat from the metal housing and vaporize into high-pressure air; in the middle-range working condition, a turbo air compressor is adopted to produce compressed air, the compressed air is condensed and liquefied through a counter-flow heat exchanger, liquid air is continuously produced in the air, a pneumatic working medium pump is used for applying pressure, and the liquid air and the compressed air are subjected to counter-flow heat exchange to form high-pressure air again; in the long-range working condition, during the gliding period of the airplane, liquid air is produced and stored by utilizing the low-temperature high-pressure air throttling chamber; in addition, a generator, a storage battery and an electric heater are arranged, and high-pressure air generated by the opposite convection heat exchanger is heated into high-temperature high-pressure air by the electric heater occasionally; the high-pressure air and the high-temperature high-pressure air are respectively utilized to generate recoil thrust to drive the airplane to fly in the air against resistance.

The invention has unexpected technical effect, and the technical effect is to create an aviation industry era with zero pollution, zero emission and extremely low operation cost.

The invention has wide application, and the principle, industrial and commercial application of the invention is included in the scope of the claims of the invention, and any improvement on the technology based on the invention is taken from the claims of the invention.

Claims

1. A zero-emission aviation aircraft navigation process method, the method adopts mechanical power to drive the aircraft to navigate; the method is characterized in that according to the physical principle that the physical condition for determining the movement speed of an object is mechanical work, kinetic energy and momentum, the mechanical work formed by the action distance of force and force is directly utilized to pull the airplane to lift off and take off, the ground-off speed of the airplane is efficiently and maximally improved, and on the basis, an onboard power device of the airplane absorbs heat from generated compressed air to vaporize airborne and become high-pressure air to be sprayed out to the airplane backwards to generate recoil thrust to push the airplane to overcome resistance to fly in the air.

2. The method as claimed in claim 1, wherein the existing aviation aircraft is driven to run at high speed on the airport runway by using the fuel of the onboard turbine engine to jet outwards, so as to overcome the friction force between the onboard tires and the ground and enable the aircraft wings to generate lift force to take off; the improvement comprises that a steel rail is arranged on an airport runway, a flat car is arranged on the steel rail, an airplane is arranged on the flat car, a variable frequency electric winch arranged below the airport runway uses a cable to pull the flat car and the airplane to advance on the steel rail at a high speed, after the airplane reaches a set maximum speed on the flat car, the lift force of the wings of the airplane is adjusted to reach the maximum value, and meanwhile, an ejector and a buckling device arranged between the airplane and the flat car are opened, so that the airplane generates the flying speed off the ground as high as possible.

3. The method of claim 1, wherein a metallic enclosure is provided at the front end of the aircraft body to block high thermal barrier air at the front end of the aircraft, and a network of thermally evaporated metal pipes is provided at the back of the metallic enclosure, without affecting the visual field of the aircraft pilot; applying high pressure to liquid air stored in an airplane cabin by using a pneumatic working medium pump, pumping the liquid air into a thermal evaporation metal pipe network on the back of a metal housing, enabling the liquid air in the thermal evaporation metal pipe network to absorb heat from thermal barrier air at the front end of the airplane through the metal housing and vaporize the heat into high-pressure air, and finally spraying the high-pressure air to the rear of the airplane from a high-pressure air spray pipe arranged at the edge of the metal housing to form airplane advancing thrust; during landing, the high-pressure air jet pipe jets air towards the traveling direction of the airplane, so that resistance for decelerating and stopping the airplane is formed.

4. The method of claim 1, wherein during the short range flight condition, the aircraft is no longer fuelled and no turbine engine is provided, and after maximum ground speed is produced from cable pull and catapult ejection from the variable frequency electric winch, the aircraft is flown through a dense layer of sky air and then glided; when the aircraft needs to advance in the air in an accelerating way, liquid air carried by the aircraft absorbs heat from thermal barrier air at the front end of an aircraft body through a thermal evaporation metal pipe network and is vaporized to form high-pressure air, and finally, the high-pressure air is sprayed to the aircraft from a high-pressure air spray pipe arranged at the edge of a metal housing at the front end of the aircraft to push the aircraft to sail in the air against resistance.

5. The method according to claim 1, characterized in that, in the operating conditions of the aircraft during mid-range flight, there is also no fuel carried and no turbine engine; in order to multiply enlarge the flight range of the airplane under the premise of a set amount of liquid air carried by the airplane, on the basis of the short-range power device, a turbo air compressor and a high-pressure air spray pipe are arranged at the lower part of the wing of the existing airplane provided with a turbine engine, and meanwhile, an opposite convection heat exchanger and a pneumatic working medium pump are arranged in the wing; the turbo air compressor sucks a large amount of natural air from the advancing direction of the airplane, the natural air is pressurized by the turbine blades to form compressed air, and the compressed air is input into the opposite convection heat exchanger through the metal pipe; the opposite convection heat exchanger is composed of a high-pressure inner pipe and a medium-pressure outer pipe in a composite mode, compressed air is input into the medium-pressure outer pipe at the middle and hot ends of the opposite convection heat exchanger, a pneumatic working medium pump applies high pressure to liquid air stored in the machine cabin and pumps the liquid air into the high-pressure inner pipe at the cold end of the opposite convection heat exchange pipe, and the compressed air in the medium-pressure outer pipe and the liquid air in the high-pressure inner pipe perform opposite convection heat exchange; the compressed air is condensed into low-temperature liquid air in the cold end outer pipe of the opposite convection heat exchanger, so that the liquid air is continuously produced in the air; after high pressure is applied to liquid air by a pneumatic working medium pump, the liquid air is pumped into a cold end high-pressure inner pipe in the opposite convection heat exchanger and then exchanges heat with compressed air in a medium-pressure outer pipe in the opposite convection heat exchanger to finally become high-pressure air; inputting a small amount of the high-pressure air into a turbine expansion machine at the rear part of the turbo air compressor to do work, enabling the high-pressure air to become power for driving the turbo air compressor to continuously operate, and discharging clean tail gas to a natural space; the rest high-pressure air is sprayed out from the high-pressure air spray pipe arranged below the wing to the rear direction of the airplane and becomes the advancing power for driving the airplane to fly in the air against the resistance; liquid air formed by condensing and liquefying compressed air through the opposite convection heat exchanger is divided into a part and is injected into a thermal evaporation metal pipe network in a metal cover at the front end of the engine body after high pressure is applied to the part, so that the part absorbs heat and is vaporized and then is sprayed out of the engine from a high-pressure air spray pipe; therefore, airborne liquid air is enabled to provide cold energy supplement required by heat exchange temperature difference for maintaining set low temperature at the cold end of the opposite convection heat exchanger.

6. The method as claimed in claim 1, characterized in that in the operating mode of the aircraft for long-range flight, no fuel is carried and no turbine engine is arranged, on the basis of the arrangement of the medium-range power device, a storage battery, an electric heater, a throttle valve and a low-temperature high-pressure air throttle chamber are additionally arranged in the wing, and a generator is additionally arranged below the wing; before the airplane takes off, a ground power supply is used for supplying power to the storage battery; in the air gliding stage of the airplane, starting a generator which coaxially operates with the turbo air compressor to generate electricity and supplement the electric power of a storage battery, and occasionally utilizing a low-temperature high-pressure air throttling chamber to produce and store liquid air in the air gliding stage of the airplane; when the airplane needs strong air acceleration, the input amount of liquid air in a high-pressure inner pipe at the cold end of the opposite convection heat exchanger is increased, high-pressure air flowing out of a high-pressure pipe at the hot end of the opposite convection heat exchanger is introduced into an electric heater through a metal pipe for heating, a storage battery supplies power to the electric heater, the high-pressure air realizes equal-pressure volume-increasing expansion and heat absorption in the electric heater to become high-temperature high-pressure air, and finally the high-pressure air is sprayed out to the rear direction of the airplane from a high-pressure air spray pipe arranged below wings, so that the airplane is driven to accelerate.

7. The method according to claim 1, wherein the steel rails are arranged on the airport runway, and the flat car is placed on the steel rails, and the steel wheels below the flat car can roll on the steel rails to travel, or a magnetic levitation device is arranged between the flat car and the steel rails, so that the flat car can travel without friction under the working condition of levitation on the steel rails.

8. A zero-emission aviation aircraft power device comprises an aviation aircraft body, an airport and an airport lifting runway; the device is characterized by further comprising a variable-frequency electric winch, a cable, a steel rail, a flat car, a machine body and flat car buckling and pressing device, an ejector, a machine body front end metal housing, a thermal evaporation metal pipe network, a turbine air compressor, a liquid air storage bin, an opposite convection heat exchanger, a low-temperature high-pressure air throttling chamber, a throttling valve, a pneumatic working medium pump, a high-pressure air spraying pipe, a generator, a storage battery, an electric heater and a plurality of metal connecting pipes.

9. The variable-frequency electric winch is arranged in a basement at the terminal of an airport runway, an ejector is arranged on a flat car, a steel rail is arranged on the airport take-off runway, the steel rail is fixedly installed on the ground of the airport runway, the flat car is arranged on the steel rail, the flat car and the variable-frequency electric winch are connected through a cable, an aviation airplane is arranged on the flat car, an electric buckling and pressing device is arranged between the flat car and an airplane body, the ejector is arranged at the rear end of the flat car, and the ejector abuts against the rear end of the airplane body; the front end of an aircraft body is provided with a metal housing for resisting heat expansion air, the back of the metal housing is provided with a thermal evaporation metal pipe network, and the left and right positions of the edge of the metal housing are symmetrically provided with high-pressure air spray pipes; a cold end liquid inlet pipe orifice in the thermal evaporation metal pipe network is connected with a pneumatic working medium pump arranged in the machine cabin through a metal pipe, and a hot end gas outlet pipe orifice is connected with a high-pressure air spray pipe; the inner cabin of the airplane body is provided with a liquid air storage cabin and a pneumatic working medium pump; in the short voyage working condition, the liquid air storage bin and the pneumatic working medium pump are connected with the thermal evaporation metal pipe network through metal pipes; in the middle-range working condition, the heat exchanger is also connected with the opposite convection heat exchanger through a metal pipe; in the long-range working condition, the liquid air storage bin is also connected with the low-temperature high-pressure air throttling chamber through the metal pipe.

10. A mid-range aircraft power plant according to claim 8, wherein the following components are additionally provided in addition to the above-mentioned on-board power plant: turbine air compressors are symmetrically arranged on the left and right of the position where a turbine engine is arranged on the lower portion of a wing of an existing airplane, the front portion of each turbine air compressor is provided with an air compressor, the rear portion of each turbine air compressor is provided with a turbine expander, a compressed air chamber in each air compressor is connected with an outer pipe at the hot end of an opposite convection heat exchanger through a metal pipe, and a high-pressure air chamber of each turbine expander is connected with a high-pressure inner pipe at the hot; the wing is also internally provided with an opposite convection heat exchanger and a pneumatic working medium pump, and the pneumatic working medium pump is respectively connected with a high-pressure inner pipe and a medium-pressure outer pipe at the cold end of the opposite convection heat exchanger through metal pipes; the opposite convection heat exchanger is composed of composite pipes, the inner pipe is a high-pressure pipe, and the outer pipe is a medium-pressure pipe; and meanwhile, a high-pressure air spray pipe is arranged at the bottom of the wing and is connected with a hot-end high-pressure inner pipe of the opposite convection heat exchanger through a metal pipe.

11. The power plant of a long-range aircraft according to claim 8, wherein the following components are additionally arranged on the basis of the power plant of the middle-range aircraft: a generator is arranged at the lower part of the wing, and the generator and the turbine air compressor run coaxially and are driven by the turbine expander; a storage battery, an electric heater and a low-temperature high-pressure air throttling chamber are additionally arranged in the wing; a throttle valve is arranged above the low-temperature high-pressure air throttling chamber, the throttle valve is connected with a high-pressure inner pipe in the middle of the opposite convection heat exchanger through a metal pipe, and the lower part of the low-temperature high-pressure air throttling chamber is connected with a liquid air storage bin in the machine bin through the metal pipe.

12. The invention as claimed in claim 8, wherein the ejector is a strong spring ejector, an electromagnetic ejector or a compressed air ejector.

13. The invention as claimed in claim 8, wherein the turbo air compressor is composed of an air compressor composed of turbine blades and a turbo expander which are coaxially assembled, and the air compressor at the front part of the turbo air compressor is responsible for compressing air at normal temperature and normal pressure into air at medium and low pressure with set pressure; the turbine expander at the rear part of the air compressor provides mechanical power for the front-end air compressor and the coaxially operated generator under the drive of the high-pressure air turbine; compressed air generated by an air compressor at the front end part is input into a hot end outer pipe of the opposite convection heat exchanger arranged in the wing through a metal pipeline; the high pressure air required by the rear-end turboexpander is provided by a hot-end high pressure pipe in the counter-flow heat exchanger, and the clean tail gas is discharged to the natural space.

14. The invention as claimed in claim 8, wherein the platform wagon is placed on the rails, which may be supported by steel wheels of the platform wagon, or the platform wagon is suspended on the rails by magnetic levitation means disposed between the platform wagon and the rails.

15. The invention as claimed in claim 8, wherein the pneumatic working medium pump is a working medium pump driven by high-pressure air generated in the front end thermal evaporation metal pipe network and the high-pressure pipe in the opposite convection heat exchanger.