阅读说明：本技术 梭镖型垂直发射可返回高超音速导弹飞机 (Shuttle dart type vertical launching returnable hypersonic missile aircraft ) 是由 林立 夏建国 于 2020-12-03 设计创作，主要内容包括：本发明一种梭镖型垂直发射可返回高超音速导弹飞机,它是用二台电磁型垂直起降喷气发动机和一台发电型超高速推力矢量喷气发动机来推动导弹飞机垂直起降、发射或飞行。现在飞机用的是涡轮喷气发动机,结构复杂、技术难度高,因涡轮制造需要大量的高性能的耐高温材料,这些材料贵如金,所以造成了加工难、制造难、维修难,是个世界性的难题,而本发明的飞机和喷气发动机,它体积小、重量轻、易加工、易制造、易维修,解决了这个世界性的难题,它比现在的喷气发动机结构更简单,去掉了涡轮和轴,去掉了阻力、降低了噪音,又有发电功能,它能控制燃烧室内的燃气温度和压气机的增压比,提高了热效率和推进效率,它能实现低油耗、高效率、高可靠性、运转性能良好的梭镖型垂直发射高超音速导弹飞机。(The invention relates to a dart type vertical launching returnable hypersonic guided missile aircraft, which uses two electromagnetic vertical take-off and landing jet engines and a power generation type hypersonic thrust vector jet engine to push the guided missile aircraft to take off, land, launch or fly vertically. The aircraft and the jet engine of the invention have small volume, light weight, easy processing, easy manufacturing and easy maintenance, solve the worldwide problem, have simpler structure than the existing jet engine, remove the turbine and the shaft, remove the resistance, reduce the noise, have the power generation function, can control the gas temperature in a combustion chamber and the pressurization ratio of a gas compressor, improve the thermal efficiency and the propulsion efficiency, and can realize a dart-type vertical launching hypersonic missile aircraft with low oil consumption, high efficiency, high reliability and good operation performance.)

1. A dart type vertical launching returnable hypersonic missile aircraft comprises a body (1), a chassis, a front wing (2), a vertical wing (3), a rear wing (4), a missile bay (5), an electromagnetic vertical take-off and landing jet engine (6), a power generation type ultrahigh-speed thrust vector jet engine (7), an adjustable air inlet (8), a vector spray pipe (9), an adjustable nozzle (10), a front landing gear wheel, a rear landing gear wheel (11), a high-pressure oil pipe, a high-pressure air pipe, a cable, a storage battery, a charger, a signal lamp, a radar, a computer, a display screen, an operating lever, an instrument and an electronic switch, wherein the missile bay (5) is used for loading missiles, bombs and satellites, the vector spray pipe (9) is used for regulating and controlling the direction, the missile aircraft is designed into a dart type, the body is designed into a stealthy streamline type, and the engine is designed into a non-turbine type missile aircraft, The power generation type, just guided missile aircraft is more advanced, characterized by: a sharp nose with a round tip is arranged right ahead a machine body (1) and can be opened or closed up and down, a front wing (2) and a rear wing (4) are arranged on the periphery of a chassis of the machine body (1), a door and a window are arranged on the machine body (1), a vertical wing (3) is arranged on the rear part of the machine body (1), the rear wing (4) can be folded upwards or folded on the front wing (2), air resistance can be reduced when a guided missile aircraft takes off, space can be saved when the guided missile aircraft stops on the ground, a front landing gear wheel is arranged on the front part under the chassis of the machine body (1), two rear landing gear wheels (11) are arranged on the rear part, an electromagnetic vertical take-off and landing jet engine (6) or an electromagnetic turbofan is respectively arranged on two sides of a missile cabin (5) of the machine body (1), a power generation super-speed thrust vector jet engine (7) is arranged on the rear part of the chassis of the machine body (1) and, the computer is started firstly, cover plates at two ends of the engine are opened, the power generation type ultra-high-speed thrust vector jet engine (7) is started simultaneously, the engine (7) can be started and generate power for the two electromagnetic type vertical take-off and landing jet engines (6), at the moment, the booster nozzles in the combustion chambers of the two electromagnetic type vertical take-off and landing jet engines (6) and the power generation type ultra-high-speed thrust vector jet engine (7) can automatically spray and burn mixed gas, the spark plugs can automatically ignite and burst, the generated high-temperature and high-pressure gas is discharged downwards from the adjustable exhaust port (13) and the vector spray pipe (9) through the adjustable nozzle (10), so that the reaction thrust to the engine is generated, the missile is pushed to ascend, the computer is used for controlling the air flow sprayed by each jet engine, the missile aircraft is ensured to ascend in balance or suspend in the air immovable, when the missile aircraft, the front and the rear landing gear wheels (11) are retracted, the two electromagnetic vertical take-off and landing jet engines (6) are closed, the cover plates at the two ends of the engines are closed, the plane is formed by the engine body (1) and the chassis, the air resistance is reduced, the rear wings (4) are unfolded and locked at the same time, the vector spray pipe (9) is regulated and controlled to spray air upwards, so that the guided missile aircraft flies at high hypersonic speed in the air or flies to an enemy target, a sharp nose with a round tip or a cabin door below the guided missile cabin (5) is opened, the guided missile is sent out from the sharp nose with the round tip or thrown to the enemy target from the cabin door opening to destroy an enemy project, then the guided missile aircraft returns, if the guided missile aircraft flies to space, only a rocket is required to be arranged behind the vector spray pipe (9) and the adjustable nozzle (10) of the guided missile aircraft which can return to the hypersonic speed by vertically launching in a dart type, and then the electricity generation type thrust vector jet engine (7, because the missile aircraft has limited fuel, the missile aircraft is sent into near space by using a rocket, the rocket is automatically separated and falls off, then the missile aircraft continuously rushes into space by using self power, the missile aircraft throws out a satellite in the space, when the missile aircraft returns, the missile aircraft rushes into the atmosphere to fly by using the self power, when the missile aircraft lands, cover plates at two ends of an engine are opened, two electromagnetic vertical take-off and landing jet engines (6) are started, a vector spray pipe (9) of a power generation type ultrahigh-speed thrust vector jet engine (7) is regulated and controlled to spray air downwards, air flow sprayed by each jet engine is controlled by a computer, the missile aircraft is ensured to land safely vertically or land on a runway in a sliding way, and the missile aircraft can fly at high supersonic speed by unmanned or manned operation.

2. An electromagnetic vertical take-off and landing jet engine comprises a shell (1), a stator (2), a rotor (3), a turbofan (4), a shaft (5), a gas compressor (6), a swirler (7), a high-pressure oil pipe (8), a high-pressure air pipe (9), a thrust augmentation nozzle (10), a combustion chamber (11), an air inlet (12) and an air outlet (13), wherein the electromagnetism consists of an armature and a permanent magnet and is used for pushing the permanent magnet to rotate by means of a moving magnetic field generated by current, when the engine is started, the moving magnetic field generated by the current in the stator (2) pushes the rotor (3) to rotate, the rotor (3) rotates to drive the turbofan (4) and the shaft (5) to rotate, the shaft (5) rotates to drive the gas compressor (6) to rotate at high speed to convey air to the combustion chamber (11), the thrust augmentation nozzle (10) in the combustion chamber (11) can automatically spray and burn mixed gas, and a spark plug can, the generated high-temperature and high-pressure fuel gas is discharged from the exhaust port (13), so that the reaction thrust to the engine is generated, and the missile aircraft is pushed to ascend.

3. A power generation type ultra-high-speed thrust vector jet engine comprises a shell (1), an adjustable air inlet (2), an outer turbofan (3), a force bearing frame (4), a small-sized high-speed thrust vector jet engine (5), an inner turbofan (6), a generator (7), a turbofan (8), an outer bypass (9), an inner bypass (10), a gas compressor (11), a swirler (12), a movable joint (13), an electric brush (14), a hollow shaft (15), a bearing (16), a high-pressure oil pipe (17), an oxygen supply and oil supply pipe (18), a boosting nozzle (19), a combustion chamber (20), a vector spray pipe (21), a rotator (22), an adjustable nozzle (23), a high-pressure oil pipe (24), a cable (25), a spark plug (26), an oil injector (27), a combustion chamber (28), a vector nozzle (29), a stator (30), a rotor (31), a coil and, Charger, accumulator, computer, instrument and electronic switch, the small-scale high-speed thrust vector jet engine (5) is made up of inner turbofan (6), hollow shaft (15), high-pressure oil pipe (24), cable (25), spark plug (26), fuel injector (27), combustion chamber (28) and vector nozzle (29) into an organic whole, it is used for driving the outer turbofan (3), inner turbofan (6), generator (7) and air compressor (11) to rotate, the hollow shaft (15) is used for transporting the fuel oil, while launching, the fuel injector (27) in the combustion chamber (28) of the small-scale high-speed thrust vector jet engine (5) will spray the gas mixture automatically, the spark plug (26) will ignite and burst automatically, the high-temperature high-pressure fuel gas produced is discharged from the vector nozzle (29), thus produced and acted thrust, impelled the inner turbofan (6) to rotate, the inner turbofan (6) rotates to drive the hollow shaft (15) to rotate, the hollow shaft (15) rotates to drive the outer turbofan (3), the generator (7) and the air compressor (11) to rotate together at a high speed to convey air to the combustion chamber (20), at the moment, the boosting nozzle (19) in the combustion chamber (20) can automatically spray and burn mixed gas, a spark plug can automatically ignite and explode, the generated high-temperature and high-pressure gas is discharged from the vector spray pipe (21) through the adjustable nozzle (23), and therefore reaction thrust on the engine is generated, and the missile aircraft is pushed to fly at a high supersonic speed.

Technical Field

The invention relates to a dart type vertical launching returnable hypersonic missile aircraft, an electromagnetic vertical take-off and landing jet engine and a power generation type ultrahigh-speed thrust vector jet engine which are matched with the dart type vertical launching returnable hypersonic missile aircraft.

Background

At present, no hypersonic returnable missile aircraft exists in the market, and all missiles are launched and cannot be returned. The invention relates to a missile launching method, which is characterized in that a missile needs fuel and a ramjet engine when being launched, the ramjet engine can not be started under the condition of static ground because the ramjet engine has no structure of an air compressor, so the ramjet engine is not suitable for being used as a power device of a common airplane, and through years of research, a dart type vertical launching missile airplane capable of returning to a hypersonic speed is invented. The structure of the existing airplane and jet engine is completely changed, the existing jet engine is a jet engine with a turbine structure, the function of generating electricity is not provided, a generator is additionally arranged, and another space is occupied. The prior turbojet engine has the defects of complex structure, high technical difficulty, difficult processing, difficult manufacturing and difficult maintenance due to the fact that the turbine and the shaft are manufactured by a large amount of high-performance high-temperature-resistant materials which are expensive such as gold, and is a worldwide problem. The existing turbojet engine is an oil slot, the high-temperature and high-pressure gas generated by explosion of mixed gas in a combustion chamber is used for pushing a turbine to rotate, the turbine rotates to drive a shaft, a fan and a gas compressor to rotate together, the turbine generates resistance to the discharge of the high-temperature gas, generates noise and consumes part of energy, so that the turbojet engine is high in oil consumption, low in efficiency, small in thrust, large in noise, large in size, difficult to machine, difficult to manufacture, difficult to maintain and high in cost. Because the high-temperature turbine, the air compressor and the fan are arranged on the same shaft, the gas temperature in the combustion chamber and the pressure ratio of the air compressor cannot be regulated, and the heat efficiency and the propulsion efficiency of the turbojet engine cannot be improved. In order to improve the thermal efficiency and the propulsion efficiency of the jet engine, and remove resistance and reduce noise, only a turbine and a shaft behind a combustion chamber of the jet engine are removed, the thermal efficiency and the propulsion efficiency can be improved only by scientifically and advanced removing the resistance and reducing the noise, the gas temperature in the combustion chamber and the pressure ratio of a gas compressor can be regulated and controlled, the power generation function can be realized, and the airplane and the jet engine can be realized, and have the advantages of simple structure, easy processing, easy manufacture and easy maintenance, low oil consumption, high efficiency, large thrust, high speed, low noise and low cost. At present, the energy is gradually exhausted, the energy is tense, the oil price is expensive, and only the major innovation, the invention of a new machine and a new airplane, the energy conservation and the protection of the natural environment are hard reasons. Through years of research, a dart type vertical launching missile aircraft capable of returning to hypersonic speed, an electromagnetic vertical take-off and landing jet engine matched with the dart type vertical launching missile aircraft, and a power generation type ultrahigh-speed thrust vector jet engine are invented. The missile-plane is a combination of missile and plane, it uses two novel jet engines as power device of missile-plane, it can implement missile-plane vertical launching, and can return to ground. The power generation type ultrahigh-speed thrust vector jet engine has the advantages that the structure of the existing airplane and jet engine is completely changed, a turbine and a shaft are removed, the structure is simpler, the oil consumption is lower, the efficiency is higher, the thrust is higher, the speed is higher, the noise is lower, the volume is smaller, the weight is lighter, the cost is lower, the processing is easy, the manufacturing and the maintenance are easy, the power generation function is realized, the gas temperature in a combustion chamber and the pressurization ratio of a gas compressor can be controlled by a computer, the heat efficiency and the propulsion efficiency are higher, the operating performance is better, and the worldwide problem is solved. The invention relates to a dart type vertical launching returnable hypersonic missile aircraft, which comprises a body, a chassis, a front wing, a vertical wing, a rear wing, a missile cabin, an electromagnetic vertical take-off and landing jet engine, a power generation type ultrahigh-speed thrust vector jet engine, an adjustable air inlet, a vector spray pipe, an adjustable nozzle, a front landing gear wheel, a rear landing gear wheel, a high-pressure oil pipe, a high-pressure air pipe, a cable, a storage battery, a charger, a signal lamp, a radar, a computer, a display screen, a control rod, an instrument and an electronic switch The dart type vertical launching with high reliability and good flight performance can return to the hypersonic missile aircraft. The missile aircraft is designed into a dart shape, the body of the missile aircraft is designed into a stealthy streamline shape, the missile aircraft has the advantages of high speed, small resistance, large lift force, large missile loading capacity and long time of flight, can vertically take off and land or slide, can suspend in the air and fly immovably or cruise, can realize unmanned or manned full-automatic driving and operation of the missile aircraft, has huge commercial development value, and inevitably makes great contribution to the national defense aviation industry.

Disclosure of Invention

The invention relates to a dart type vertical launching missile aircraft capable of returning to hypersonic missile aircraft, and aims to invent a missile aircraft which has the advantages of simple structure, low oil consumption, high efficiency, high thrust, high speed, easiness in processing, manufacture and maintenance, low noise, light weight, low cost and easiness in operation. The dart type vertical launching returnable hypersonic missile aircraft comprises a body, a chassis, a front wing, a vertical wing, a rear wing, a missile cabin, an electromagnetic type vertical take-off and landing jet engine, a power generation type hypersonic thrust vector jet engine, an adjustable air inlet, a vector jet pipe, an adjustable nozzle, a front landing gear wheel, a rear landing gear wheel, a high-pressure oil pipe, a high-pressure air pipe, a cable, a storage battery, a charger, a signal lamp, a radar, a computer, a display screen, an operating rod, an instrument and an electronic switch, has simpler structure, lower oil consumption, higher efficiency, higher thrust, higher speed, lower noise, lower cost, easy processing, easy manufacture, easy maintenance and a power generation function compared with the prior vertical take-off and landing supersonic aircraft, can regulate the gas temperature in a combustion chamber and the pressurization ratio of a gas compressor by the computer, can pilot the missile aircraft without people or with people, the dart type vertical launching can return to the hypersonic missile aircraft, and has the advantages of low pollution, low emission, low noise, low oil consumption, high efficiency, high reliability and good flight performance.

The technical scheme of the invention is realized as follows: a dart-type vertical launching returnable hypersonic missile aircraft comprises a body, a chassis, a front wing, a vertical wing, a rear wing, a missile bay, an electromagnetic vertical take-off and landing jet engine, a power generation type hypersonic thrust vector jet engine, an adjustable air inlet, a vector spray pipe, an adjustable nozzle, a front landing gear wheel, a rear landing gear wheel, a high-pressure oil pipe, a high-pressure air pipe, a cable, a storage battery, a charger, a signal lamp, a radar, a computer, a display screen, a control rod, an instrument and an electronic switch, wherein the missile bay is used for loading missiles, bombs and satellites, the vector spray pipe is used for regulating and controlling the direction, the missile aircraft is designed into a dart shape, the body is designed into a hidden streamline shape, an engine is designed into a non-turbine type and a power generation type, the missile aircraft is advanced, a sharp nose head is arranged right in front of the body and can be opened or closed up and down, the front wing and the rear wing are arranged on, the missile launching cabin has one electromagnetic vertical take-off and landing jet engine or one electromagnetic turbofan, one power generating superhigh speed thrust vector jet engine in the back part of the body chassis, one computer, two covers on two ends of the engine, one power generating superhigh speed thrust vector jet engine, one booster nozzle to spray mixed gas automatically, the spark plug can automatically ignite and burst, the generated high-temperature and high-pressure gas is discharged from the adjustable nozzle and the vector spray pipe downwards through the adjustable nozzle, so that reaction thrust to the engine is generated, the missile aircraft is pushed to ascend, the air flow sprayed by each jet engine is controlled by a computer, the missile aircraft is ensured to ascend in balance or suspend in the air and not move, when the missile aircraft ascends to a certain safe height, the front and rear landing frame wheels are folded, the two electromagnetic vertical take-off and landing jet engines are closed, the cover plates at the two ends of the engines are closed, the plane is formed between the aircraft body and the chassis, the air resistance is reduced, the rear wing is unfolded and locked, the vector spray pipe is regulated and controlled to spray upwards, the missile aircraft can cruise at high supersonic speed in the air or fly to an enemy target, the sharp aircraft nose with the circular tip or the cabin door below the missile cabin is opened, and the missile is emitted from the sharp aircraft nose mouth or thrown to the, The enemy project is destroyed by pushing, then the missile aircraft returns, if the missile aircraft flies to the space, only a rocket is needed to be arranged behind a vector spray pipe and an adjustable nozzle which are vertically launched in a shuttle dart type and can return to the hypersonic missile aircraft, then a power generation type ultrahigh-speed thrust vector jet engine is used for providing power and air for the rocket, because the missile aircraft has limited fuel, the missile aircraft is sent to the near space by using a rocket, the rocket is automatically separated and falls off, then the missile aircraft continues to rush into the space by using the power of the missile aircraft, the missile aircraft throws out a satellite, when the missile aircraft returns, the missile aircraft flies in the atmosphere by using the power of the missile aircraft, when the missile aircraft lands, cover plates at two ends of the engine are opened, two electromagnetic type vertical take-off and landing jet engines are started, the vector spray pipe of the power generation type ultrahigh-speed thrust vector jet engine is regulated and used for downwards jetting, and the, the safe vertical landing or sliding landing on the runway of the missile aircraft is ensured, and unmanned or manned guided missile aircraft can fly.

The invention relates to an electromagnetic vertical take-off and landing jet engine which comprises a shell, a stator, a rotor, a turbofan, a shaft, a gas compressor, a swirler, a high-pressure oil pipe, a high-pressure air pipe, a thrust augmentation nozzle, a combustion chamber, an air inlet and an air outlet.

The invention relates to a power generation type ultra-high-speed thrust vector jet engine which comprises a shell, an adjustable air inlet, an outer turbofan, a force bearing frame, a small-sized high-speed thrust vector jet engine, an inner turbofan, a power generator, a turbofan, an outer duct, an inner duct, a gas compressor, a swirler, a movable joint, an electric brush, a hollow shaft, a bearing, a high-pressure oil pipe, an oxygen supply and oil supply pipe, a boosting nozzle, a combustion chamber, a vector spray pipe, a rotator, an adjustable nozzle, a high-pressure oil pipe, a cable, a spark plug, a fuel injector, a combustion chamber, a vector nozzle, a stator, a rotor, a coil, a charger, a storage battery, a computer, an instrument and an electronic switch The inner turbofan, the generator and the compressor rotate, the hollow shaft is used for conveying fuel oil, when the jet engine is started, an oil injector in a combustion chamber of the small high-speed thrust vector jet engine can automatically jet and combust mixed gas, the spark plug can automatically ignite and explode, the generated high-temperature high-pressure fuel gas is discharged from the vector nozzle, so that reaction thrust is generated, the inner turbofan is pushed to rotate, the inner turbofan rotates to drive the hollow shaft to rotate, the hollow shaft rotates to drive the outer turbofan, the generator and the compressor to rotate together at high speed to convey air to the combustion chamber, at the moment, the thrust augmentation nozzle in the combustion chamber can automatically jet and combust the mixed gas, the spark plug can automatically ignite and explode, the generated high-temperature high-pressure fuel gas is discharged from the vector nozzle through the adjustable nozzle, so that the reaction thrust to the engine is generated, and the.

Drawings

FIG. 1 is a schematic illustration of a dart-type vertical launch returnable hypersonic missile aircraft of the present invention;

FIG. 2 is a schematic front side view of the structure of FIG. 1;

FIG. 3 is a schematic diagram of an electromagnetic VTOL jet engine of the present invention;

FIG. 4 is a side view schematic of the structure of FIG. 3;

FIG. 5 is a schematic view of a super high speed thrust vector jet engine of the power generation type of the present invention;

FIG. 6 is a side view schematic of the structure of FIG. 5;

FIG. 7 is a side view schematic of the structure of FIG. 6;

FIG. 8 is a side view schematic of the structure of FIG. 5;

the specific implementation mode is as follows:

as shown in figures 1 and 2, a dart type vertical launching returnable hypersonic missile aircraft comprises a body 1, a chassis, a front wing 2, a vertical wing 3, a rear wing 4, a missile bay 5, an electromagnetic vertical take-off and landing jet engine 6, a power generation type ultrahigh-speed thrust vector jet engine 7, an adjustable air inlet 8, a vector nozzle 9, an adjustable nozzle 10, a front landing gear wheel, a rear landing gear wheel 11, a high-pressure oil pipe, a high-pressure air pipe, a cable wire, a storage battery, a charger, a signal lamp, a radar, a computer, a display screen, a control lever, an instrument and an electronic switch, wherein the missile bay 5 is used for containing missiles, bombs and satellites, the vector nozzle 9 is used for regulating and controlling the direction, the missile aircraft is designed into a dart type, the body is designed into a dart type streamline type, the engine is designed into a non-turbine type and a power generation type, the missile aircraft is advanced, a sharp nose with a round tip is arranged right ahead of the, The aircraft can be opened or closed up and down, a front wing 2 and a rear wing 4 are arranged on the periphery of a chassis of an engine body 1, a door and a window are arranged on the engine body 1, a vertical wing 3 is arranged on the rear part of the engine body 1, the rear wing 4 can be folded upwards or folded on the front wing 2, air resistance can be reduced when a missile aircraft takes off, space can be saved when the missile aircraft stops on the ground, a front landing gear wheel is arranged at the front part below the chassis of the engine body 1, two rear landing gear wheels 11 are arranged at the rear part, an electromagnetic vertical take-off and landing jet engine 6 or an electromagnetic fan is respectively arranged at two sides of a missile cabin 5 of the engine body 1, a power generation type ultrahigh-speed thrust vector jet engine 7 is arranged at the rear part of the chassis of the engine body 1, a computer is started firstly during vertical take-off, cover plates at two ends of the engine are opened, and the power generation type ultrahigh, The power generation is used for two electromagnetic vertical take-off and landing jet engines 6, at the moment, the boosting nozzles in the combustion chambers of the two electromagnetic vertical take-off and landing jet engines 6 and the power generation type super-high-speed thrust vector jet engine 7 can automatically spray and burn mixed gas, the spark plugs can automatically ignite and burst, the generated high-temperature and high-pressure gas is discharged downwards from the adjustable exhaust port 13 and the vector spray pipe 9 through the adjustable spray nozzles 10, so that the reaction thrust to the engines is generated, the missile aircraft is pushed to ascend, the air flow sprayed by the jet engines is controlled by a computer, the missile aircraft is ensured to ascend in a balanced manner or suspend in the air immovable manner, when the missile aircraft ascends to a certain safety height, the front and rear landing frame wheels 11 are folded, the two electromagnetic vertical take-off and landing jet engines 6 are closed, the cover plates at the two ends of the engines are closed, the machine body 1, meanwhile, the rear wing 4 is unfolded and locked, the vector nozzle 9 is regulated and controlled to jet air upwards, so that the guided missile aircraft flies at high supersonic speed in the air or flies to an enemy target, a sharp-pointed nose or a cabin door below the guided missile cabin 5 is opened, a guided missile is sent out from a sharp-pointed nose port or thrown to the enemy target from a cabin door port, the enemy project is destroyed, then the guided missile aircraft returns, if the guided missile aircraft flies to the space, only a rocket is required to be vertically launched in a shuttle dart shape to return to the hypersonic guided missile aircraft, a rocket is arranged behind the vector nozzle 9 and an adjustable nozzle 10, a power generation type ultrahigh-speed thrust vector jet engine 7 is used for providing power and air for the rocket, because the guided missile aircraft has limited fuel, the guided missile aircraft is sent to the near space by using a rocket, the rocket is automatically separated and falls off, then the guided missile aircraft continuously rushes into the space by using the power of the guided missile aircraft, and the guided missile, when the missile aircraft returns, the missile aircraft flies in the atmosphere by using the power of the missile aircraft, when the missile aircraft lands, the cover plates at the two ends of the engine are opened, the two electromagnetic vertical take-off and landing jet engines 6 are started, the vector jet pipe 9 of the power generation type ultrahigh-speed thrust vector jet engine 7 is regulated and controlled to jet air downwards, the air flow sprayed by each jet engine is controlled by a computer, the missile aircraft is ensured to land safely and vertically or slide on a runway to land, and the high-supersonic speed flight of the missile aircraft controlled by unmanned or manned operation can be realized.

As shown in fig. 3 and 4, an electromagnetic vertical take-off and landing jet engine comprises a shell 1, a stator 2, a rotor 3, a turbofan 4, a shaft 5, a compressor 6, a swirler 7, a high-pressure oil pipe 8, a high-pressure air pipe 9, a thrust augmentation nozzle 10, a combustion chamber 11, an air inlet 12 and an air outlet 13, wherein the electromagnetism is composed of an armature and a permanent magnet and is used for pushing the permanent magnet to rotate by means of a moving magnetic field generated by current, when the engine is started, the rotor 3 is pushed to rotate by the moving magnetic field generated by the current in the stator 2, the turbofan 4 and the shaft 5 are driven to rotate by the rotation of the rotor 3, the shaft 5 drives the compressor 6 to rotate at high speed to convey air to the combustion chamber 11, the thrust augmentation nozzle 10 in the combustion chamber 11 can automatically spray and combust mixed gas, a spark plug can automatically ignite and explode, and the generated high-temperature and high-pressure gas is, pushing the missile plane to ascend.

As shown in figures 5, 6, 7 and 8, the power generation type ultra-high speed thrust vector jet engine comprises a shell 1, an adjustable air inlet 2, an outer turbofan 3, a force bearing frame 4, a small high speed thrust vector jet engine 5, an inner turbofan 6, a generator 7, a turbofan 8, an outer bypass 9, an inner bypass 10, a compressor 11, a swirler 12, a movable joint 13, an electric brush 14, a hollow shaft 15, a bearing 16, a high pressure oil pipe 17, an oxygen supply and oil supply pipe 18, an afterburning nozzle 19, a combustion chamber 20, a vector spray pipe 21, a rotator 22, an adjustable nozzle 23, a high pressure oil pipe 24, a cable 25, a spark plug 26, an oil injector 27, a combustion chamber 28, a vector spray nozzle 29, a stator 30, a rotor 31, a coil, a charger, a storage battery, a computer, instruments and electronic switches, wherein the small high speed thrust vector jet engine 5 comprises the inner turbofan 6, the hollow shaft 15, the high pressure oil pipe, The cable 25, the spark plug 26, the fuel injector 27, the combustion chamber 28 and the vector nozzle 29 are combined into a whole, the outer turbofan 3, the inner turbofan 6, the generator 7 and the compressor 11 are driven to rotate by the cable, the hollow shaft 15 is used for conveying fuel oil, when the small-sized high-speed thrust vector jet engine 5 is started, the fuel injector 27 in the combustion chamber 28 automatically sprays and combusts mixed gas, the spark plug 26 automatically ignites and explodes, the generated high-temperature high-pressure fuel gas is discharged from the vector nozzle 29 to generate reaction thrust to push the inner turbofan 6 to rotate, the inner turbofan 6 rotates to drive the hollow shaft 15 to rotate, the hollow shaft 15 rotates to drive the outer turbofan 3, the generator 7 and the compressor 11 to rotate together at a high speed to convey air to the combustion chamber 20, the boosting nozzle 19 in the combustion chamber 20 automatically sprays and combusts the mixed gas, the spark plug automatically ignites and explodes, the generated high-temperature high-pressure fuel gas is discharged from the vector nozzle 21 through the adjustable nozzle 23, thereby generating reaction thrust to the engine and pushing the missile aircraft to fly at hypersonic speed.