CN209126969U - It can the annular wing disc-shaped flying craft that can hover of VTOL - Google Patents

Abstract

The utility model disclose it is a kind of can the annular wing disc-shaped flying craft that can hover of VTOL, the aircraft is made of oval fuselage, cockpit, main cabin, piggyback pod, taper tail vane, the annular wing, flight controller etc., since fuselage is using oval saucer structure, it is the optimal configuration that flies in air flow field, it is minimum for the disturbance of gas flowfield, and air drag is minimum in flight course.Such shape is with VTOL achieved by multiaxis screw wing power aerial vehicle, the flight performances such as fixed height hovers, but compared with multiaxis screw wing power aerial vehicle, flight attitude is hardly influenced by air effluent, and flight attitude is more reliable reliable；There is flying speed achieved by fixed-wing duct aircraft again, and flight energy consumption is much smaller than existing fixed-wing duct aircraft, and landing does not need runway auxiliary, the utility model can obtain lift required for aircraft, reduce the resistance of aircraft and improve its flight safety performance, be easy to popularization and application.

Description

It can the annular wing disc-shaped flying craft that can hover of VTOL

Technical field

The utility model relates to aerospace field technology, refer in particular to it is a kind of can the annular wing dish that can hover of VTOL Shape aircraft.

Background technique

In recent years, with the continuous social and economic development, urban population and motor vehicles increasingly increase, urban highway traffic It is crowded oneself is through becoming the generally existing phenomenon in world big and medium-sized cities with obstruction, thus bring traffic congestion, traffic accident, energy The problems such as environmental pollution caused by the automobile emission that source wastes and is multiplied, not only seriously restrict city and society The economic sustainable development of meeting, while also severely impacting the quality of life of city dweller.Traffic above-ground is no longer satisfied The growing material life of people needs, it is faster, conveniently, efficiently aerial multilevel traffic will become people and study and close The new issue of note.

Most aviation aircraft can be seen from daily life usually has two classes:

1, Fixed Wing AirVehicle, such as airline carriers of passengers: 5000-10000 meters of height, 500-800 kilometers per hour of speed.Civil aviaton Passenger plane generallys use fixed-wing and adds jet engine form, and loading capacity is big, and flying speed is fast, and mobility is high.Aircraft flight is not By the barrier of high mountain, river, desert, ocean goer.It is safe, comfortable, and relatively small, safety coefficient height is influenced by weather.Gu but Determine that wing aircraft is maximum the disadvantage is that landing must be using sliding speedup or deceleration, therefore is seriously limited by landing site, no It may be popularized as automobile.

2, screw wing class aircraft, such as helicopter: below height ten thousand metres.Speed is about 0-300 kilometers per hour. Helicopter is its biggest characteristic is that provide upward lift with one or more large-scale power engines rotated horizontally.Helicopter it is excellent Point is can be vertically moved up or down, and can also rest on motionless (hovering) in midair, can do low latitude, low speed or fly backward.But it goes straight up to Machine is due to flying and seriously restricting in the shadow of air effluent and turbulent flow using without constraint free space spiral shell power engine driving It rings, driving difficulty is big, and safety cannot ensure.It can not be promoted as civil aircraft.

Summary of the invention

In view of this, the utility model is in view of the existing deficiencies of the prior art, main purpose is to provide one kind can be vertical The annular wing disc-shaped flying craft that landing can hover can be used as civil aircraft popularization.

To achieve the above object, the utility model is using following technical solution:

It is a kind of can the annular wing disc-shaped flying craft that can hover of VTOL, including

One fuselage, the shape of the fuselage are dished disk shapes；

One cockpit, the cockpit are circle, and cockpit protrudes from the top of fuselage, and to fly, people can be looked around week Surrounding environment；

One main cabin, the main cabin are located in fuselage and immediately below cockpit, and main cabin (seizing the opportunity cabin) is provided with biggish sky Between, to take passenger or loading；

One piggyback pod, the piggyback pod are located in the peripheral ring shaped region in main cabin, and aircraft central axis is surrounded on piggyback pod It is uniformly distributed several channels up and down；The upper end in each channel is the intermittent air entry with water conservancy diversion of annular, in each channel In engine is set, for the engine by inside air-breathing suitable for reading, it is dynamic that the mode of the lower downward jet of mouth for aircraft provides flight Power；

The border circular areas within main cabin is arranged in one taper tail vane, the taper tail vane, which connects steering engine, root According to the variation of flying speed, the cone tail of tail vane can be elongated, shortened or disappeared, to reduce air when aircraft goes up to the air rapidly Viscous force；

The one annular wing, the annular wing are arranged in the region other than piggyback pod, and the annular wing, which passes through, dashes forward under the edge of a wing, upwarps or hidden Hiding flies to change the lift or up reversal power of air to realize to go up to the air, land or put down in flight course；

One flight controller, the flight controller are set on aircraft.

The utility model has clear advantage and beneficial effect compared with prior art, specifically, by above-mentioned technology Scheme it is found that

One, the utility model disclose it is a kind of can the annular wing disc-shaped flying craft that can hover of VTOL, the aircraft is by ellipse The compositions such as round fuselage, cockpit, main cabin, piggyback pod, taper tail vane, the annular wing, flight controller, since fuselage is using oval Shape saucer structure is the optimal configuration that flies in air flow field, and the structure is minimum for the disturbance of gas flowfield, and Air drag is minimum in flight course.The aircraft shape of the utility model can be real with multiaxis screw wing power aerial vehicle institute Existing VTOL, the flight performances such as fixed high hovering, but compared with multiaxis screw wing power aerial vehicle, flight attitude is hardly by sky The influence of gas side stream, flight attitude are more reliable reliable；The utility model aircraft has fixed-wing duct aircraft institute can be real again Existing flying speed, and flight energy consumption is much smaller than existing fixed-wing duct aircraft, and landing does not need runway auxiliary, is general And the speciality that property aircraft must have.So that the resistance that the utility model obtains lift required for aircraft, reduces aircraft Power and the flight safety performance for improving it.

Two, utility model people is also disclosed for many years for the result of study of Bird Flight in the utility model, and with Bird Flight Posture is reference, for it is described in the utility model can the air force of annular wing disc-shaped flying craft that can hover of VTOL it is special Point, carries out the imitation and improvement of Bird Flight, to design the intermittent air entry with water conservancy diversion of annular, telescopic taper tail Rudder and the annular wing.Air entry allows aircraft from surface air-breathing, so that generating a cylinder vacuum negative pressure right above aircraft Region, to obtain the pulling force moved upwards.Engine is set among the channel of piggyback pod, can be passed through according to power demand It is a series of to accurately calculate, rotating air suction can control, continual is generated, and the air of sucking is sprayed to aircraft lower part Stomata jet-stream wind obtains corresponding thrust.Border circular areas of the aircraft lower part fumarole within main cabin is provided with taper Tail vane, tail vane be able to can elongate as needed the cone tail of tail vane, shorten or disappear according to the variation of flying speed, to reduce The viscous force of air when aircraft goes up to the air rapidly.Oval fuselage circumference is provided with the annular wing can be stealthy or deformed, the annular wing Can be according to the needs of flight attitude or stealthy, or upwarp, or drop-down, optimal flight performance is obtained to cooperate.

For the structure feature and effect for more clearly illustrating the utility model, come with reference to the accompanying drawing with specific embodiment pair The utility model is described in detail.

Detailed description of the invention

Fig. 1 is the aircraft appearance schematic diagram of the embodiment of the utility model.

Fig. 2 is the aircraft top view of the embodiment of the utility model.

Fig. 3 is the internal structure chart of the axial flow turbojet of the embodiment of the utility model.

Fig. 4 is the internal structure chart of the turbofan of the embodiment of the utility model.

Fig. 5 is the bionical working principle diagram of aircraft birds of the embodiment of the utility model.

Fig. 6 is the air-flow and mechanics study figure of the embodiment to Bird Flight of the utility model.

Fig. 7 is the embodiment of the utility model to birds wing structural research figure.

Fig. 8 is the athletic posture performance plot of the aircraft vertical movement of the embodiment of the utility model.

Fig. 9 is the athletic posture performance plot of the aircraft pitching movement of the embodiment of the utility model.

Figure 10 is the athletic posture performance plot of the aircraft rolling movement of the embodiment of the utility model.

Figure 11 is the athletic posture performance plot of the vehicle yaw movement of the embodiment of the utility model.

Figure 12 is the athletic posture performance plot that the aircraft of the embodiment of the utility model moves forward and backward.

Figure 13 is the athletic posture performance plot of the aircraft lateral movement of the embodiment of the utility model.

Description of drawing identification:

10, fuselage 20, cockpit

30, main cabin 40, piggyback pod

41, channel 42, air entry

43, engine 50, taper tail vane

60, the annular wing

80, axial flow turbojet 81, the first outer cylinder

82, first rotating shaft 83, inlet plenum

84, low pressure compressor 85, high pressure compressor

86, the first combustion chamber 87, the first turbine

88, exhaust chamber 90, turbofan

91, the second outer cylinder 92, the second shaft

93, fan 94, compressor

95, the second combustion chamber 96, the second turbine

97, jet pipe 98, main duct

99, by-pass air duct.

Specific embodiment

It please refers to shown in Fig. 1 to Fig. 3, it to be a kind of that show the specific structures of the preferred embodiment of the utility model Can 60 disc-shaped flying craft of the annular wing that can hover of VTOL, including fuselage 10, cockpit 20, main cabin 30, piggyback pod 40, taper Tail vane 50, the annular wing 60, flight controller (not shown go out).

Wherein, the shape of the fuselage 10 is dished disk shape, and vertical section is an ellipsoidal structure.

The cockpit 20 is circle, and cockpit 20 protrudes from the top of fuselage 10, and to fly, people can look around periphery Environment.

The main cabin 30 is located in fuselage 10 and immediately below cockpit 20, and biggish space can be set in main cabin 30, uses To take passenger or loading.

The piggyback pod 40 is located in the peripheral ring shaped region in main cabin 30, uniform around aircraft central axis on piggyback pod 40 It is distributed several channels 40 up and down；The upper end in each channel 40 is the intermittent air entry 42 with water conservancy diversion of annular, each logical The inner setting engine 43 in road 40, the engine 43 are mentioned by inside air-breathing suitable for reading, the mode of the lower downward jet of mouth for aircraft For flying power.

The border circular areas within main cabin 30 is arranged in the taper tail vane 50, which connects steering engine, according to winged The variation of scanning frequency degree can elongate the cone tail of tail vane, shortens or disappear, to reduce the viscous of air when aircraft goes up to the air rapidly Power.

And the annular wing 60 is arranged in the region other than piggyback pod 40, the annular wing 60 pass through dash forward under the edge of a wing, upwarp or It hides, to change the lift or up reversal power of air, flies to realize to go up to the air, land or put down in flight course.

The flight controller is set on aircraft, and management, the flight for controlling aircraft power battery are fast in real time Degree management, to ensure to control acceleration management, cockpit 20 and 30 air pressure of main cabin, temperature, oxygen content parameter comfortable and set Management, emergency escape management.

Can requirement situation according to the load-carrying of aircraft and own wt and user to aircraft performance, phase is set 3 or 3 or more engines 43 usually can be set in channel 40 and the engine 43 for answering quantity.The utility model patent is to set It sets for 4 engines 43 and illustrates Flight Vehicle Structure characteristic and flight theory.

Channel 40 on the piggyback pod 40 of the utility model has four, is provided with 4 engines 43 and forms four active flights Device.Aircraft described in the utility model can configure different types of air-breathing jet engine 43, to obtain different Performance and flying speed, such as axial flow turbojet 80, turbofan 90, turbine wheel shaft can be selected to start Machine 43(is not shown out).

As shown in figure 3, the axial flow turbojet 80 includes the first outer cylinder 81, first rotating shaft 82, inlet plenum 83, low pressure compressor 84, high pressure compressor 85, the first combustion chamber 86, the first turbine 87, exhaust chamber 88, first outer cylinder 81 are divided into 5 sections from top to bottom, and the inner diameter size of paragraph 1 is identical, and the 2nd section of internal diameter gradually becomes smaller, and the 3rd section of internal diameter, which first becomes larger, to be continued Become smaller again after a distance, the 4th section of internal diameter becomes larger, and the 5th section of internal diameter gradually becomes smaller；The inlet plenum 83 setting is the The top of one outer cylinder 81, the low pressure compressor 84 are located inside paragraph 1, and the high pressure compressor 85 is located at the 2nd intersegmental part, institute It states the first combustion chamber 86 and is centered around outside first rotating shaft 82 and is located at the 3rd intersegmental part, first turbine 87 is located in the 4th section Portion, the exhaust chamber 88 are located at the 5th intersegmental part.

This axial flow turbojet 80 is completely dependent on combustion gas stream and generates thrust, and whirlpool jet circulation road 40 only has one A, efficiency is higher when high speed, can provide high speed motive force, and axial flow turbojet 80 has cross section small, pressure Contracting is than high advantage.After the flying speed of aircraft is more than velocity of sound (Ma > 1.0), this axial flow turbojet 80 Propulsive efficiency promoted rapidly, even if the propulsive efficiency of turbojet 43 is still under Mach number 2.5-3.0 range It can achieve 90%, can be realized the supersonic cruise of (Ma1.4).

As shown in figure 4, the turbofan 90 includes the second outer cylinder 91, the second shaft 92, fan 93, compressor 94, the second combustion chamber 95, the second turbine 96, jet pipe 97, second outer cylinder 91 have main duct 98 and by-pass air duct 99, this is interior Duct 98 passes through for 43 core air of engine, which is located at the outside of main duct 98, only 93 air of fan By；Second outer cylinder 91 is divided into 3 sections from top to bottom, and the internal diameter of paragraph 1 gradually becomes smaller in bell shape, the outer culvert Road 99 extends to the 3rd section of end since the 2nd section, and the 2nd section of internal diameter becomes larger, and the 3rd section of internal diameter gradually becomes smaller；The wind Fan 93 is set in paragraph 1, and compressor 94 is arranged in main duct 98 and positioned at the 2nd section of upper position, second burning Room 95 is located at outside the second shaft 92 and in the 2nd section of medium position, and second turbine 96 is positioned at the 2nd section by bottom It sets, 3 intersegmental part forms the jet pipe 97.

The area of the chopped-off head compressor 94 of this turbofan 90 is larger, is simultaneously used as air propeller, By the air of part sucking by the periphery of injection engine to pusher, 43 core air of engine passes through main duct 98, only The core engine exterior portion that 93 air of fan passes through is by-pass air duct 99.

The Some gases thermal energy of fanjet 43 passes to fan 93 by efficient second turbine 96, due to wind Work efficiency is high for fan 93, helps to improve 43 propeller power of engine；Meanwhile also making the reduction of intension jet velocity, engine 43 reduce from speed loss, it helps improve 43 propulsive efficiency of engine.So the gross efficiency of fanjet 43 is high, oil consumption Rate is low, 43 good economy performance of engine.Turbofan 90 is most suitable for use at 400 to 1000 kilometers of flying speed.

In addition, this turbofan 90 is the high duct turbofan of mixing exhaust, due to the inside and outside culvert of engine 43 Jet velocity substantially reduces, and 43 jet noise intensity of engine is directly proportional to eight times squares of jet velocity.So engine 43 jet noises are lower, and the total noise level of engine 43 is relatively low, effectively reduce the noise pollution to environment, can make to fly Row device becomes more comfortable.

Aircraft described in the utility model can also carry the aircraft power device of other existing different sizes and model, Make it that can show completely different flight performance.According to actual needs can 0 to 800 kilometers/hour when vt space in, Between 0 to ten thousand metres high-altitude, according to user to aircraft performance different demands, the civilian individual of different model specification is customized Aviation aircraft.

In conjunction with shown in Fig. 2, Fig. 5 to Fig. 7, by studying birds flapping flight bionics, the structure including studying feather of birds How air friction in-flight, the speed of the flowing that how to perceive air and direction, air pressure, height above sea level etc. can reduce, with And it is lifted on research birds wing and the movements such as wing pushing.Under the inspiration of Bird Flight mechanism, it is winged to obtain the utility model Row device structural design scheme: the intermittent air entry 42 with water conservancy diversion of annular, from aircraft right above air-breathing so that aircraft just on Side generates a cylinder vacuum negative pressure region, to obtain the pulling force (as shown in Figure 5) moved upwards.In the channel of piggyback pod 40 Engine 43 is set among 40, can be accurately calculated, be generated can control, constant by a series of according to power demand Rotating air suction, and the air of sucking is pushed away accordingly to aircraft lower part (near-earth heart side) fumarole jet-stream wind Power.Border circular areas of the aircraft lower part fumarole within main cabin 30 is provided with taper tail vane 50, and tail vane can be according to flight The variation of speed can elongate as needed the cone tail of tail vane, shorten or disappear, to reduce air when aircraft goes up to the air rapidly Viscous force.Oval 10 periphery of fuselage is provided with the annular wing 60 can be stealthy or deformed, and the annular wing 60 can be according to flight attitude It needs or stealthy, or upwarps, or drop-down, obtain optimal flight performance to cooperate.

The flight controller of 60 butterfly aircraft of the annular wing of the utility model is collection singlechip technology, a sensor skill More technologies such as art, GPS navigation technology, mechanics of communication, flight control technology, task control technology, programming technique simultaneously rely on hard The high-tech product of part.It controls butterfly aircraft and realizes the movement such as climb, hover, turning.

Specifically, the integrated and external computing unit of the flight controller, navigation sensor, wireless data transmission module, Engine 43 and steering engine control module.The navigation sensor includes inertial navigation, earth magnetism, GPS, ultrasonic wave, laser, barometer, light Stream, navigation camera etc..The engine 43 and steering engine control module are connected with engine 43, steering engine respectively, the no line number Transmission module realizes the flight of aircraft remote control, and the flight controller operation has embedded system, and has sensing data Fusion, posture and position control, independent navigation, autonomous flight, destination management, failure protection function.For example, can select plus take Big Micropilot business flies control.

As shown in Fig. 8 to Figure 13, the utility model is on four power aerial vehicles equipped with front and rear, left and right, upper and lower 3 directions Gyroscope and 3 reference axis are that the acceleration transducer of shaft forms inertial navigation module, calculate aircraft with respect to ground Posture and acceleration, angular speed, flight controller by algorithm, calculate rotary force required when motion state to be kept and Lift, and engine 43 is fed back to by electronic adjusting controller, so that engine 43 exports suitable power to complete aircraft phase The movement posture answered:

(1) it moves vertically

Referring to Fig. 8, adjacent two pairs of engines 43 can be set and turn on the contrary, the air-flow that they spray in this way can balance it To the reaction torque of fuselage 10, when the output power for increasing by four engines 43 simultaneously, 43 output power of engine increases so that total Pulling force increase, when total pulling force is enough to overcome the weight of complete machine, four power aerial vehicles just liftoff vertical ascent；Conversely, simultaneously Reduce the output power of four engines 43, four power aerial vehicles then vertically decline, until balance landing, realizes along z-axis Vertical movement；When external disturbance amount is zero, when the lift that engine 43 generates is equal to the self weight of aircraft, aircraft is just protected Hold floating state.

(2) pitching movement

Referring to Fig. 9, the output power of the 1st engine rises, the output power decline of the 3rd engine, the 2nd engine, the 4th The output power of engine remains unchanged, in order not to because the change of 43 output power of engine causes four power aerial vehicles whole Torque and total pulling force change, the 1st engine answered with the size of the 3rd engine output power knots modification it is equal, due to the 1st engine Lift rise, the drop in lift of the 3rd engine, the unbalanced moments of generation makes fuselage 10 rotate (direction such as Fig. 9 institute around y-axis Show), similarly, when the output power of the 1st engine declines, the output power of the 3rd engine rises, and fuselage 10 is just around y-axis to another One direction rotates, and realizes the pitching movement of aircraft.

(3) rolling movement

Referring to Figure 10, rolling movement is identical as pitching movement principle, and rolling movement need to change the 2nd engine and the 4th and start The output power of machine keeps the output power of the 1st engine and the 3rd engine constant, then fuselage 10 can be made to rotate around x axis (just To with it is reversed), realize the rolling movement of aircraft；

(4) yawing rotation

Referring to Figure 11, four power aerial vehicle yawing rotations can be by the reaction torque and fuselage appropriate that engine 43 generates 10 inclinations are to realize, in 43 rotation process of engine, since air drag effect will form the reaction torque opposite with rotation direction, In order to overcome reaction torque to influence, two in four engines 43 can be made to rotate forward, two reversions, and each on diagonal line starts 43 rotation direction of machine is identical.The size of reaction torque is related with 43 output power of engine, when four 43 output power phases of engine Meanwhile the reaction torque that four engines 43 generate mutually balances, four power aerial vehicles do not rotate；When four engines 43 are defeated When power is not exactly the same out, unbalanced reaction torque can cause four power aerial vehicles to rotate；When the 1st engine and the 3rd starts The output power of machine rises, when the output power of the 2nd engine and the 4th engine declines, the 1st engine and the 3rd engine pair The reaction torque of fuselage 10 is greater than the 2nd engine and the 4th engine to the reaction torque of fuselage 10, and fuselage 10 is just in reaction torque more than needed It is rotated under effect around z-axis, realizes the yawing rotation of aircraft, turned to opposite with the 1st engine, the steering of the 3rd engine.Because The total life of engine 43 is constant, and aircraft will not move vertically.

(5) it moves forward and backward

Referring to Figure 12, to realize the movement of aircraft front and rear, left and right in the horizontal plane, it is necessary in the horizontal plane to flight Device applies certain power, increases the 3rd engine output power of power, increases pulling force, corresponding to reduce the output of the 1st engine of power Power reduces pulling force, while keeping 43 output power of other two engines constant, and reaction torque still will keep balancing.It presses According to pitching movement theory, a degree of inclination occurs first for aircraft, to make 43 pulling force generation level of power engine point Amount, therefore the preceding winged movement of aircraft may be implemented.It flies backward exactly the opposite with flight forward.Certainly in Fig. 9 Figure 10, fly Row device can also generate the horizontal movement along x, y-axis while generating pitching, tumbling motion.

(6) lateral movement

Referring to Figure 13, due to four power aerial vehicle symmetrical configurations, so the working principle of crabbing with moved forward and backward It is complete the same.

The above descriptions are merely preferred embodiments of the present invention, not makees to the technical scope of the utility model Any restrictions, therefore any trickle amendment made by the above technical examples according to the technical essence of the present invention, equivalent change Change and modify, is still within the scope of the technical solutions of the present invention.

Claims (7)

1. one kind can the annular wing disc-shaped flying craft that can hover of VTOL, it is characterised in that: including

One fuselage, the shape of the fuselage are dished disk shapes；

One cockpit, the cockpit are circle, and cockpit protrudes from the top of fuselage, and to fly, people can look around peripheral ring Border；

One main cabin, the main cabin are located in fuselage and immediately below cockpit；

One piggyback pod, the piggyback pod are located in the peripheral ring shaped region in main cabin, uniform around aircraft central axis on piggyback pod It is distributed several channels up and down；The upper end in each channel is the intermittent air entry with water conservancy diversion of annular, is set in each channel Engine is set, the engine provides flying power by inside air-breathing suitable for reading, the mode of the lower downward jet of mouth for aircraft；

The border circular areas within main cabin is arranged in one taper tail vane, the taper tail vane, which connects steering engine, according to winged The variation of scanning frequency degree can elongate the cone tail of tail vane, shortens or disappear, to reduce the viscous of air when aircraft goes up to the air rapidly Power；

The region other than piggyback pod is arranged in the one annular wing, the annular wing, and the annular wing, which passes through, to be dashed forward, upwarp or hide under the edge of a wing, Change the lift or up reversal power of air, goes up to the air, lands or flat fly in flight course to realize；

One flight controller, the flight controller are set on aircraft.

2. according to claim 1 can the annular wing disc-shaped flying craft that can hover of VTOL, it is characterised in that: the hair Motivation is axial flow turbojet, including the first outer cylinder, first rotating shaft, inlet plenum, low pressure compressor, high pressure compressed Machine, the first combustion chamber, the first turbine, exhaust chamber, first outer cylinder are divided into 5 sections from top to bottom, the inner diameter size phase of paragraph 1 Together, the 2nd section of internal diameter gradually becomes smaller, and the 3rd section of internal diameter first becomes larger and becomes smaller after lasting a distance again, and the 4th section of internal diameter gradually becomes Greatly, the 5th section of internal diameter gradually becomes smaller；The top of the first outer cylinder is arranged in the inlet plenum, and the low pressure compressor is located at paragraph 1 Inside, the high pressure compressor are located at the 2nd intersegmental part, and first combustion chamber is centered around outside first rotating shaft and is located at the 3rd section Inside, first turbine are located at the 4th intersegmental part, and the exhaust chamber is located at the 5th intersegmental part.

3. according to claim 1 can the annular wing disc-shaped flying craft that can hover of VTOL, it is characterised in that: the hair Motivation is turbofan, including the second outer cylinder, the second shaft, fan, compressor, the second combustion chamber, the second turbine, Jet pipe, second outer cylinder have main duct and by-pass air duct, which passes through for engine core partial air, the by-pass air duct Positioned at the outside of main duct, only fan air passes through；Second outer cylinder is divided into 3 sections from top to bottom, the internal diameter of paragraph 1 by Small gradual change is in bell shape, and the by-pass air duct extends to the 3rd section of end since the 2nd section, and the 2nd section of internal diameter becomes larger, 3rd section of internal diameter gradually becomes smaller；The fan is set in paragraph 1, and compressor is arranged in main duct and leans on positioned at the 2nd section Upper position, it is outer and in the 2nd section of medium position that second combustion chamber is located at the second shaft, and second turbine is located at the 2 sections of upper position, 3 intersegmental part form the jet pipe.

4. according to claim 1 can the annular wing disc-shaped flying craft that can hover of VTOL, it is characterised in that: described to fly Line control unit has integrated computing unit, navigation sensor, wireless data transmission module, engine and steering engine control module external, the hair Motivation and steering engine control module are connected with engine, steering engine respectively.

5. according to claim 4 can the annular wing disc-shaped flying craft that can hover of VTOL, it is characterised in that: described to lead Boat sensor includes inertial navigation, earth magnetism, GPS, ultrasonic wave, laser, barometer, light stream, navigation camera.

6. according to claim 1 can the annular wing disc-shaped flying craft that can hover of VTOL, it is characterised in that: described to fly Line control unit selects Canada Micropilot business to fly control.

7. according to claim 1 can the annular wing disc-shaped flying craft that can hover of VTOL, it is characterised in that: described dynamic Channel on power cabin has four, is provided with 4 engines and forms four power aerial vehicles, on four power aerial vehicles equipped with front and back, Left and right, the gyroscope in upper and lower 3 directions and 3 reference axis are that the acceleration transducer of shaft forms inertial navigation module.