CN109850142A - Novel jet can vertical translation aircraft and new aeropropulsion system - Google Patents

Abstract

The present invention changes the mentality of designing of existing jet-propelled vertical translation aircraft, and appearance uses the streamlined fuselage of the wing body one as devil fish；Using two whirlpool axis aero-engines as core engine to save fuel oil, increase rotary fan the efficiency of air-breathing and pressurized air stream using two；The pressure chamber of engine is made into the load-bearing chassis of aircraft to mitigate the weight of aircraft and fill part using the inner space of aircraft；Engine allows big-flow high-pressure air-flow spirt pressure chamber pressure chamber become each vector nozzle assembly and sprays the buffer of air-flow, as the muffler of abatement fan and engine noise；Let us can be connected to the throughput and jet direction that each vector nozzle sprays around aircraft by open and close and continuously adjusting, and increase the controllability of aircraft.To produce be easy manipulation, can vertical translation aircraft and new aeropropulsion system in shuttle flight among city, all dirigible novel jet of the ordinary people as automobile.

Description

Novel jet can vertical translation aircraft and new aeropropulsion system

Technical field

It is the invention belongs to jet-propelled Convertiplane correlative technology field, in particular to a kind of jet-propelled to be vertically moved up or down Airborne aircraft and new aeropropulsion system.

Background technique

Currently, well known a few money vertical lift airborne aircrafts are all to provide the lift of aircraft using propeller and push away Power, the only deformation of helicopter still maintain that helicopter noise is big, speed is slow, voyage is short, is difficult to the characteristics of manipulating. It is all to use science and technology most advanced in the world, production technology although also occurring the jet-propelled Convertiplane of several moneys now, Manufacture difficulty is very big, and the whole world only has a few science and technology country the most flourishing and has the ability to manufacture at present, not only price It is high, and complexity is manipulated, general public can not bear, not be available and also nowhere buy, and be only limitted to a few developed country Military use, such jet-propelled Convertiplane is clearly present following shortcoming:

(1) jet-propelled Convertiplane currently in use has two sections in the world at present, is Britain's " sparrow hawk formula " and beauty respectively State F-35.Britain's " sparrow hawk formula " and the jet-propelled Convertiplane of U.S. F-35 are all military fighter aircrafts, in order to increase speed and machine Dynamic property, is all made of cylindrical body fuselage and the sweepback wing compared with small area, this results in needing biggish level speed that could produce Raw enough lift, makes aircraft from the state of taking off vertically excessively to regular flight condition, thus in the stage of taking off vertically, it needs Long period uses the augmentor of engine, and the fuel consumption for augmentor of firing an engine wants high decades of times than usual, makes At higher oil consumption and shorten voyage.

(2) F-35 jet-propelled Convertiplane in the U.S. uses the fanjet of small bypass ratio, " the F- that it is used The bypass ratio of 135 " turbofan aero-engines only has 0.3, although the state of taking off vertically can also in the middle part of aircraft to turn rise Power fan component sprays lift of the air-flow as front support aircraft, in a disguised form increases the bypass ratio of engine, but normally flying Under row state, the phenomenon that but causing excessive oil consumption since bypass ratio is too low, substantially reduces the radius of aircraft and big Width increases routine use cost.

(3) there are four nozzles for the jet-propelled Convertiplane installation of Britain " sparrow hawk formula ", are sent out respectively by " flying horse " turbofan aviation The drawing fan rear portion of motivation draw two rotatable nozzles of front end and two of rear end are divided by the jet pipe of engine can Rotate nozzle.Low-temperature airflow after drawing fan is sprayed by two nozzles of front end, the high temperature gas flow that nozzle sprays Then it is divided into two strands of two nozzles by rear end to spray, is provided by the injection direction that four nozzles of rotation change air-flow for aircraft The thrust of lift and flight forward.When aircraft engine change power, aerial flow perturbation, imitate interference etc. factors make When changing at the posture of aircraft, the thrust of four nozzles in front and back will will appear fluctuation, to cause the posture of aircraft It accordingly changes, pilot is difficult to the phenomenon that effectively controlling.It will be by controlling, changing the injection side of engine large flow-rate gas stream To and injection flow, make aircraft be able to maintain steadily in the sky hovering or from the state of taking off vertically smoothly excessively to just Often state of flight is extremely difficult, and This Is England " sparrow hawk formula ", and jet-propelled Convertiplane is difficult to the reason of manipulating.Therefore, Its steerable system is sufficiently complex, and the maneuvering capability and respond requirement to pilot are very high, and this opportunity of combat is not common Opportunity of combat pilot can drive, it is necessary to those pilots the most outstanding are selected, using long-term stringent training ability This jet-propelled Convertiplane is driven, although the requirement to pilot is so stringent, the crash of Britain " sparrow hawk formula " aircraft Ratio is still far higher than common jet plane.Although the front and back nozzle of the jet-propelled Convertiplane of U.S. F-35 designs There is very big difference with Britain " sparrow hawk formula " aircraft, in addition controlling using modern advanced computer control technology to each nozzle assembly System, it is more much better than Britain " sparrow hawk formula " opportunity of combat to the manipulation of attitude of flight vehicle in vertical lift and hovering stage, but due to There is wave in the ununified buffer unit of the air-flow that each nozzle assembly sprays, the thrust of still unavoidable front and back nozzle assembly It is dynamic, thus the situation for causing the posture of aircraft uncontrollable.Therefore, the reaction power system of this two kinds of aircrafts is not appropriate for It jet-propelled is vertically moved up or down among airborne aircraft using what can be driven in the ordinary people as automobile.

(4) Britain " sparrow hawk formula " and the jet-propelled Convertiplane of the U.S. F-35 noise and hair that in flight, fan is generated The huge noise that motivation fuel oil explosive combustion generates all is to be passed directly to outside, is not provided with effective sound arrester, therefore, this Two kinds of reaction power systems are not appropriate for requiring low noise, the jet-propelled of shuttle flight can be vertically moved up or down among city Airborne aircraft uses.

Summary of the invention

The technical problem to be solved by the present invention is to how overcome above-mentioned every defect of existing jet-propelled Convertiplane, An object of the present invention be to provide it is a kind of it is cheap, be easy to manufacture and energy conservation and environmental protection, the ordinary people as automobile Can drive, can the low noise of shuttle flight be jet-propelled is vertically moved up or down airborne aircraft among city.

In order to overcome existing technical deficiency, main technical schemes of the invention are as follows: one kind is jet-propelled to be vertically moved up or down sky Middle aircraft, including devil's fish appearance wing body one streamlined fuselage, left air inlet, left air intake duct, right air inlet, right air inlet Road, intermediate air inlet cover board, intermediate air inlet, intermediate air intake duct, jet-propelled aeropropulsion system, port tailplane, left direction rudder, the right side Empennage, right direction rudder, left elevator, right elevator, tail bone antenna element, rear middle nozzle assembly, rear left nozzle assembly, rear right spray Nozzle assembly, front left nozzle assembly, front right nozzle assembly, nose-gear, rear left undercarriage, rear right landing gear；The left air inlet, The right air inlet and the intermediate air inlet are respectively positioned on the middle section at the top of aircraft, are respectively communicated with the left air intake duct, institute State right air intake duct and the intermediate air intake duct；The left air inlet, the right air inlet are located at the intermediate air inlet epistome two End；The intermediate air intake duct is a cubic space, upper side be the intermediate air inlet, downside area be equal to it is described The area of intermediate air inlet, trailing flank height, width are greater than the diameter of the drawing fan in the jet-propelled aeropropulsion system, Trailing flank is connected the air inlet as drawing fan with drawing fan, and two flank side surfaces are respectively communicated with the left air intake duct, described Right air intake duct；The intermediate air inlet cover board is located above the intermediate air inlet, area is greater than the intermediate air inlet and covers Intermediate air inlet is stated in residence, and the intermediate air-inlet cover postlaminar part connect with body and can upwardly open in the past, exposes lower section The intermediate air inlet；(the novel jet aeropropulsion system has applied for another to the jet-propelled aeropropulsion system Patent of invention: " multicore scheming band after-burner turbofan aeropropulsion system and aircraft ") it include drawing fan, drawing fan Transmission shaft, force(d) (draft) fan, force(d) (draft) fan transmission shaft, uni-drive gear box, reinforcing fuel nozzle, after-burner, clutch, power Transmission shaft, several whirlpool axis aero-engines, engine charge pipeline, engine exhaust conduit, pressure chamber and several vector nozzles Component；Force(d) (draft) fan transmission gear shape in the uni-drive gear box is that cone, centre have a cylindrical space, institute Stating force(d) (draft) fan transmission shaft is also that centre has a cylindrical space and is fixedly connected with the force(d) (draft) fan transmission gear, the increasing Press fan driving shaft mediate cylindrical space diameter be equal to the force(d) (draft) fan transmission gear mediate cylindrical space diameter, Greater than the outer dia of the drawing fan transmission shaft；The drawing fan transmission shaft passes through the hollow force(d) (draft) fan and is driven The cylindrical space of axis, the force(d) (draft) fan transmission gear is also the drawing fan and shape in the uni-drive gear box The drawing fan transmission gear of cone is fixedly connected；Power transmission gear in the uni-drive gear box is also cone Shape, the whirlpool axis aero-engine are connect by the clutch, the power transmission shaft with the power transmission gear；Institute The shaft power for stating the rotation output of whirlpool axis aero-engine drives the force(d) (draft) fan transmission by power transmission gear rotation Gear and the drawing fan transmission gear are counter-rotation, pass through the drawing fan transmission shaft and the force(d) (draft) fan transmission shaft It drives the drawing fan, the force(d) (draft) fan counter-rotation simultaneously, sucks simultaneously pressurized air；The engine charge pipeline connects Lead to the whirlpool axis aero-engine air inlet and the force(d) (draft) fan rear portion, provide for the whirlpool axis aero-engine through described The pressurized high pressure fresh air of force(d) (draft) fan；The engine exhaust conduit is connected to the exhaust outlet of the whirlpool axis aero-engine With the pressure chamber, the high-temp waste gas that the whirlpool axis aeroengine combustor buring is crossed is discharged into the pressure chamber；The reinforcing combustion Oil burner nozzle is fixedly mounted on the uni-drive gear box rear portion, and the after-burner is located at the reinforcing fuel nozzle rear portion and leads to Excess pressure chamber air inlet is connected to pressure chamber fixation；The pressure chamber is mounted on the bottom of aircraft, as aircraft Load-bearing chassis becomes a load-bearing support member of aircraft fuselage；(the vector nozzle assembly is for the vector nozzle assembly Apply for another patent of invention: " novel jet aero-engine vector nozzle and aero-engine ", application number: 201810762795.8) it is mounted on aircraft bottom surrounding, the fixed connection pressure chamber；Vector nozzle assembly includes being located to fly The front left nozzle assembly and the front right nozzle assembly of row device bottom front, the rear left positioned at aircraft bottom rear end Nozzle assembly, the rear right nozzle component, the rear middle nozzle assembly among the rear end of aircraft bottom；Vector nozzle sets Part air-flow rudder face includes the front left nozzle assembly and the front right nozzle assembly for being mounted on aircraft bottom front, position Front left nozzle assembly air-flow rudder above the rear left nozzle assembly of aircraft bottom rear end, the rear right nozzle component Face, front right nozzle assembly air-flow rudder face, rear left nozzle assembly air-flow rudder face, rear right nozzle component air-flow rudder face；The tail bone day Line component is located among the rearmost end of aircraft, the radio station for the antenna connection aircraft being mounted above；The port tailplane, The starboard tailplane is located at two sides of rear end at the top of aircraft, the tail bone antenna element, the left direction rudder, the right direction Rudder is respectively arranged in the middle and upper part part of the port tailplane, the starboard tailplane rear portion, and one end and the port tailplane, the starboard tailplane connect It connects, the other end can swing, to control the left and right heading of aircraft；The left elevator, the right elevator It is separately mounted to the rear end position of two wings of aircraft, one end is connect with wing, and the other end can be swung up and down, to Control the heading up and down of aircraft；The nose-gear is mounted on the front end middle position of aircraft bottom, has motor Driving device with left and right turn and can drive aircraft slowly to move on ground；The rear left undercarriage, the rear lesser Frame is mounted on two side position of rear end of aircraft bottom or so, has a brake device, can be when aircraft is in flat winged state The nose-gear, the rear left undercarriage, the rear right landing gear are taken in fuselage and are covered with undercarriage cover board, and fuselage bottom is made Portion is smoothly integrated, frictional resistance of the air to fuselage in reduction flight course.

Core engine of several civilian whirlpool axis aero-engines as dynamical system is used as a preferred technical solution, Power is provided for aircraft.Since the civilian whirlpool axis aero-engine for providing power for helicopter is cheap, light-weight, performance Stable and power is abundant, it is often more important that civilian whirlpool axis aero-engine is readily available on the market, is little affected by related The limitation of authorities, the present invention have creatively used core engine of the more whirlpool axis aero-engines as dynamical system, institute It states after-burner, the pressure chamber and the vector nozzle assembly and forms the jet-propelled aeropropulsion system, let us is big Amount produces the excellent jet-propelled airborne aircraft that is vertically moved up or down of inexpensive property and is possibly realized.

As a preferred technical solution, by using two to rotary fan to increase air-breathing and charging efficiency, with the whirlpool Axis aero-engine is as core engine to save fuel oil；The more whirlpool axis aero-engines pass through the clutch and the biography Movable tooth roller box is connected, and every whirlpool axis aero-engine can be controlled by the open and close of the clutch in dynamical system Disembark and run, entire dynamical system can be allowed only to run the whirlpool axis aero-engine or the more whirlpool axis Aero-engine is run simultaneously, drives the drawing fan and the force(d) (draft) fan opposite direction rotating by the uni-drive gear box, The large flow-rate gas stream of cryogenic high pressure, then each vector nozzle sets by being connected to the pressure chamber are provided to the pressure chamber Part sprays air-flow to outside and generates thrust, forms ejection aircraft exterior when a set of bypass ratio is more than 20, does not open augmentor The jet-propelled turbofan aeropropulsion system of superelevation bypass ratio of the gas flow temperature lower than 100 degrees Celsius, green energy conservation.

The whirlpool axis aero-engine is sucked fresh by the engine charge pipeline as a preferred technical solution, Air is from two to the pressure-air introduced after rotary fan, pressure is 2.5atm-3atm after being pressurized, therefore the whirlpool axis aviation The power that engine generates will be than being mounted on pure helicopter, the same engine directly from external suction pressure for 1atm air 20% is increased above, just as installing the automobile engine of turbo charging installation additional, the power of generation will be than same engine Increase above 20%.

As a preferred technical solution, since the bypass ratio of the jet-propelled aeropropulsion system is more than 20, does not open reinforcing When device spray aircraft exterior gas flow temperature be lower than 100 degrees Celsius, when starting augmentor, the reinforcing fuel nozzle to High pressure draught spirt great amount of fuel oil in the after-burner allows the high pressure draught for spraying aircraft substantially to heat up, dynamical system The thrust of system output is also significantly increased；Due to low bypass ratio fanjet (such as bypass ratio be 0.3 modern combat aircraft send out Motivation) in the case where not starting augmentor, the gas flow temperature that dynamical system sprays aircraft is about 1000 degrees Celsius, And dynamical system sprays every 100 degrees Celsius of the promotion of gas flow temperature of aircraft, the thrust of dynamical system output also can correspondingly increase Add 7%, in the case where starting augmentor, the gas flow temperature that dynamical system sprays aircraft can be promoted to 1800 degrees Celsius (spraying the gas flow temperature of aircraft with after-burner turbofan aero-engine used in modern combat aircraft is typically all 1800 Degree Celsius), the thrust F1 (adding) of dynamical system output also can be increased to correspondingly:

F (adding)=F+F*0.07* (1800-1000)/100=1.56*F,

Wherein F is the thrust of dynamical system output in the case where not starting augmentor

The gas flow temperature that aircraft exterior is sprayed when not opening augmentor due to the jet-propelled aeropropulsion system is lower than 100 degrees Celsius, in the case where starting augmentor, the gas flow temperature that dynamical system sprays aircraft can be promoted to 1800 and take the photograph The thrust of family name's degree, dynamical system output also can be increased to correspondingly:

F2 (adding)=F+F*0.07* (1800-100)/100=2.19*F

Wherein F is the thrust of dynamical system output in the case where not starting augmentor

If the turbofan aero-engine of a cuff after-burner, bypass ratio is the 0.3 (culvert of modern combat aircraft engine 0.3) road is than being typically all, its thrust is 8 tons under normal circumstances, and in the case where starting augmentor, its thrust will It increases to:

1.56*8=12.48 ton

If also there is a set of jet-propelled aeropropulsion system, its thrust is also 8 tons under normal circumstances, when starting adds In the case where power device, its thrust will be increased to:

2.19*8=17.52 ton

That is, using its maximum take-off weight ratio of the aircraft of the jet-propelled aeropropulsion system using same The aircraft for the small bypass ratio turbofan aero-engine that the modern combat aircraft of thrust uses will be higher by 5 tons.Moreover, because the spray Gas formula aeropropulsion system sprays the gas flow temperature of aircraft exterior lower than 100 degrees Celsius when not opening augmentor, and modern war In the case where not starting augmentor, dynamical system sprays outside aircraft the small bypass ratio turbofan aero-engine that bucket machine uses The gas flow temperature in portion is about 1000 degrees Celsius, the jet-propelled aeropropulsion system in the case where not starting augmentor, The oil consumption rate of same thrust is generated, one of three parts of the small bypass ratio turbofan aero-engine that only modern combat aircraft uses, It can be seen that the huge advantage that the jet-propelled aeropropulsion system superelevation bypass ratio has.

As a preferred technical solution, aircraft vertical go up and down the stage, need that Power System of Flight Vehicle is substantially improved it is defeated When thrust out, augmentor can be started, high pressure draught spirt of the reinforcing fuel nozzle into the after-burner is big Measure fuel oil, allow fuel oil the after-burner, the pressure chamber high pressure draught in burn and high pressure draught enabled substantially to heat up, Again by being mounted on aircraft surrounding, the fixed vector nozzle assembly high speed ejection for being connected to the pressure chamber, at this moment fly The dynamical system of device can provide the thrust of aircraft maximum take-off weight 50%-110%, and aircraft vertical is allowed to go up and down；It is flying Device climbs, boost phase, and augmentor is then not required to enable, and whirlpool axis aero-engine described in multi-section is used only and provides power, relies on The drawing fan, force(d) (draft) fan sucking and pressurized air, then by being mounted on aircraft aft, the fixed connection pressure Outside the rear left nozzle assembly of power chamber, the rear right nozzle component and the rear middle nozzle assembly ejection machine, mentioned for aircraft For the thrust of maximum take-off weight 30% -50%, to reach the effect of saving fuel oil；In aircraft cruising flight phase, It can only use the whirlpool axis aero-engine by the closure of clutch described in control dynamical system and power is provided, then lead to It crosses outside the rear middle nozzle assembly ejection machine for being mounted on aircraft aft, the fixed connection pressure chamber, is provided for aircraft The thrust of maximum take-off weight 10%-30%；Therefore, the jet-propelled aeropropulsion system has wide power output model It encloses.

The load-bearing chassis that the pressure chamber of dynamical system is made into aircraft as a preferred technical solution, is winged to mitigate The weight of row device and fill part utilize aircraft inner space, allow engine sucking, pressurization large flow-rate gas stream spirt fly The pressure chamber of device, then each vector nozzle assembly by being connected on the pressure chamber eject；Pass through this Kind cleverly arranges, and can produce following every benefit:

(1) pressure chamber described in will become the buffer of big-flow high-pressure air-flow, when the engine of aircraft changes function Rate, aerial flow perturbation, imitate interference etc. factors cause sucking dynamical system big-flow high-pressure air-flow fluctuate, it is described Cryogenic high pressure air in pressure chamber will filter out these fluctuation effects of air-flow, allow air-flow can be by being connected to the pressure Each vector nozzle assembly on power chamber equably ejects, to avoid the thrust of each vector nozzle assembly There is transient fluctuation, causes as Britain's " sparrow hawk formula " and the jet-propelled Convertiplane of U.S. F-35, it is each due to aircraft The thrust that a nozzle generates in a short time is uneven and the posture of aircraft is caused to be difficult to the case where manipulating, and let us can lead to The throughput and jet direction for adjusting be connected to that each vector nozzle assembly sprays on the pressure chamber respectively are crossed, more just Just aircraft is simply manipulated.

(2) when starting augmentor, fire in the reinforcing by the great amount of fuel oil in the reinforcing fuel nozzle spirt air-flow It burning and flows into the pressure chamber after primary combustion in room, fuel oil burns away under the environment of high temperature, high pressure and fresh air abundance, Time with air-flow in aircraft interior flow burning will extend, and further release those and have enough time reinforcing not yet The fuel oil energy to burn in combustion chamber, increases the efficiency of fuel burning, to increase the thrust of dynamical system generation；Therefore, The jet-propelled fuel oil work doing efficiency for being vertically moved up or down airborne aircraft with the pressure chamber, it will do not have higher than dynamical system The common jet plane of pressure chamber, increase is jet-propelled to be vertically moved up or down airborne aircraft economy used in everyday, reduces combustion Oil adverse effect caused by environment.

(3) the huge noise that drawing fan described in, the force(d) (draft) fan and engine intermediate fuel oil explosive combustion generate will It is absorbed by cryogenic high pressure air insulated a large amount of in the pressure chamber, energy entrained by these huge noises acts on the pressure In pressure-air in power chamber, the temperature of pressure-air in the pressure chamber is allowed to increase and be converted to thrust, is greatly reduced and passes to The noise of aircraft exterior；Let us is produced low noise, the jet-propelled of shuttle flight can be vertically moved up or down among city Airborne aircraft is possibly realized.

It is installed simultaneously on the pressure chamber due to us as a preferred technical solution, and several close, opens and can It continuously adjusts and sprays throughput, the changeable vector nozzle assembly for spraying airflow direction, let us passes through to each arrow The operation of flow nozzle component controls, and can not only allow aircraft smoothly to take off vertically landing, flight forward, can also aircraft be allowed to exist Hovering and all around slowly movement, greatly strengthen the jet-propelled functionality for being vertically moved up or down airborne aircraft and use Range；Front left nozzle assembly described in aircraft bottom front, the front right nozzle assembly can close, open and continuously adjustable spray Throughput out, the front left nozzle assembly air-flow rudder face, the front right nozzle assembly air-flow rudder face can swing 60 °, thus Change the left and right direction for spraying air-flow；Rear left nozzle assembly described in the rear end of aircraft bottom, the rear right nozzle component not only may be used It closes, unlatching and continuously adjustable spray throughput, the rear left nozzle assembly air-flow rudder face, the rear right nozzle component air-flow Rudder face can also swing 60 °, to change the left and right direction for spraying air-flow；The rear left nozzle assembly, the rear right nozzle Component can also be swung up 15 degree and to 105 degree of lower swing, to change the upper and lower direction for spraying air-flow；When the rear left Nozzle assembly, it is described after right nozzle component when being rotated up 15 ° from horizontal direction, generate forward, down thrust keep aircraft high First flight upwards；When the rear middle nozzle assembly in the middle part of aircraft rear end is closed, the rear left of aircraft bottom rear end Nozzle assembly, the rear right nozzle component rotate down 90 °, cooperate the front left nozzle assembly, the preceding right nozzle of unlatching Component, which generates upwards thrust, makes aircraft vertical go up and down or hover in the sky；The rear left nozzle assembly, the rear right nozzle Component is rotated down less than 90 °, and the front left nozzle assembly of unlatching, the front right nozzle assembly is cooperated to generate upwards, forward Thrust moves aircraft suspension slow forward；Right nozzle component continues to rotate down when the rear left nozzle assembly, described after When greater than 90 ° to 105 °, cooperate the front left nozzle assembly of unlatching, the front right nozzle assembly generate upwards, backward thrust Move aircraft suspension slowly backward；When aircraft bottom rear end the rear left nozzle assembly, it is described after right nozzle component 90 ° are rotated down, the front left nozzle assembly, the front right nozzle assembly, the rear left nozzle assembly, the rear right nozzle group Part is all turned on, and when the air-flow rudder face that they are installed is swung to the right, aircraft suspends slowly toward moving left, when their air-flow Rudder face is swung to the left, and aircraft suspension is slowly past to move right；When close the front left nozzle assembly, the front right nozzle assembly, The rear middle nozzle assembly in the middle part of aircraft rear end, by the rear left nozzle assembly of aircraft bottom rear end, the rear right side When the spout steering horizontal position of nozzle assembly, vector nozzle, which generates forward thrust, makes the horizontal flight forward of aircraft；It can also be with The front left nozzle assembly, the front right nozzle assembly, the rear left nozzle assembly, the rear right nozzle component are closed, and only It is the rear middle nozzle assembly opened in the middle part of aircraft rear end, equally also can produce forward thrust makes aircraft horizontally forward Flight；Therefore the throughput sprayed backward only can be closed, open and be continuously adjusted to the rear middle nozzle assembly in the middle part of aircraft rear end, The upper and lower, left and right direction for spraying air-flow can not be changed, mainly under flat winged cruising condition, provide for aircraft and fly forward Capable thrust.

Each vector nozzle assembly being connected to as a preferred technical solution, with the pressure chamber is mounted on aircraft Surrounding, the loudspeaker that each vector nozzle assembly is in the shape of long trapezoid body and contains multiple nozzles, outer spout is in expanding Shape；The air-flow that is uniform and fluctuating very little that each vector nozzle assembly sprays forms both length and wide ejection air-flow face, From the surrounding of aircraft, support supports aircraft in large area, and aircraft is significantly increased and landing or in the sky hovers rank taking off The stability of section, becomes easy the manipulation of aircraft simply；Let us can control more easily, the appearance of change of flight device State, make it is jet-propelled be vertically moved up or down airborne aircraft and manipulate simple, ordinary people as automobile can all drive.

Devil fish appearance wing body one streamlined fuselage described in (1) has splendid pneumatic as a preferred technical solution, Performance, only taking level speed of the speed more than 100 kilometers just can produce the enough aerial weight of lift support aircraft, It is not required to provide down thrust to aircraft again, can allow aircraft from landing state excessively to flat winged state；When aircraft is suitable Wind flies or can close engine in gliding flight state, has splendid aeroperformance wing body one using aircraft Streamlined fuselage design, can allow aircraft pass through as aerodone the elevator and the rudder manipulation aircraft without Active flight；When the dynamical system of aircraft occur catastrophe failure completely can not in use, can also by the elevator and The rudder manipulates aircraft unpowered flight as aerodone, and aircraft security is allowed to land.

(2) the jet-propelled airborne aircraft appearance that is vertically moved up or down of uses wing body one, aeroperformance pole as devil fish Good streamlined fuselage, in the ascent stage that takes off, it is only necessary to which, as soon as starting augmentor minute, can make its level speed is more than speed per hour 100 kilometers, enough air lifts are generated, make aircraft from takeoff condition excessively to normal state of flight, and stop using Augmentor.And Britain's " sparrow hawk formula " and the jet-propelled Convertiplane of U.S. F-35, in the ascent stage that takes off, level speed must It must at least need to start augmentor three minutes or more, just aircraft can be made excessive from takeoff condition more than 324 kilometers of speed per hour To regular flight condition；The oil consumption rate that aero-engine starts augmentor is about the 30 of regular flight condition oil consumption rate Times, due to it is jet-propelled be vertically moved up or down airborne aircraft flown to from the normal flight stage at least reduces use augmentor two divide More than clock, the fuel oil of saving allows aircraft to fly one hour or more under regular flight condition enough, therefore jet-propelled can vertically rise Drop airborne aircraft appearance is used as combustion can be greatly reduced in the splendid streamlined fuselage of that wing of devil fish body one, aeroperformance The consumption of oil, to increase the radius and routine use economy of aircraft.

The stage is gone up and down in aircraft as a preferred technical solution, the intermediate air inlet cover board is opened backward, and air is logical The left air inlet, the right air inlet and the intermediate air inlet are crossed by the left air intake duct, the right air intake duct and institute Intermediate air intake duct is stated into the novel jet aeropropulsion system, compression of the air Jing Guo dynamical system, combustion heating, from The spout for being mounted on the dynamical system nozzle assembly around aircraft sprays, and provides lift, thrust for aircraft；When the centre Air inlet cover board is opened backward, and large quantity of air is sucked into dynamical system by the intermediate air inlet, it will is generated to aircraft One huge upward suction, to increase the down thrust of dynamical system output；In the aircraft flat winged stage, the centre into Port cover board, which is put down, covers the intermediate air inlet, air by the left air inlet, the right air inlet by it is described it is left into Air flue, the right air intake duct enter the intermediate air intake duct, enter back into the novel jet aeropropulsion system, and air passes through The compression of dynamical system sprays from the spout for the dynamical system nozzle assembly for being mounted on aircraft aft, provides and push away for aircraft Power.In the aircraft downwind stage, the intermediate air inlet cover board is opened backward, can be significantly increased with the wind air-flow to aircraft Thrust；In the aircraft landing station runway stage, the intermediate air inlet cover board is opened backward, and air-flow can be significantly increased to winged The resistance of row device shortens ground run distance when landing.

It as a preferred technical solution, can be by controlling the rear left nozzle assembly, the rear right nozzle component backward The different spray air flows for spraying air-flow, generate different thrust in two side of aircraft aft, to control the left/right rotation of aircraft To；Can by control the rear left nozzle assembly air-flow rudder face, it is described after right nozzle component air-flow rudder face swing, change Become the direction that air-flow sprays, controls the left and right turn of aircraft；Can also by control be mounted on empennage the left direction rudder, The right direction rudder, controls the left and right turn of aircraft；It can be by controlling the rear left nozzle assembly, the rear right nozzle group Part sprays the injection direction up and down of air-flow, controls the heading up and down of aircraft；Wing can also be mounted on by control The left elevator, the right elevator control the heading up and down of aircraft；Can by the closure of the clutch, The connection for controlling the whirlpool axis aero-engine and the uni-drive gear box is provided dynamic using axis aero-engine in whirlpool described in multi-section Power, or when the whirlpool axis aero-engine having breaks down, only use a normal whirlpool axis aviation Engine drives the opposite direction rotating of the drawing fan and the force(d) (draft) fan, continues as flying by the uni-drive gear box Device provides power；Therefore, the jet-propelled airborne aircraft that is vertically moved up or down has more set control aircraft or so heading, up and down The component of heading, the management system with multiple redundancy, is significantly increased the handling and safety of aircraft.

The nose-gear has motor drive and transfer as a preferred technical solution, and aircraft is electronic It can slowly move, turn under the driving of machine, change direction of taking off；The rear left undercarriage, the rear right landing gear have brake Device, aircraft airfield runway land when can brake, shorten landing when ground run distance.

The second object of the present invention is to provide a kind of novel jet-propelled aeropropulsion system, above-described jet-propelled It includes the novel jet aeropropulsion system that airborne aircraft, which can be vertically moved up or down,.

Compared to the prior art, the present invention has an advantage that

1, the present invention uses devil fish appearance wing body one streamlined fuselage, has splendid aeroperformance, only needs very low Level speed just can produce the enough aerial weight of lift support aircraft, therefore in the ascent stage that takes off, need to only make With the augmentor of very short time, aircraft can be allowed, excessively to flat winged state, the consumption of fuel oil to be greatly reduced from landing state Amount；When aircraft can close engine in downwind state or in the state of gliding, using aircraft with splendid gas The fuselage design of dynamic performance allows aircraft to pass through elevator and rudder manipulation aircraft unpowered flight as aerodone, To increase aircraft radius and economy used in everyday；In the downwind stage, the intermediate air inlet of aircraft Cover board is opened backward, air-flow with the wind can be significantly increased to the thrust of aircraft, in the aircraft landing station runway stage, it is intermediate into Port cover board is opened backward, and air-flow can be significantly increased to the resistance of aircraft, shorten ground run distance when landing；When aircraft Dynamical system occur catastrophe failure completely can not in use, can also by the elevator and the rudder as aerodone that Sample manipulates aircraft unpowered flight, and aircraft security is allowed to land.

2, the present invention creatively uses core engine of the whirlpool the Duo Tai axis aero-engine as dynamical system, due to go straight up to The civilian whirlpool axis aero-engine that machine provides power is cheap, light-weight, performance is stable and power is abundant, and in market On be readily available, be little affected by the limitation of appropriate authorities, excellent jet-propelled of the inexpensive property of let us mass production is vertically moved up or down Airborne aircraft is possibly realized.

3, by the present invention in that use two to rotary fan with increase air-breathing and charging efficiency, using whirlpool axis aero-engine as Core engine is to save fuel oil；The whirlpool Duo Tai axis aero-engine is connected by clutch with uni-drive gear box, and clutch can be passed through Open and close control every whirlpool axis aero-engine disembarking in dynamical system and run, entire dynamical system can be allowed only to transport One whirlpool axis aero-engine of row or the whirlpool Duo Tai axis aero-engine run simultaneously, drive air-breathing wind by uni-drive gear box Fan and force(d) (draft) fan opposite direction rotating provide the large flow-rate gas stream of cryogenic high pressure to pressure chamber, then pass through each of connection pressure chamber Vector nozzle assembly sprays air-flow to outside and generates thrust, forms ejection when a set of bypass ratio is more than 20, does not open augmentor and flies The novel jet turbofan aviation power of superelevation bypass ratio of the gas flow temperature lower than 100 degrees Celsius, green energy conservation outside row device System.

4, the present invention is provided with pressure chamber in dynamical system, and the load-bearing chassis that pressure chamber is made into aircraft is winged to mitigate The weight of row device and fill part utilize aircraft inner space, allow engine sucking, pressurization large flow-rate gas stream spirt fly The pressure chamber of device, then each vector nozzle assembly by being connected on pressure chamber eject；It is cleverly arranged by this, The pressure chamber of dynamical system will become the buffer of big-flow high-pressure air-flow, when the engine of aircraft changes power, aerial Flow perturbation, imitate interference etc. factors cause sucking dynamical system big-flow high-pressure air-flow fluctuate, in pressure chamber Cryogenic high pressure air will filter out these fluctuation effects of air-flow, allow air-flow can be by each arrow for being connected on pressure chamber Flow nozzle component equably ejects, so that the thrust of each vector nozzle assembly be avoided transient fluctuation occur；Add when starting When power device, reinforces the great amount of fuel oil in fuel nozzle spirt air-flow and enters pressure chamber after primary combustion in after-burner, It burns away under the environment of high temperature, high pressure and fresh air abundance, fuel oil is as air-flow is in aircraft interior flow burning Time will extend, and further release those fuel oil energy for being in time for burning in after-burner not yet, increase combustion The efficiency of combustion of oil, to increase the thrust of dynamical system generation；Drawing fan, force(d) (draft) fan and the explosion of engine intermediate fuel oil The huge noise that burning generates will be absorbed by cryogenic high pressure air insulated a large amount of in pressure chamber, entrained by these huge noises Energy act in the pressure-air in pressure chamber, the temperature of pressure-air in pressure chamber allowed to increase and be converted to thrust, greatly Width reduces the noise for passing to aircraft exterior；The present invention installs simultaneously on pressure chamber and several close, opens and can continuously adjust Section sprays throughput, the changeable vector nozzle assembly for spraying airflow direction, and let us passes through the behaviour to each vector nozzle assembly It controls, aircraft can not only be allowed smoothly to take off vertically landing, flight forward, aircraft can also be allowed to hover in the sky and front and back Left and right is slowly mobile, greatly strengthens the jet-propelled functionality for being vertically moved up or down airborne aircraft and use scope.

5, dynamical system of the invention has wide power output range, can provide maximum take-off weight for aircraft The thrust of 10%- 110%；The bypass ratio of dynamical system is more than 20, in the case where not starting augmentor, sprays aircraft External gas flow temperature is lower than 100 degrees Celsius, generates the oil consumption rate of same thrust, the small duct that only modern combat aircraft uses Than one of three parts of turbofan aero-engine；When starting augmentor, high pressure gas of the fuel nozzle into after-burner is reinforced Spirt great amount of fuel oil is flowed, the high pressure draught for spraying aircraft is allowed substantially to heat up, the thrust of dynamical system output is also significantly increased；By Huge advantage possessed by this visible novel jet aeropropulsion system superelevation bypass ratio.

6, the present invention has the management system of multiple redundancy, and the safety and handling of aircraft is significantly increased.

Detailed description of the invention

Fig. 1 is airborne aircraft surface structure aerial view；

Fig. 2 is airborne aircraft surface structure side view；

Fig. 3 is the surface structure aerial view that airborne aircraft opens air inlet cover board；

Fig. 4 is structure of transmission gear box schematic diagram；

Fig. 5 is airborne aircraft surface structure bottom view；

Fig. 6 is novel jet aeropropulsion system appearance three-dimensional figure；

Fig. 7 is novel jet aeropropulsion system structural perspective；

Fig. 8 is novel jet aeropropulsion system structure aerial view；

Fig. 9 is the structural schematic diagram of vector nozzle assembly；

Figure 10 is the rearview of vector nozzle assembly；

Figure 11 is the side view of vector nozzle assembly；

Wherein, 1, devil's fish appearance wing body one streamlined fuselage；2, left air inlet；3, left air intake duct；4, right air inlet； 5, right air intake duct；6, intermediate air inlet cover board；7, intermediate air inlet；8, intermediate air intake duct；9, novel jet aviation power system System；11, port tailplane；12, left direction rudder；13, starboard tailplane；14, right direction rudder；15, left elevator 16, right elevator；20, after Middle nozzle assembly；21, rear left nozzle assembly；22, rear left nozzle assembly air-flow rudder face；23, rear right nozzle component；24, rear right spray Nozzle assembly air-flow rudder face；25, front left nozzle assembly；26, front left nozzle assembly air-flow rudder face；27, front right nozzle assembly；28, preceding Right nozzle component air-flow rudder face；30, tail bone antenna element；31, rear left undercarriage；32, rear right landing gear；33, nose-gear； 40, drawing fan；41, drawing fan transmission shaft；42, force(d) (draft) fan；43, force(d) (draft) fan transmission shaft；44, uni-drive gear box；45, Reinforce fuel nozzle；46, clutch；47, power transmission shaft；48, whirlpool axis aero-engine；49, engine charge pipeline；50, Engine exhaust conduit；51, after-burner；52, pressure chamber air inlet；53, pressure chamber；54, vector nozzle assembly；55, it swears Flow nozzle component air-flow rudder face；56, force(d) (draft) fan transmission gear；57, drawing fan transmission gear；58, power transmission gear；

Specific embodiment

In order to make the objectives, technical solutions, and advantages of the present invention clearer, below in conjunction with drawings and embodiments Invention is further described in detail.It should be appreciated that described herein, specific examples are only used to explain the present invention, not For limiting the present invention.

As shown in Figure 1, Figure 2, shown in Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9, Figure 10, Figure 11:

One kind is jet-propelled to be vertically moved up or down airborne aircraft, including devil's fish appearance wing body one streamlined fuselage 1, Zuo Jin Port 2, left air intake duct 3, right air inlet 4, right air intake duct 5, intermediate air inlet cover board 6, intermediate air inlet 7, intermediate air intake duct 8, Novel jet aeropropulsion system 9, port tailplane 11, left direction rudder 12, starboard tailplane 13, right direction rudder 14, left elevator 15, the right side Elevator 16, rear middle nozzle assembly 20, rear left nozzle assembly 21, rear left nozzle assembly air-flow rudder face 22, rear right nozzle component 23, rear right nozzle component air-flow rudder face 24, front left nozzle assembly 25, front left nozzle assembly air-flow rudder face 26, front right nozzle assembly 27, front right nozzle assembly air-flow rudder face 28, tail bone antenna element 30, rear left undercarriage 31, rear right landing gear 32, nose-gear 33；Left air inlet 2, right air inlet 4 and intermediate air inlet 7 are respectively positioned on the middle section at the top of aircraft, are respectively communicated with left air intake duct 3, right air intake duct 5 and intermediate air intake duct 8；Left air inlet 2, right air inlet 4 are located at intermediate 7 front of air inlet, two end；Intermediate air inlet Road 8 is a cubic space, upper side be intermediate air inlet 7, downside area be equal to the area of intermediate air inlet 7, after Profile height, width are greater than the diameter of the drawing fan 40 in novel jet aeropropulsion system 9, trailing flank and air-breathing wind The air inlet that fan 40 is connected as drawing fan 40, two flank side surfaces are respectively communicated with left air intake duct 3, right air intake duct 5；Intermediate air inlet Velar plate 6 is located at intermediate 7 top of air inlet, area is greater than intermediate air inlet 7 and covers intermediate air inlet 7, intermediate air-inlet cover 6 rear portion of plate connect with body and can upwardly open in the past, exposes the intermediate air inlet 7 of lower section；Novel jet aviation power system (novel jet aeropropulsion system has applied for another patent of invention to system 9: " multicore scheming band after-burner turbofan aviation Dynamical system and aircraft ") it include: drawing fan 40, drawing fan transmission shaft 41, force(d) (draft) fan 42, force(d) (draft) fan transmission shaft 43, uni-drive gear box 44, reinforcing fuel nozzle 45, clutch 46, power transmission shaft 47, several whirlpool axis aero-engines 48, hair Motivation admission line 49, engine exhaust conduit 50, after-burner 51, pressure chamber air inlet 52, pressure chamber 53, several vectors Nozzle assembly 54 and vector nozzle assembly air-flow rudder face 55；56 shape of force(d) (draft) fan transmission gear in uni-drive gear box 44 is round Cone, centre have a cylindrical space, force(d) (draft) fan transmission shaft 43 be also it is intermediate have a cylindrical space and with pressurization wind Fan transmission gear 56 is fixedly connected, and the diameter in 43 mediate cylindrical space of force(d) (draft) fan transmission shaft is equal to force(d) (draft) fan driving cog Take turns the diameter in 56 mediate cylindrical spaces, greater than the outer dia of drawing fan transmission shaft 41；Drawing fan transmission shaft 41 passes through The cylindrical space of hollow force(d) (draft) fan transmission shaft 43, force(d) (draft) fan transmission gear 56, drawing fan 40 and transmission gear Shape in case 44 is also that the drawing fan transmission gear 57 of cone is fixedly connected；Power in uni-drive gear box 44 passes Moving gear 58 is also cone shape, and whirlpool axis aero-engine 48 passes through clutch 46, power transmission shaft 47 and power transmission tooth 58 connection of wheel；The shaft power of the rotation output of whirlpool axis aero-engine 48 drives force(d) (draft) fan to pass by the rotation of power transmission gear 58 Moving gear 56 and drawing fan transmission gear 57 are counter-rotation, pass through drawing fan transmission shaft 41 and force(d) (draft) fan transmission shaft 43 It drives drawing fan 40, force(d) (draft) fan 42 counter-rotation simultaneously, sucks simultaneously compressed air；Engine charge pipeline 49 is connected to whirlpool 42 back space of air inlet and force(d) (draft) fan of axis aero-engine 48 provides for whirlpool axis aero-engine 48 through drawing fan 40 Sucking, the compressed high pressure fresh air of force(d) (draft) fan 42；The row of the connection whirlpool axis aero-engine 48 of engine exhaust conduit 50 Port and pressure chamber 53, in the high-temp waste gas spirt pressure chamber 53 that whirlpool axis aero-engine 48 is discharged；Reinforce fuel nozzle 45 It is fixedly mounted on 44 rear portion of uni-drive gear box, after-burner 51 is located at reinforcing 45 rear portion of fuel nozzle and passes through pressure chamber air inlet Mouth 52 is connected to the fixation of pressure chamber 53；Pressure chamber 53 is mounted on the bottom of aircraft, as the load-bearing chassis of aircraft, becomes winged One load-bearing support member of row device fuselage；Vector nozzle assembly 54 (vector nozzle assembly has applied for another patent of invention: " novel jet aero-engine vector nozzle and aero-engine ", application number: 201810762795.8) is mounted on flight Device bottom surrounding, fixed connection pressure chamber 53；Vector nozzle assembly 54 includes the front left nozzle sets positioned at aircraft bottom front Part 25 and front right nozzle assembly 27, rear left nozzle assembly 21, rear right nozzle component 23 positioned at aircraft bottom rear end are located at and fly Rear middle nozzle assembly 20 among the rear end of row device bottom；Tail bone antenna element 30 is located among the rearmost end of aircraft, is mounted on The radio station of antenna connection aircraft above；Port tailplane 11, starboard tailplane 13 are located at rear end at the top of aircraft, tail bone antenna Two sides of component 30, left direction rudder 12, right direction rudder 14 are respectively arranged in the middle and upper part part of port tailplane 11,13 rear portion of starboard tailplane, One end is connect with port tailplane 11, starboard tailplane 13, and the other end can swing, to control the left and right turn of aircraft；Zuo Sheng Drop rudder 15, right elevator 16 are separately mounted to the rear end position of two wings of aircraft, and one end is connect with wing, the other end It can swing up and down, to control the heading up and down of aircraft；Nose-gear 33 is mounted in the front end of aircraft bottom Between position, have motor driver, with left and right turn and aircraft can be driven slowly to move on ground；Rear left undercarriage 31, rear right landing gear 32 is mounted on two side position of left and right of aircraft wing bottom, has brake device, and aircraft is in flat and flies Nose-gear 33, rear left undercarriage 31, rear right landing gear 32 can be taken in fuselage when state and be covered with undercarriage cover board, made Fuselage bottom is smoothly integrated, frictional resistance of the air to fuselage in reduction flight course.

It is jet-propelled to be vertically moved up or down airborne aircraft the pressure chamber 53 of engine is made into the load-bearing chassis of aircraft to subtract The weight of Airplane Lighter Than Air and the inner space that part utilizes aircraft is filled, makes the novel jet aviation with after-burner 51 dynamic Pressure chamber 53 of the Force system 9 big-flow high-pressure air-flow spirt aircraft；Installing several simultaneously on pressure chamber 53 has tune Section sprays throughput size, can open, close the vector nozzle assembly 54 for spraying air-flow and can changing jet direction up and down, The air-flow in pressure chamber 53 is allowed to spray generation thrust by each relevant vector nozzle assembly 54；It is high that pressure chamber 53 becomes big flow The buffer of pressure gas stream, when aircraft engine change power, aerial flow perturbation, imitate interference etc. factors cause spirt Big-flow high-pressure air-flow in pressure chamber 53 fluctuates, and the considerable low-temperature pressure-air in pressure chamber 53 will filter out gas These fluctuation effects of stream, air-flow can be ejected uniformly across the vector nozzle assembly 54 being connected on pressure chamber 53 Come, so that the thrust of vector nozzle assembly 54 be avoided therefore to fluctuate, causes as Britain " sparrow hawk formula " and U.S. F-35 are jet-propelled The posture of the such aircraft of Convertiplane is difficult to the case where manipulating.Let us can be connected to aircraft pressure by adjusting Each throughput sprayed in relation to vector nozzle assembly 54 and jet direction increase the controllability of aircraft on chamber 53, thus raw Output structure is simple, it is cheap, be easy manipulation, as automobile ordinary people all it is dirigible it is jet-propelled be vertically moved up or down it is aerial Aircraft.

Since the novel jet aeropropulsion system 9 with after-burner 51 flies big-flow high-pressure air-flow spirt The pressure chamber 53 of device, then each vector nozzle assembly 54 by being connected on pressure chamber 53 eject, and air-flow is in aircraft The time of interior flowing will extend.When starting augmentor, the great amount of fuel oil reinforced in 45 spirt air-flow of fuel nozzle is adding After the inner primary combustion in power combustion chamber 51, into pressure chamber 53 after will be after under the environment of high temperature, high pressure and fresh air abundance Afterflame is burnt, and is further released those fuel oil energy for being in time for burning in after-burner 51 not yet, is increased fuel oil Efficiency of combustion increases the thrust of engine simultaneously.Therefore, the jet-propelled combustion for being vertically moved up or down airborne aircraft with pressure chamber Oily service efficiency does not have Britain's " sparrow hawk formula " of pressure chamber and the jet-propelled vertical lift of U.S. F-35 after will being far longer than engine Aircraft further increases the jet-propelled routine use economy for being vertically moved up or down airborne aircraft and reduces fuel oil and causes to environment Adverse effect.

Since the novel jet aeropropulsion system 9 with after-burner 51 flies big-flow high-pressure air-flow spirt The pressure chamber 53 of device, then each vector nozzle assembly 54 by being connected on pressure chamber 53 eject, and drawing fan 40 increases The huge noise for pressing fan 42 and engine intermediate fuel oil explosive combustion to generate will be empty by the inner a large amount of cryogenic high pressure of pressure chamber 53 Gas separate absorption in the pressure-air that energy entrained by these huge noises acts in pressure chamber 53, makes these high pressures empty The temperature of gas increases and is converted to thrust, and the only noise of very little can pass to the outside of aircraft, let us produce low noise, It the civilian jet-propelled airborne aircraft that is vertically moved up or down of shuttle flight can be possibly realized among city.

Due to we on pressure chamber 53 simultaneously install it is several close, open and continuously adjustable spray throughput, can Change the vector nozzle assembly 54 for spraying airflow direction, let us is controlled by the operation to each nozzle assembly, can not only be allowed winged Row device smoothly takes off vertically landing, flight forward, can also allow aircraft to hover in the sky and slowly mobile all around, significantly Enhance the jet-propelled functionality for being vertically moved up or down airborne aircraft and use scope；The front left nozzle sets of aircraft bottom front Part 25, front right nozzle assembly 27 can close, open and continuously adjustable sprays throughput, two side of Raphael's spout of nozzle assembly It is fitted with air-flow rudder face 55, air-flow rudder face 55 can swing 60 °, to change the left and right direction for spraying air-flow；Aircraft The rear left nozzle assembly 21 of bottom rear end, rear right nozzle component 23 can not only close, open and continuously adjustable sprays throughput, Two side of Raphael's spout of nozzle assembly is equally equipped with air-flow rudder face 55, air-flow rudder face 55 can also swing 60 °, to change Become the left and right direction for spraying air-flow；Rear left nozzle assembly 21, rear right nozzle component 23 can also be swung up 15 degree and to the bottoms It is 105 degree dynamic, to change the upper and lower direction for spraying air-flow；When rear left nozzle assembly 21, after right nozzle component 23 from level side To when being rotated up 15 °, generate forward, down thrust make aircraft hold head high to fly upwards；In the middle part of the aircraft rear end after in When nozzle assembly 20 is closed, the rear left nozzle assembly 21 of aircraft bottom rear end, rear right nozzle component 23 rotate down 90 °, match Run the front left nozzle assembly 25 opened jointly, the generation of front right nozzle assembly 27 upwards thrust makes aircraft vertical go up and down or hang in the sky Stop；Rear left nozzle assembly 21, rear right nozzle component 23 rotate down the front left nozzle assembly 25 for cooperating unlatching less than 90 °, front right Nozzle assembly 27, which generates upward, forward thrust, to be made aircraft suspend aerial and moves slow forward；When rear left nozzle assembly 21, after When right nozzle component 23 is continued to rotate down greater than 90 ° to 105 °, cooperate front left nozzle assembly 25, the front right nozzle assembly of unlatching 27, which generate upward, backward thrust, makes aircraft suspend aerial and slowly moves backward；When the front left nozzle assembly of aircraft bottom 25, front right nozzle assembly 27, rear left nozzle assembly 21, rear right nozzle component 23 are all turned on, the air-flow rudder face that they are installed 55 swing to the right, and aircraft suspends in the air and slowly toward moving left, their air-flow rudder face 55 is swung to the left, and aircraft suspends empty In and slowly toward moving right；When closing front left nozzle assembly 25, front right nozzle assembly 27, the after middle nozzle in the middle part of aircraft rear end Component 20, by the rear left nozzle assembly 21 of aircraft bottom rear end, rear right nozzle component 23 spout steering horizontal position when, arrow Flow nozzle, which generates forward thrust, makes the horizontal flight forward of aircraft；Front left nozzle assembly 25, front right nozzle assembly can also be closed 27, rear left nozzle assembly 21, rear right nozzle component 23 only open the rear middle nozzle assembly 20 in the middle part of aircraft rear end, equally Also can produce forward thrust makes the horizontal flight forward of aircraft；Therefore the rear middle nozzle assembly 20 in the middle part of aircraft rear end can only close The throughput sprayed backward is closed, opened and continuously adjusted, not can control the upper and lower, left and right direction for changing and spraying air-flow, it is main If providing the thrust of flight forward under flat winged cruising condition for aircraft.

Each vector nozzle assembly 54 being connected to the pressure chamber 53 is mounted on the surrounding of aircraft, each vector nozzle sets Part 54 is in the shape of long trapezoid body and horn-like in expanding containing multiple nozzles, outer spout；Each vector nozzle assembly 54 sprays Out uniform and the air-flow for fluctuating very little form both long and wide ejection air-flow faces, from the surrounding of aircraft support in large area Aircraft is supported, aircraft is significantly increased in landing or the stability of hovering phase in the sky of taking off, also makes the behaviour of aircraft Control becomes easy simple；Let us can control more easily, the posture of change of flight device, make it is jet-propelled be vertically moved up or down it is aerial Aircraft is easy manipulation as automobile, ordinary people can drive.

The different spray air flows of air-flow can be sprayed backward by control rear left nozzle assembly 21, rear right nozzle component 23, Different thrust is generated in two side of aircraft aft, to control the left and right turn of aircraft；Left nozzle after control can be passed through Component 21, rear right nozzle component 23 air-flow rudder face 55 swing, change the direction that air-flow sprays, control a left side for aircraft Right turn；Can also by control be mounted on the left direction rudder 12 of empennage, right direction rudder 14 swings, control aircraft Left and right turn；The injection direction up and down of air-flow, control can be sprayed by control rear left nozzle assembly 21, rear right nozzle component 23 The heading up and down of aircraft；The left elevator 15 of wing, the upper bottom of right elevator 16 can also be mounted on by control It is dynamic, control the heading up and down of aircraft；Whirlpool axis aero-engine 48 and transmission can be controlled by the closure of clutch 46 The connection of gear-box 44 provides power using multi-section whirlpool axis aero-engine 48, or sends out in the whirlpool axis aero-engine 48 having When raw failure, drawing fan 40 is only driven by uni-drive gear box 44 using a normal whirlpool axis aero-engine 48 With the opposite direction rotating of force(d) (draft) fan 42, continues as aircraft and power is provided.Therefore, jet-propelled to be vertically moved up or down airflight utensil There is the component of more set control aircraft or so heading, upper and lower heading, there is the management system of multiple redundancy, greatly The handling and safety of width increase aircraft.

By using two to rotary fan to increase air-breathing and charging efficiency, using whirlpool axis aero-engine 48 as core engine To save fuel oil；The whirlpool Duo Tai axis aero-engine 48 is connected by clutch 46 with uni-drive gear box 44, and clutch 46 is passed through Open and close control every whirlpool axis aero-engine 48 disembarking in dynamical system and run, can allow entire dynamical system only It runs a whirlpool axis aero-engine 48 or the whirlpool Duo Tai axis aero-engine 48 while running, driven by uni-drive gear box 44 Dynamic 42 opposite direction rotating of drawing fan 40 and force(d) (draft) fan provides the large flow-rate gas stream of cryogenic high pressure to pressure chamber 53, then passes through company Each vector nozzle assembly 54 of logical pressure chamber 53 sprays air-flow to outside and generates thrust, and forming a set of bypass ratio is more than 20, no Superelevation bypass ratio of the gas flow temperature lower than 100 degrees Celsius of aircraft exterior, the jet of green energy conservation are sprayed when opening augmentor Formula turbofan aeropropulsion system.

Novel jet aeropropulsion system 9 by using two to rotary fan air-breathing and pressurization, in addition to because of removal wind The stator of fan can reduce outside the weight of dynamical system and the structure of simplified dynamical system, and the effect of dynamical system can also be substantially improved Rate.The use experience of amp- 70 military transportation airplane of power is provided using co-axial contra rotating propeller according to Russia, using second mate to turning spiral shell Paddle is revolved as power, is provided same thrust ratio using the engine of single propeller and is wanted fuel-efficient 20%-30%.It is some to use second mate The use experience of relative rotation propcopter also indicates that, using the engine driving of same power, revolves using second mate is opposite The helicopter lift of rotating propeller design is 10%-12% higher than using the helicopter of single Design of Propeller.In this set power In system, due to sucking the air-flow of big flow to rotary fan using two and these air-flows be pressurized to 2.5atm- by 1atm 3atm by the pressure chamber 53 to the 51 spirt dynamical system of after-burner after rotary fan, then passes through connection pressure chamber 53 It is sprayed with the vector nozzle assembly 54 for being installed on aircraft surrounding, is converted into the thrust of aircraft, dynamical system can be made to generate Thrust increase 10%-12% or so.

Whirlpool axis aero-engine 48 by the fresh air that engine charge pipeline 49 sucks be from two to rotary fan after The pressure-air that portion introduces, pressure is 2.5atm-3atm after being pressurized, therefore the power that whirlpool axis aero-engine 48 generates will be than peace 20% is increased above mounted in pure helicopter, directly from the same power engine that external suction pressure is 1atm air, just as The automobile engine for installing turbo charging installation additional is such, and the power of generation will increase above 20% than same power engine.

It is mounted on power caused by the whirlpool axis aero-engine of pure helicopter, about 20% will distribute to helicopter Tail rotor use, the centrifugal force that generates when for overcoming helicopter big propeller to rotate maintains the balance of helicopter, makes fuselage The whirlpool axis for not rotating, not playing a role during providing lift for helicopter, but used in our this set dynamical system Power caused by aero-engine 48 then all sucks and is pressurized large flow-rate gas stream, then lead to for driving two to rotary fan Connection pressure chamber 53 is crossed, the vector nozzle assembly 54 for being installed on aircraft surrounding sprays downwards, is converted into the lift of aircraft.Therefore The whirlpool axis aero-engine 48 being mounted in our this set dynamical system is the lift that aircraft can be provided, since we are exquisite Design arrangement, theoretically will than the same power being mounted on pure helicopter whirlpool axis aero-engine increase 30%- 50% or so.

In order to illustrate more clearly of every advanced function of the invention, we are explained in detail with an example: if adopted Domestic 16 aero-engine of whirlpool axis (in the present example, two 16 aviation of the whirlpool axis hairs for being 1500KW with two maximum powers Motivation is mounted on two side of left and right of uni-drive gear box 44, and the up and down direction of tangible uni-drive gear box 44 can also install two again 16 aero-engine of whirlpool axis, whole system can install four 16 aero-engines of whirlpool axis simultaneously, can be navigated by every whirlpool axis The open and close for the clutch 46 that empty engine 48 connects control every whirlpool axis aero-engine 48 disembarking in dynamical system and transport Row, controls entire dynamical system and only runs a whirlpool axis aero-engine 48 or the same luck of the whirlpool Duo Tai axis aero-engine 48 The defeated turnout of row), drawing fan 40 and 42 opposite direction rotating of force(d) (draft) fan are driven by uni-drive gear box 44, they the use of diameter are 1.3 The drawing fan of rice, then each second about can be lower than 100 degrees Celsius, 2.5atm- to 230 kilograms of the offer of pressure chamber 53, temperature 3atm cryogenic high pressure air, then about 8 tons are generated to the external air-flow that sprays by the vector nozzle assembly 54 of connection pressure chamber 53 (for lift in rotary fan component, the diameter of fan is 1.27 meters to thrust, per second in the middle part of the jet-propelled Convertiplane of U.S. F-35 The cold air that 230 kilograms are sprayed under clockwise, generates 9 tons of down thrust).

The U.S. " Apache " armed helicopter maximum take-off weight reaches 10 tons, is equipped with two GE company maximum work outputs The whirlpool the T-700-GE-701C axis aero-engine that rate is 1800 kilowatts；China Wu Zhishi armed helicopter maximum take-off weight 6 Ton, domestic 9 aero-engine of whirlpool axis for being 1200 kilowatts equipped with two peak power outputs.

Although the big propeller of helicopter passes through me because diameter can provide biggish lift often greatly for helicopter Exquisite design arrangement, be mounted on domestic 16 aero-engine of whirlpool axis of two 1500KW above airborne aircraft, be The lift that aircraft can be provided will theoretically increase than being mounted on the whirlpool axis aero-engine of same power on pure helicopter Add 30%-50% or so.Still use two power for 1500KW domestic 16 aero-engine of whirlpool axis drive air-breathing wind Fan and force(d) (draft) fan opposite direction rotating provide the cryogenic high pressure air-flow of big flow to pressure chamber, in the case where not opening augmentor, 8 tons of down thrust is provided for airborne aircraft, the 3000KW power that two 16 aero-engines of whirlpool axis are exported is enough 's.

At this time, the air mass flow for flowing into two whirlpool axis, 16 aeroengine combustor buring room each second is only 10 kilogram (two Axis 16 aero-engine in platform whirlpool generates inspiratory capacity when peak power), then the bypass ratio of entire dynamical system is up to 230/10 =23, it is the jet-propelled aeropropulsion system of current highest bypass ratio in the world.

Entire dynamical system is not in the case where starting augmentor, oil consumption rate about 900 kilograms of (two whirlpool axis ten per hour Six aero-engines generate highest oil consumption rate hourly when maximum power), it is only using small bypass ratio turbofan aero-engine Britain's " sparrow hawk formula " and one of about five parts of the jet-propelled Convertiplane oil consumption rate of U.S. F-35 (due to small bypass ratio turbofan The temperature that aero-engine sprays air-flow when not opening augmentor is about 1000 degrees Celsius, and our this novel jets navigate The temperature that lost motion Force system 9 sprays air-flow when not opening augmentor will but be lower than 100 degrees Celsius, therefore under normal operating conditions Oil consumption rate it is very low), be added significantly to the radius of aircraft and routine use cost be greatly reduced, use civilian whirlpool axis Aero-engine fills part as the advantage of superelevation bypass ratio dynamical system core engine and presents out.

Due to the superelevation bypass ratio of entire dynamical system, 230 kg of air per kg of water evaporated per second by pressure chamber 53 major part absolutely is all It is not to be up to the fresh air that 2.5atm-3atm, temperature are but lower than 100 degrees Celsius by burning, air pressure.If starting reinforcing Device, clockwise after-burner 51 per second sprays about ten kilograms of fuel oils, and (by calculating, 230 kg of air per kg of water evaporated heat up from 100 degrees Celsius To 1800 degrees Celsius, 8 kilograms of aviation kerosines are needed, some unknowable losses is reserved herein, therefore is set as 10 kilograms), then may be used Air themperature by 53 per second 230 kilograms of pressure chamber is promoted to about 1800 degrees Celsius of (turbofan aviations with augmentor It is about 1800 degrees Celsius that the temperature of air-flow is sprayed when engine starts augmentor), the thrust that entire dynamical system generates will More than 17 tons, (by calculating, when the temperature for spraying air-flow is 1800 degrees Celsius, the thrust that entire dynamical system generates is 17.52 ton):

F2 (adding)=F+F*0.07* (1800-100)/100=2.19*F=2.19*8=17.52 tons

It is enough that taking off vertically for 16 tons of aircraft of maximum take-off weight is supported (to pass through and calculate, contained in 230 kg of air per kg of water evaporated Oxygen completely burned, needs 15 kilograms of aviation kerosines, and the heat of generation can be warming up to 230 kg of air per kg of water evaporated from 100 degrees Celsius About 3500 degrees Celsius, dynamical system generate thrust will be more than 19 tons, reserve herein some unknowable losses and Limitation in engineering manufacture to material, technique, therefore only dynamical system is designed as to be warming up to 1800 degree, 17 tons of generation pushes away Power.In fact, the power output of entire dynamical system there are also it is wide can room for promotion).

Since airborne aircraft appearance uses the streamlined fuselage that wing body one, aeroperformance are splendid as devil fish, In ascent stage, level speed is only needed more than 100 kilometers of speed per hour, so that it may be generated enough air lifts, be made aircraft From takeoff condition excessively to normal state of flight, continue to provide down thrust without dynamical system, support aircraft Weight allows aircraft to float in air.The thrust that dynamical system generates, all can provide flight forward for aircraft Power.Therefore aircraft, in the incipient stage taken off vertically, we only need to start augmentor one minute, and it is public to expend about 600 Jin fuel oil, the level speed of aircraft will be more than 100 kilometers of speed per hour, and by takeoff condition excessively to normal state of flight.

And appearance is not the aircraft of that wing body one streamlined fuselage, as Britain's " sparrow hawk formula ", U.S. F-35 are jet-propelled vertical Drop aircraft is gone straight up to, in the stage taken off vertically, level speed needs to reach 324 kilometers of speed per hour, just can produce enough skies Gas lift power makes aircraft from takeoff condition excessively to normal state of flight.Level speed will reach 324 kilometers of speed per hour, start The time of augmentor will extend, and minimum needs 3 minutes or more, the fuel oil of consuming will be more than 1800 kilograms.

Since the appearance of airborne aircraft is using the streamlined fuselage 1 of the wing body one as devil fish, vertically rise every time Fly that therefore the fuel oil more than one ton can be saved, increases the loading capacity of aircraft more than one ton, flight can also be increased The radius of device reduces the consumption of fuel oil, generates good economic benefit.

Aircraft entire voyage exhausted most time all in cruising level flight state, at this time engine only needs to provide The thrust of aircraft gross weight amount about 10% can maintain the cruising level flight state of aircraft；Aircraft in acceleration mode, The thrust that engine needs to provide aircraft gross weight amount about 30% can maintain the acceleration mode of aircraft, and aircarrier aircraft is in machine Field runway, which slides, is in this state when taking off；And aircraft, when taking off vertically state, engine then needs to provide winged The thrust of 105% or more row device total weight can just allow aircraft vertical to take off.Therefore, jet-propelled to be vertically moved up or down airflight Device requires engine to have wide power output range, and all reaction power system can not save in the world at present So wide power output range is provided about in the state of fuel oil, as Britain's " sparrow hawk formula ", the jet-propelled vertical lift of U.S. F-35 Reaction power system used in aircraft, the temperature that it sprays air-flow when maintaining the cruising level flight state of aircraft are about 1000 degrees Celsius, the temperature that air-flow is sprayed when the state of taking off vertically starts augmentor is about 1800 degrees Celsius, oil consumption rate point Be not it is very big, aircraft all in high oil consumption state, substantially reduces the radius and substantially of aircraft in entire voyage Increase routine use cost.And novel jet aeropropulsion system 9 sprays gas when maintaining the cruising level flight state of aircraft The temperature of stream is lower than 100 degrees Celsius, and when the state of taking off vertically starts augmentor, the temperature for spraying air-flow is about 1800 to take the photograph The power output of family name's degree, entire dynamical system haves a wide reach, and oil consumption rate differs greatly.Therefore, oil of the aircraft in entire voyage Loss-rate plays Britain " sparrow hawk formula ", F-35 jet-propelled Convertiplane in the U.S. wants much lower.

Two whirlpool axis aero-engines 48 used by novel jet aeropropulsion system 9 by clutch 46 and pass Movable tooth roller box 44 is connected, then drives 42 opposite direction rotating of drawing fan 40 and force(d) (draft) fan.By the open and close of clutch 46, I Control with can be convenient whirlpool axis aero-engine 48 and uni-drive gear box 44 separation, connection.This design allows for ten thousand One has a whirlpool axis aero-engine 48 to break down, we can separate it and uni-drive gear box 44 by clutch 46 Connection, and only using the opposite of another normal whirlpool axis aero-engine 48 driving drawing fan 40 and force(d) (draft) fan 42 Rotation continues to provide power, increases the safety coefficient of aircraft for aircraft.When aircraft is in cruising level flight state, only A small amount of thrust of aircraft gross weight amount about 10% need to be provided to maintain the cruising level flight state of aircraft, we also can use This function only starts a whirlpool axis aero-engine 48, and another is in shutdown status, to substantially save fuel oil, increases The radius of aircraft.

In the above-mentioned example, navigate if we only start the domestic whirlpool axis 16 that a maximum power is 1500KW Empty engine, it can provide 2 tons to 4 tons of thrust for aircraft, fully meet 16 tons of maximum take-off weight of aircraft and patrol Power demand when the flat winged state of boat, but the oil consumption of aircraft can halve that be down to be about 200 kilogram -400 public per hour Jin.Due to aircraft entire voyage exhausted most time all in cruising level flight state, therefore carrying same weight fuel oil In the case where, the radius of aircraft will only start a wherein core because of with this open and close by clutch Machine provides the unique function of power and doubles, to generate huge economic benefit.The flight that 16 tons of maximum take-off weight If device carries 5 tons of fuel oils, 1 ton therein is kept for aircraft use when taking off vertically, landing, 4 tons of entrained fuel oils Aircraft can be allowed to fly more than ten hour in cruising level flight state, if the speed per hour of aircraft is every as common airliner Hours 900 kilometers, then the radius of aircraft will be considerably beyond 10,000 kilometers, and close to 1.5 ten thousand kilometers.

When 16 tons of maximum take-off weight jet-propelled is vertically moved up or down airborne aircraft standby for takeoff, pass through nose-gear 33 Motor driven and transfer drive aircraft suitably to take off direction to suitable takeoff setting and going to, aircraft top Intermediate air inlet cover board 6 open backward, close aircraft rear end in the middle part of rear middle nozzle assembly 20 and rear left nozzle assembly 21 and rear right nozzle component 23 by horizontal direction go to lower section 90 °；Front left nozzle assembly 25, front right nozzle assembly 27, rear left Nozzle assembly 21 and rear right nozzle component 23 are opened to maximum spout tolerance and start engine, at this time four vector nozzle assemblies 54 Injection air pressure downwards is up to the air-flow that 2.5atm-3atm, temperature are but lower than 100 degrees Celsius simultaneously, is then turned on augmentor, adds The clockwise after-burner 51 per second of power fuel nozzle 45 sprays about ten kilograms of fuel oils, and the downward temperature for spraying air-flow is promoted to greatly About 1800 degrees Celsius, the gross thrust that four vector nozzle assemblies 54 spray is more than 17 tons and fluctuates small and uniform air-flow and form both Long and wide ejection air-flow face, from the surrounding of aircraft, support supports aircraft in large area, by adjusting front left nozzle assembly 25, the ejection throughput of front right nozzle assembly 27, rear left nozzle assembly 21 and rear right nozzle component 23 allows aircraft to be in vertical 30 ° -60 ° of takeoff condition has been held high in rising, prow upwards；When aircraft is 2-3 meters liftoff, at this moment on one side rear left nozzle sets Part 21 and the slow back track of rear right nozzle component 23 slowly reduce front left nozzle assembly 25, front right nozzle assembly 27 on one side Throughput is sprayed, aircraft is allowed to hold head high to fly forward, upwards；After about one minute, when the level speed of aircraft forward flight After 100 kilometers of speed per hour, augmentor is closed, only provides about 8 using two 16 aero-engines of whirlpool axis for aircraft The thrust of ton；Aircraft flies to ideal height, the intermediate air inlet cover board 6 at the top of aircraft is closed, on one side gradually rear Left nozzle component 21 and the slow back track of rear right nozzle component 23 gradually slowly reduce front left nozzle assembly 25, front right on one side The ejection throughput of nozzle assembly 27, and slowly open aircraft rear end in the middle part of rear middle nozzle assembly 20, gradually be turned up after in The ejection throughput of nozzle assembly 20 is to maximum；Until rear left nozzle assembly 21 and the complete back track of rear right nozzle component 23 Horizontal position, front left nozzle assembly 25, front right nozzle assembly 27 ejection throughput completely close.

Aircraft enters after cruising level flight state, can be nose-gear 33, rear left undercarriage 31, rear right landing gear 32 It takes in fuselage and is covered with undercarriage cover board, make fuselage bottom smoothly one, reduce friction of the air to fuselage in flight course Resistance.At this moment power only can be provided with an aero-engine 48 as needed, if being in downwind position, or even is contemplated that and closes Close aero-engine 48, open the intermediate air inlet cover board 6 at the top of aircraft, allow aircraft be in gliding flight with the wind fill state with Save fuel oil.

When aircraft is when destination, power is adjusted to minimum and opens the intermediate air inlet cover board 6 at the top of aircraft, The drag braking flight for increasing air, allows aircraft slowly to decline, then rear left nozzle assembly 21 and rear right nozzle component 23 by Horizontal direction goes to 60 ° -90 ° of lower section, and the rear middle nozzle assembly 20 in the middle part of the slowly closing aircraft rear end of one side is slowly opened on one side Front left nozzle assembly 25, front right nozzle assembly 27, rear left nozzle assembly 21 and rear right nozzle component 23 are opened, under making aircraft slow Drop flies to destination overhead, and nose-gear 33, rear left undercarriage 31, rear right landing gear 32 are put down, then adjusts throttle and fly The posture of row device, allows aircraft slowly to drop to destination；Since airborne aircraft appearance uses the wing body one as devil fish The splendid streamlined fuselage of body, aeroperformance does not need largely to expend fuel oil unlatching augmentor, is winged in landing phases Row device provides huge supporting force, and only relying on air can allow aircraft slowly to drop to purpose the resistance of aircraft itself Ground.

The above content is combine specific optimal technical scheme further detailed description of the invention, and it cannot be said that Specific implementation of the invention is only limited to these instructions.For the professional technician of the technical field of the invention, Under the premise of not departing from present inventive concept, a number of simple deductions or replacements can also be made, should all be considered as belonging to of the invention Protection scope.

Claims (10)

1. a kind of novel jet can vertical translation aircraft, which is characterized in that including devil's fish appearance wing body one streamlined Fuselage, left air inlet, left air intake duct, right air inlet, right air intake duct, intermediate air inlet cover board, intermediate air inlet, intermediate air inlet Road, jet-propelled aeropropulsion system, port tailplane, left direction rudder, starboard tailplane, right direction rudder, left elevator, right elevator, tail bone Antenna element, it is rear in nozzle assembly, rear left nozzle assembly, rear right nozzle component, front left nozzle assembly, front right nozzle assembly, preceding Undercarriage, rear left undercarriage, rear right landing gear；The left air inlet, the right air inlet and the intermediate air inlet are respectively positioned on Middle section at the top of aircraft is respectively communicated with the left air intake duct, the right air intake duct and the intermediate air intake duct；It is described it is left into Port, the right air inlet are located at intermediate two end of air inlet epistome；The intermediate air intake duct is a cubic space, upside Face be the intermediate air inlet, downside area be equal to the intermediate air inlet area, trailing flank height, width are greater than The diameter of drawing fan in the jet-propelled aeropropulsion system, trailing flank is connected with drawing fan as drawing fan Air inlet, two flank side surfaces are respectively communicated with the left air intake duct, the right air intake duct；The intermediate air inlet cover board is located in described Between above air inlet, area be greater than the intermediate air inlet and cover the intermediate air inlet, after the intermediate air inlet cover board Portion connect with body and can upwardly open in the past, exposes the intermediate air inlet of lower section；The jet-propelled aeropropulsion system Including drawing fan, drawing fan transmission shaft, force(d) (draft) fan, force(d) (draft) fan transmission shaft, uni-drive gear box, reinforcing fuel nozzle, After-burner, clutch, power transmission shaft, several whirlpool axis aero-engines, engine charge pipeline, the exhaust pipe of engine Road, pressure chamber and several vector nozzle assemblies；Force(d) (draft) fan transmission gear shape in the uni-drive gear box be cone, There is a cylindrical space in centre, the force(d) (draft) fan transmission shaft be also centre have a cylindrical space and with the force(d) (draft) fan Transmission gear is fixedly connected, and the diameter in the force(d) (draft) fan transmission shaft mediate cylindrical space is equal to the force(d) (draft) fan driving cog Take turns the diameter in mediate cylindrical space, greater than the outer dia of the drawing fan transmission shaft；The drawing fan transmission shaft is worn The cylindrical space for crossing the hollow force(d) (draft) fan transmission shaft, the force(d) (draft) fan transmission gear, the drawing fan with Shape is also that the drawing fan transmission gear of cone is fixedly connected in the uni-drive gear box；In the uni-drive gear box Power transmission gear be also cone shape, the whirlpool axis aero-engine pass through the clutch, the power transmission shaft It is connect with the power transmission gear；The shaft power of the whirlpool axis aero-engine rotation output passes through the power transmission gear Rotation drives the force(d) (draft) fan transmission gear and the drawing fan transmission gear counter-rotation, is passed by the drawing fan Moving axis and the force(d) (draft) fan transmission shaft drive the drawing fan, the force(d) (draft) fan counter-rotation simultaneously, suck and are pressurized Air；The engine charge pipeline be connected to the whirlpool axis aero-engine air inlet and the force(d) (draft) fan rear portion, for institute Whirlpool axis aero-engine is stated to provide through the pressurized high pressure fresh air of the force(d) (draft) fan；The engine exhaust conduit connection The exhaust outlet and the pressure chamber of the whirlpool axis aero-engine, the high-temp waste gas that the whirlpool axis aeroengine combustor buring is crossed are arranged Into in the pressure chamber；The reinforcing fuel nozzle is fixedly mounted on the uni-drive gear box rear portion, the after-burner position It is connected in the reinforcing fuel nozzle rear portion and by pressure chamber air inlet with pressure chamber fixation；The pressure chamber is mounted on The bottom of aircraft becomes a load-bearing support member of aircraft fuselage as the load-bearing chassis of aircraft；The vector spray Nozzle assembly is mounted on aircraft bottom surrounding, the fixed connection pressure chamber；Vector nozzle assembly includes being located at aircraft bottom The front left nozzle assembly and the front right nozzle assembly of front end, the rear left nozzle sets positioned at aircraft bottom rear end Part, the rear right nozzle component, the rear middle nozzle assembly among the rear end of aircraft bottom；Vector nozzle assembly air-flow Rudder face includes the front left nozzle assembly and the front right nozzle assembly for being mounted on aircraft bottom front, is located at flight Front left nozzle assembly air-flow rudder face, front right above the rear left nozzle assembly of device bottom rear end, the rear right nozzle component Nozzle assembly air-flow rudder face, rear left nozzle assembly air-flow rudder face, rear right nozzle component air-flow rudder face；Tail bone antenna element position Among the rearmost end of aircraft, the radio station for the antenna connection aircraft being mounted above；The port tailplane, the right tail The wing is located at two sides of rear end at the top of aircraft, the tail bone antenna element, and the left direction rudder, the right direction rudder are pacified respectively Middle and upper part part loaded on the port tailplane, the starboard tailplane rear portion, one end is connect with the port tailplane, the starboard tailplane, another End can swing, to control the left and right heading of aircraft；The left elevator, the right elevator are installed respectively In the rear end position of two wings of aircraft, one end is connect with wing, and the other end can be swung up and down, to control flight The heading up and down of device；The nose-gear is mounted on the front end middle position of aircraft bottom, has motor driver, With left and right turn and aircraft can be driven slowly to move on ground；The rear left undercarriage, the rear right landing gear are mounted on Two side position of rear end of aircraft bottom or so, has brake device, and aircraft can be described preceding when being in flat winged state It falls frame, the rear left undercarriage, the rear right landing gear and takes in fuselage.

2. novel jet according to claim 1 can vertical translation aircraft, which is characterized in that the jet-propelled aviation Dynamical system flows into institute by the after-burner by the drawing fan, force(d) (draft) fan sucking and pressurized air State in pressure chamber, by be mounted on aircraft bottom surrounding, it is fixed be connected to the pressure chamber it is described after in nozzle assembly, described Rear left nozzle assembly, it is described after right nozzle component, the front left nozzle assembly, be winged outside the front right nozzle assembly ejection machine Row device provides thrust, lift；Aircraft take off vertically, landing phases spray downwards air-flow, provide lift for aircraft, push away Power forms the airflow supports face to have a wide reach in aircraft bottom surrounding；Nozzle during aircraft is rear described in the cruising level flight stage Component, the rear left nozzle assembly, the rear right nozzle component spray air-flow backward, thrust are provided for aircraft, in aircraft Rear portion form the air-flow that haves a wide reach and push face；Each vector nozzle assembly, have adjust spray throughput size or Person opens, closes the function of spraying air-flow.

3. jet-propelled aeropropulsion system according to claim 2, which is characterized in that by using two to rotary fan with Increase air-breathing and charging efficiency, using several civilian whirlpool axis aero-engines as core engine to save fuel oil, by described Uni-drive gear box drives the drawing fan and the force(d) (draft) fan opposite direction rotating, and Xiang Suoshu pressure chamber provides the big of cryogenic high pressure Volume airflow, then each vector nozzle assembly by connecting the pressure chamber spray air-flow to outside and generate thrust, group It is more than 20 at a set of bypass ratio, the spray of the superelevation bypass ratio, green energy conservation of not opening augmentor jet temperature lower than 100 degrees Celsius Gas formula turbofan aeropropulsion system.

4. jet-propelled aeropropulsion system according to claim 2, which is characterized in that engine is big sucking, being pressurized The pressure chamber of volume airflow spirt aircraft, then each vector nozzle assembly by being connected on the pressure chamber It ejects, the pressure chamber sprays the buffer of air-flow as each vector nozzle assembly；The drawing fan, the increasing The huge noise for pressing fan and engine intermediate fuel oil explosive combustion to generate by cryogenic high pressure air a large amount of in the pressure chamber every From absorption, efficient sound arrester of the pressure chamber as dynamical system.

5. jet-propelled aeropropulsion system according to claim 2, which is characterized in that the front left nozzle assembly air-flow rudder Face, the front right nozzle assembly air-flow rudder face, the rear left nozzle assembly air-flow rudder face, the rear right nozzle component air-flow rudder face It can swing 60 °, spray the injection direction of air-flow to the left, to the right to change；The rear left nozzle assembly, the rear right spray Nozzle assembly can rotate upwards 15 ° from level orientation and be rotated down 105 °, so that changing this two nozzle assemblies sprays air-flow Up and down direction；The front left nozzle assembly, the front right nozzle assembly, only can downward jet-stream wind, ejection air-flow can not be changed Up and down direction；In after described nozzle assembly only can jet-stream wind backward, can not change spray air-flow up and down, left and right directions.

6. jet-propelled aeropropulsion system according to claim 2, which is characterized in that aircraft vertical go up and down the stage, When dynamical system being needed to provide the thrust more than aircraft takeoff weight, augmentor can be started, aircraft power is substantially improved The thrust of system output, at this moment dynamical system can provide the thrust of aircraft takeoff weight 50%-110%；It cruises in aircraft Mission phase can be used the whole whirlpool axis aero-engine for being mounted on dynamical system while provide power, can be aircraft The thrust of take-off weight 30%-50% is provided；An institute can also be only used by the closure of clutch described in control dynamical system It states whirlpool axis aero-engine and power is provided, provide the thrust of take-off weight 10%-30% for aircraft.

7. novel jet according to claim 1 can vertical translation aircraft, which is characterized in that the devil fish appearance Wing body one streamlined fuselage has splendid aeroperformance, only very low level speed is needed just to can produce enough lift supports The aerial weight of aircraft allows aircraft from landing state excessively to flat winged state；When aircraft is in downwind state Or engine can be closed in the state of gliding, using aircraft there is the fuselage of splendid aeroperformance to design, allows aircraft Pass through elevator and rudder manipulation aircraft unpowered flight as aerodone；When the dynamical system of aircraft occurs seriously Failure completely can not in use, aircraft unpowered flight can also be manipulated as aerodone by elevator and rudder, Aircraft security is allowed to land.

8. novel jet according to claim 1 can vertical translation aircraft, which is characterized in that risen in aircraft vertical Fly, landing phases, the intermediate air inlet cover board is opened backward, and large quantity of air is sucked into dynamical system by the intermediate air inlet System, it will a huge upward suction is generated to aircraft, to increase the down thrust of dynamical system output；In aircraft Downwind stage, the intermediate air inlet cover board are opened backward, and air-flow can be significantly increased to the thrust of aircraft；In aircraft Landing station runway stage, the intermediate air inlet cover board are opened backward, and air-flow can be significantly increased to the resistance of aircraft, shorten The ground run distance of aircraft when landing.

9. novel jet according to claim 1 can vertical translation aircraft, which is characterized in that control institute can be passed through The different spray air flows for stating rear left nozzle assembly, the rear right nozzle component, generate different thrust in two side of aircraft aft, To control the left and right turn of aircraft；It can be by controlling the rear left nozzle assembly air-flow rudder face, the rear right nozzle group Part air-flow rudder face swings, and controls the left and right turn of aircraft；The left of empennage can also be mounted on by controlling It swings to rudder, the right direction rudder, controls the left and right turn of aircraft；It can be by controlling the rear left nozzle sets Part, the rear right nozzle component spray the injection direction up and down of air-flow, control the heading up and down of aircraft；It can also pass through Swinging up and down for the left elevator, the right elevator for being mounted on wing is controlled, the heading up and down of aircraft is controlled； It, can be by controlling the front left nozzle assembly air-flow rudder face, the front right nozzle assembly gas when aircraft hovers in the sky Stream rudder face, the rear left nozzle assembly air-flow rudder face, it is described after right nozzle component air-flow rudder face swing, make aircraft left It is right slowly mobile；It can also be rotated upwards by controlling the rear left nozzle assembly, the rear right nozzle component from vertical orientations 1 ° -90 ° or 1 ° -15 ° of rotation forward, make aircraft front and back slowly mobile；Institute can be controlled by the closure of the clutch The connection for stating whirlpool axis aero-engine and the uni-drive gear box provides power using axis aero-engine in whirlpool described in multi-section, or Person only uses a normal whirlpool axis aero-engine when whirlpool axis aero-engine having breaks down By the uni-drive gear box, the opposite direction rotating of the drawing fan and the force(d) (draft) fan is driven, aircraft offer is provided Power.

10. a kind of novel jet-propelled aeropropulsion system, which is characterized in that described in any item new including claim 1-9 Type is jet-propelled can vertical translation aircraft.