CN105035306B - Jet-propelled wing flap lift-rising connection wing system and its aircraft - Google Patents
Jet-propelled wing flap lift-rising connection wing system and its aircraft Download PDFInfo
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- CN105035306B CN105035306B CN201510499166.7A CN201510499166A CN105035306B CN 105035306 B CN105035306 B CN 105035306B CN 201510499166 A CN201510499166 A CN 201510499166A CN 105035306 B CN105035306 B CN 105035306B
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Abstract
The invention discloses a kind of jet-propelled wing flap lift-risings to connect wing system, including turbofan, wing, hanger, turbine wheel shaft fiaring cone, wing has trailing edge flap, turbine wheel shaft fiaring cone extends a segment length backward, it is provided with more fish scale chip convergent divergent nozzles above, by-pass air duct spout each side there are one restrain disperser by restraining the air-flow that diffusion sheet forms outside outer leading edge and two panels, main duct spout each side there are one restrain disperser by restraining the air-flow that forms of diffusion sheet in interior leading edge and two panels, wing is the connection wing, jet-propelled wing flap lift-rising connection wing systematic vertical can generate upward lift resultant force when rising and falling, when jet-propelled wing flap lift-rising connection wing system level cruising flight, thrust and lift can be generated；The aircraft disclosed by the invention that wing system is connected with jet-propelled wing flap lift-rising can realize vertical rise and fall, the smooth conversion between high-speed flight and vertical rise and fall and high-speed flight.
Description
Technical field
The present invention relates to a kind of jet-propelled externally blown flap high-lift system, more particularly to a kind of jet-propelled wing flap lift-rising connection
Wing system and the aircraft that wing system is connected with this jet-propelled wing flap lift-rising.
Background technology
There are two types of the jet-propelled externally blown flap high-lift systems being currently known, first, jet-propelled top airfoil blown flap lift-rising
System, second is that jet-propelled lower aerofoil blown flap high-lift system.
Jet-propelled top airfoil blown flap high-lift system can make the fluid jet assisted wing top airfoil air-flow of jet engine
Flowing, lift-rising efficiency is higher, but can only make aircraft short range landing, and cruising phase jet engine jet flow is also in wing
Top airfoil progress power-boosting, jet speed is high, washes away caused noise and vibration greatly to wing top airfoil covering；Jet flow temperature
Degree is high, thus serious to wing top airfoil covering and wing structure ablation, and high, another disadvantage is required to covering and wing structure
Jet cutting car flow speed is high when being landing, and noise is big.
Jet-propelled lower aerofoil blown flap high-lift system can make jet engine jet flow pass through the trailing edge slat of wing
Accelerate the flowing of wing top airfoil air-flow, lift-rising efficiency is higher, but can only make aircraft short range landing, and cruising phase is jet-propelled
The high speed jet low coverage of engine flows through wing lower aerofoil, reduces the air pressure of lower aerofoil, reduces lift coefficient, makes machine
Wing cruise efficiency is low；Another disadvantage is that jet cutting car flow speed is high when landing, noise is big.
Invention content
It is an object of the invention to provide a kind of jet-propelled wing flap lift-risings to connect wing system, this jet-propelled wing flap lift-rising connection
Wing system can be carried out efficiently power-boosting, and the aircraft with jet-propelled wing flap lift-rising connection wing system is enable vertically to rise
Fall, and the jet flow of the high temperature and high speed of the jet engine of the wing system of jet-propelled wing flap lift-rising connection at this time can reduce temperature and
Speed makes noise accordingly reduce, and reduce to wing cover wash away and ablation；The jet engine energy when aircraft cruises
Power-boosting is carried out to wing top airfoil, and jet cutting car flow will not be washed away to wing cover generation and ablation；This hair simultaneously
It is bright that a kind of aircraft connecting wing system with this jet-propelled wing flap lift-rising is also disclosed.
The jet-propelled wing flap lift-rising of the present invention connects wing system, including turbofan, wing, connection turbofan hair
The hanger of motivation and wing, turbofan have turbine wheel shaft fiaring cone, wing to have trailing edge flap, and turbine wheel shaft fiaring cone is backward
Extend a segment length, is provided with more fish scale chip convergent divergent nozzles above, the left and right sides of by-pass air duct spout, each there are one needles
Disperser is restrained to the air-flow of by-pass air duct jet flow, at left and right sides of main duct spout, also each there are one be directed to main duct jet flow
Air-flow restrain disperser, when more fish scale chip convergent divergent nozzle angular spreads are opened, for the gas of by-pass air duct jet flow
Stream convergence disperser and for main duct jet flow air-flow convergence disperser also all angular spread open so that turbofan
The inside and outside culvert jet flow of engine is blocked radiation backward by above-mentioned three and is diffused in both up and down, and the left and right sides does not have jet cutting car flow；
When more fish scale chip convergent divergent nozzles are restrained and are closed, restrains disperser for the air-flow of by-pass air duct jet flow and be directed to intension
Also all convergence is closed the air-flow convergence disperser of road jet flow so that the inside and outside jet flow of containing of engine can swimmingly spray backward；
Wing is the connection wing, and the front wing in lower section is dalta wing, and rear wing above is straight RECTANGULAR WINGS, the two by wing tip connecting pin
Face connects, connecting end surface sweepback from top to bottom, and has enough height, so that rear wing is located at after front wing, front wing and rear wing have band
The trailing edge flap of slat；Turbofan is arranged by hanger in front wing top airfoil leading edge, and in the front wing span
Portion position.
When the aircraft for connecting wing system with this jet-propelled wing flap lift-rising needs vertical rise and fall, turbofan opens
Dynamic to start to work, front wing and rear wing all put down the trailing edge flap with slat, more fish scale chip convergent divergent nozzle angular spreads
It opens, is opened for the air-flow of by-pass air duct jet flow convergence disperser all angular spreads at left and right sides of by-pass air duct spout, while intension
For the air-flow of main duct jet flow convergence disperser, also all angular spread is opened at left and right sides of road spout, turbofan
Inside and outside culvert jet flow contact by-pass air duct and main duct spout both sides angle open air-flow convergence disperser when, the left and right sides
Jet flow can be separated by upper and lower diffusion so that inside and outside culvert jet flow mixes and two bursts of jet flows above and below being formed；Then this two strands
Jet flow contact angle spreads the more fish scale chip convergent divergent nozzles opened and spread respectively to be radiated with the back lower place rearwardly and upwardly
It sprays, and all to become width flat for the cross section of jet flow；The lower aerofoil of rear wing can be contacted by spraying to the flat jet flow of width of back upper place, and by
Inclined trailing edge flap blocks water conservancy diversion and is sprayed to the back lower place down, generates the thrust of forward upward, and since slat effect pulls rear wing
The air-flow of top airfoil flows backward, generates lift rearwardly and upwardly；The upper of front wing can be contacted by spraying to the flat jet flow of width of the back lower place
Aerofoil, the air-flow for blowing front wing top airfoil flow backward, generate lift rearwardly and upwardly, and due to Coanda effect along it is lower partially after
Edge wing flap is sprayed to the back lower place, generates the thrust of forward upward；Due to as described above, the spray of turbofan rearwardly and upwardly
Stream is blocked by trailing edge flap inclined under rear wing and flows to the back lower place, at the same jet flow from turbofan to the back lower place due to Condar
Effect trailing edge flap inclined under front wing flows to the back lower place, and both this generates the thrust of forward upward；In addition, turbofan is started
The jet flow of machine rearwardly and upwardly due to slat effect pull rear wing top airfoil air-flow flow backward, while turbofan to
The air-flow that the jet flow of the back lower place blows front wing top airfoil flows backward, and both this generates lift rearwardly and upwardly, setting appropriate
The aforesaid downward angle degree of the trailing edge flap of front wing and rear wing so that the thrust of the former two's forward upward and the latter two lift rearwardly and upwardly
In, power forwardly and rearwardly just offsets each other, and remaining power is exactly the upward lift of jet-propelled wing flap lift-rising connection wing system
With joint efforts；Expand due to the air-flow convergence disperser of the by-pass air duct spout and main duct spout that are opened by angular spread and by angle
The influence of the more fish scale chip convergent divergent nozzles opened is dissipated, turbofan jet flow is divided into flat two strands up and down of width,
It is sprayed rearwardly and upwardly with back lower place stray radiation, the cross section of jet flow can gradually increase, and reduce speed, accordingly reduce and make an uproar
Sound, and in the process, two bursts of jet flows can suck more air around injection, make jet-propelled wing flap lift-rising connection wing system
Upward lift resultant force increases, and due to more air around sucking injection, so that the speed of jet flow is further decreased, make to make an uproar
Sound further declines, while further reduced class session, reduces the ablation to front wing and rear wing；Since turbofan is sent out
Motivation is arranged by hanger in front wing top airfoil leading edge, and positioned at the medium position of the front wing span, simultaneously because rear wing and front wing
Between there is enough vertical separations, and rear wing is located at front wing rear a distance, and above-mentioned effect is fully played；It is flying
When device needs level cruise, the air-flow convergence at left and right sides of the by-pass air duct spout of turbofan for by-pass air duct jet flow is expanded
It is in bulk to set all convergence closures, while all being restrained for the air-flow of main duct jet flow convergence disperser at left and right sides of main duct spout
It is closed, also all convergence is closed more fish scale chip convergent divergent nozzles, and inside and outside culvert jet flow can swimmingly spray backward, and generation pushes away
Power pushes aircraft to advance；Since turbofan is arranged by hanger in front wing top airfoil leading edge, cruise in aircraft
When flight, turbofan jet flow can also carry out power-boosting to front wing top airfoil；Since jet-propelled wing flap lift-rising connects
Wing system is attached using the connection wing, front wing and rear wing using connecting end surface, and this enhance mechanisms, and reduce front wing
With the wing tip vortex of rear wing.
A kind of aircraft connecting wing system with jet-propelled wing flap lift-rising, including fuselage, cockpit, lift fan, tail
The wing, undercarriage, it is characterised in that：The cockpit is located at fuselage middle front part, and jet-propelled wing flap lift-rising connection wing system is two
And the front lower place both sides of cockpit are symmetrically disposed on, the wing root portion of the front wing of two triangles is connected, and the two is made to form one
A entirety, and form a wedge angle in front；Rear wing is connected on fuselage, is similar to midsetwing, wing body connecting portion is in driving
The position of middle part slightly before below cabin；Front wing top airfoil and there is certain distance between belly, is connected with centre therebetween
Support chip, intermediate supports piece section are in aerofoil profile, and leading edge is the extended line of head, and is intersected in two front wings and connects the point to be formed
Angle, rear wing sweepback；It is provided with lift fan in fuselage tail cone；Aircraft is symmetrical.
Aircraft fuselage is streamlined；Cockpit is located at fuselage middle front part, and jet-propelled wing flap lift-rising connection wing system is two
Front lower place both sides that are a and being symmetrically disposed on cockpit, have been arranged between intermediate supports piece, in this way, four form frame knot
Structure, intensity higher can accordingly reduce construction weight；Since two jet-propelled wing flap lift-rising connection wing systems are set to cockpit
Front lower place both sides, in this way when aircraft needs vertical rise and fall, the connection wing system work of jet-propelled wing flap lift-rising, upward liter
Power point of resultant force is located at the position between trailing edge flap inclined under front wing and rear wing, in this way from the aircraft center of gravity at rear compared with
Closely so that the lift fan of trim in fuselage tail cone needs the aircraft weight loaded smaller, and lift fan can be with smaller, gently
A bit, make aircraft deadweight in cruising flight small；And turbofan setting is in Vehicle nose, lift fan setting
In aircraft tail portion, when vertical rise and fall, jet cutting car flow sprays to the back lower place by trailing edge flap water conservancy diversion inclined under front wing and rear wing, resistance
The sundries that only lift fan air-flow is blown afloat is moved to Vehicle nose so that turbofan sucks clean air, right
Engine works and lengthens the life advantageous；The wing body connecting portion of the rear wing position of middle part slightly before below cockpit, blocks turbine wind
Fan engine noise prevents its incoming cockpit so that aircraft is made an uproar in vertical rise and fall and level cruise flight in cockpit
Sound is relatively small；Since turbofan is located at Vehicle nose, the surfaces of revolution of turbine is located in cockpit front-seat driving
Position before the foot of member, lift fan are located at aircraft tail portion, and the back from rear passenger in cockpit is every fuselage
Numerous structures, even if there is revolving part injection, are not easy to cause to hinder to the driver and passenger in cockpit so the two is at work
Evil.
Beneficial effects of the present invention：This jet-propelled wing flap lift-rising connection wing system synthesis is blown outside using top airfoil and lower aerofoil
Gas wing flap lift-rising, lift-rising significant effect；When rising and falling with the aircraft vertical of jet-propelled wing flap lift-rising connection wing system, turbine wind
Fan engine jet flow is sprayed by stray radiation, can be sucked and the more air of injection so that the speed and temperature of jet flow reduce, and make an uproar
Sound reduce, to wing cover wash away and ablation also accordingly reduces, and jet flow thrust increase；Using this jet-propelled wing flap lift-rising
The aircraft of connection wing system can realize vertical rise and fall, high-speed flight.And cruise efficiency is high, and deadweight is small, makes an uproar in cockpit
Sound is smaller, driver and passenger's safety.
Description of the drawings
Fig. 1 is that the jet-propelled wing flap lift-rising of the present invention connects front perspective view of the wing system in level flight condition；
Fig. 2 is that the jet-propelled wing flap lift-rising of the present invention connects front perspective view of the wing system in vertical rise and fall state；
Fig. 3 is that the jet-propelled wing flap lift-rising of the present invention connects rear perspective view of the wing system in level flight condition；
Fig. 4 is that the jet-propelled wing flap lift-rising of the present invention connects rear perspective view of the wing system in vertical rise and fall state；
Fig. 5 is that the jet-propelled wing flap lift-rising of the present invention connects side view cutaway drawing of the wing system in level flight condition；
Fig. 6 is that the jet-propelled wing flap lift-rising of the present invention connects side view cutaway drawing of the wing system in vertical rise and fall state；
Fig. 7 is front perspective view of the aircraft of the present invention in level flight condition；
Fig. 8 is front perspective view of the aircraft of the present invention in vertical rise and fall state.
In figure：1. by-pass air duct casing；2. main duct casing；3. turbine wheel shaft fiaring cone；The convergence diffusion spray of the chip of fish scale more than 4.
Pipe；5. hanger；6. front wing；7. wing flap；8. rear wing；9. wing flap；10. spoiler；11. connecting end surface；12. outer auricle；It is attached outside 13.
Add block；Auricle in 14.；15. the sub- wing；16. the sub- wing；17. turbine wheel shaft；Extra block in 18.；19. diffusion sheet is restrained outside；It is received in 20.
Hold back diffusion sheet；21. outer leading edge；Leading edge in 22.；23. fuselage；24. cockpit；25. intermediate supports piece；26. lift fan cover board；
27. lift fan hatch door；28. stabilization；29. rudder face；30. parachute hatch door；31. luggage compartment door；Undercarriage after 32.；33. master
Undercarriage.
Specific implementation mode
The present invention is described in further detail with reference to the accompanying drawings and examples.
As shown in Fig. 1,2,3,4,5,6,7,8, the jet-propelled wing flap lift-rising connection wing system of the present invention includes turbofan hair
Motivation, wing connect the hanger 5 of turbofan and wing, and turbofan has turbine wheel shaft fiaring cone 3, wing
There are trailing edge flap, turbine wheel shaft fiaring cone 3 to extend a segment length backward, is provided with more fish scale chip convergent divergent nozzles 4 above, outside
The left and right sides of duct spout, each air-flow there are one for by-pass air duct jet flow restrain disperser, in main duct spout or so
Both sides, also each there are one the air-flows for being directed to main duct jet flow to restrain disperser, in more 4 angles of fish scale chip convergent divergent nozzle
When diffusion is opened, restrains disperser for the air-flow of by-pass air duct jet flow and restrain disperser for the air-flow of main duct jet flow
Also all angular spread is opened so that the inside and outside culvert jet flow of turbofan is blocked radiation backward by above-mentioned three and is diffused in up and down
Two sides, the left and right sides do not have jet cutting car flow；When more fish scale chip convergent divergent nozzles 4 are restrained and are closed, sprayed for by-pass air duct
The air-flow of stream restrains disperser and also all restrains closure for the air-flow convergence disperser of main duct jet flow so that engine
Inside and outside culvert jet flow can swimmingly spray backward；Wing is the connection wing, and the front wing 6 in lower section is dalta wing, rear wing 8 above
For straight RECTANGULAR WINGS, the two is connected by the connecting end surface 11 of wing tip, the sweepback from top to bottom of connecting end surface 11, and has enough height,
Rear wing 8 is set to be located at after front wing 6, front wing 6 and rear wing 8 have the trailing edge flap with slat；Turbofan passes through hanger 5
It is arranged in 6 top airfoil leading edge of front wing, and positioned at the medium position of 6 span of front wing.
When the aircraft for connecting wing system with this jet-propelled wing flap lift-rising needs vertical rise and fall, turbofan opens
Dynamic to start to work, front wing 6 and rear wing 8 all put down the trailing edge flap with slat, more 4 angular spreads of fish scale chip convergent divergent nozzle
It opens, is opened for the air-flow of by-pass air duct jet flow convergence disperser all angular spreads at left and right sides of by-pass air duct spout, while interior
For the air-flow of main duct jet flow convergence disperser, also all angular spread is opened at left and right sides of duct spout, and turbofan is started
When the air-flow convergence disperser that the inside and outside culvert jet flow contact by-pass air duct of machine and the angle of main duct spout both sides are opened, left and right two
The jet flow of side can be separated by upper and lower diffusion so that inside and outside culvert jet flow mixes and two bursts of jet flows above and below being formed；Then this two
Stock jet flow contact angle diffusion open more fish scale chip convergent divergent nozzles 4 and spread respectively rearwardly and upwardly with back lower place spoke
Penetrate ejection, and all to become width flat for the cross section of jet flow；The lower aerofoil of rear wing 8 can be contacted by spraying to the wide flat jet flow of back upper place,
And water conservancy diversion is blocked by lower inclined trailing edge flap and is sprayed to the back lower place, the thrust of forward upward is generated, and since slat effect pulls
The air-flow of 8 top airfoil of rear wing flows backward, generates lift rearwardly and upwardly；Front wing can be contacted by spraying to the flat jet flow of width of the back lower place
6 top airfoil, the air-flow for blowing 6 top airfoil of front wing flow backward, generate lift rearwardly and upwardly, and since Coanda effect is under
Inclined trailing edge flap is sprayed to the back lower place, generates the thrust of forward upward；Due to as described above, turbofan backward on
The jet flow of side is blocked by trailing edge flap inclined under rear wing 8 and flows to the back lower place, while turbofan is to the jet flow of the back lower place
Since Coanda effect trailing edge flap inclined under front wing 6 flows to the back lower place, both this generates the thrust of forward upward；In addition, whirlpool
The jet flow of wheel Duct-Burning Turbofan rearwardly and upwardly is since slat effect pulls the air-flow of 8 top airfoil of rear wing to flow backward, while turbine
The air-flow that Duct-Burning Turbofan blows 6 top airfoil of front wing to the jet flow of the back lower place flows backward, and both this generates liter rearwardly and upwardly
Power, the aforesaid downward angle degree of the trailing edge flap of setting front wing 6 and rear wing 8 appropriate so that the thrust of the former two's forward upward and rear two
In the lift of person rearwardly and upwardly, power forwardly and rearwardly just offsets each other, and remaining power is exactly jet-propelled wing flap lift-rising connection
The upward lift resultant force of wing system；Since the air-flow of the by-pass air duct spout and main duct spout that are opened by angular spread restrains diffusion
Device and by angular spread open more fish scale chip convergent divergent nozzles 4 influenced, turbofan jet flow is divided
Two strands up and down of Cheng Kuanbian are sprayed with back lower place stray radiation rearwardly and upwardly, and the cross section of jet flow can gradually increase, and reduce speed
Degree, accordingly reduces noise, and in the process, two bursts of jet flows can suck more air around injection, make the jet-propelled flap
Wing lift-rising connects the upward lift resultant force of wing system and increases, and due to more air around sucking injection, makes the speed of jet flow
Degree further decreases, and noise is made further to decline, while further reduced class session, reduces to front wing 6 and rear wing 8
Ablation；Since turbofan is arranged by hanger 5 in 6 top airfoil leading edge of front wing, and positioned at the middle position of 6 span of front wing
It sets, simultaneously because there is enough vertical separations between rear wing 8 and front wing 6, and rear wing 8 is located at 6 rear a distance of front wing, on
Effect is stated fully to be played；When aircraft needs level cruise, at left and right sides of the by-pass air duct spout of turbofan
Closure is all restrained for the air-flow convergence disperser of by-pass air duct jet flow, while being sprayed for main duct at left and right sides of main duct spout
Also all convergence is closed the air-flow convergence disperser of stream, and also all convergence is closed more fish scale chip convergent divergent nozzles 4, inside and outside culvert spray
Stream can swimmingly spray backward, generate thrust, and aircraft is pushed to advance；Since turbofan is arranged by hanger 5
In 6 top airfoil leading edge of front wing, in aircraft cruising flight, turbofan jet flow can also carry out 6 top airfoil of front wing
Power-boosting；Since jet-propelled wing flap lift-rising connection wing system needs to use connecting end surface using the connection wing, front wing 6 and rear wing 8
11 are attached, and this enhance mechanisms, and reduce the wing tip vortex of front wing 6 and rear wing 8.
As shown in Fig. 3,4,5,6, the air-flow of the left and right sides of the by-pass air duct spout restrains disperser, respectively by before outer
Diffusion sheet 19 is restrained outside edge 21 and two panels to form, and outer auricle is provided on by-pass air duct casing corresponding with above-mentioned three position 1
12, it is provided with outer extra block 13 on corresponding main duct casing 2, the main part of outer auricle 12 and outer extra block 13 is all flat
Face shape, and and horizontal line, 12 rest part of outer auricle with by-pass air duct casing 1 is smooth merges, 13 rest part of outer extra block
With main duct casing 2 is smooth merges, to reduce resistance；It is all horizontally disposed that diffusion sheet 19 is restrained outside outer leading edge 21 and two panels, before outer
Edge 21 is fixed between outer auricle 12 and outer extra block 13, before the hinge setting outside that diffusion sheet 19 passes through root is restrained outside two panels
On edge 21, the planar section of outer auricle 12 is close in the outside that diffusion sheet 19 is restrained outside two panels, and the flat of outer extra block 13 is close in inside
Face part makes by-pass air duct spout be separated into two parts up and down；Diffusion sheet 19 is restrained outside two panels to be existed by the hinge of root
It is opened with upper and lower directions angular spread after outer leading edge 21, to spread by-pass air duct jet flow；Also it can be received with upper and lower directions by hinge
Closure is held back, makes to restrain the shape that diffusion sheet 19 forms one section of wing outside outer leading edge 21 and two panels so as to by-pass air duct jet flow resistance
It is small.
The left and right sides that diffusion sheet 19 is located at by-pass air duct spout is restrained outside outer leading edge 21 and two panels, with above-mentioned three position phase
It is provided with outer auricle 12 on corresponding by-pass air duct casing 1, outer extra block 13, external ear are provided on corresponding main duct casing 2
The main part of piece 12 and outer extra block 13 is all planar shaped, and and horizontal line, 12 rest part of outer auricle and by-pass air duct
1 smooth fusion of casing, 13 rest part of outer extra block with main duct casing 2 is smooth merges, to reduce resistance；Outer leading edge 21 and two
It restrains diffusion sheet 19 outside piece to be all horizontally disposed with, outer leading edge 21 is fixed between outer auricle 12 and outer extra block 13, is restrained outside two panels
The planar section of outer auricle 12 is close in the outside of diffusion sheet 19, and inside is close to the planar section of outer extra block 13, by-pass air duct is made to spray
Mouth is separated into two parts up and down, restrain outside the two panels diffusion sheet 19 by the hinge of root in outer leading edge 21 after with upper and lower directions
When angular spread is opened, the jet flow of by-pass air duct spout both sides can be restrained diffusion sheet 19 outside by four and be spread separately with upper and lower directions,
By-pass air duct jet flow is set to be divided into two bursts of jet flows up and down；When two panels restrains diffusion sheet 19 by the hinge of root with upper and lower directions outside
Diffusion sheet 19 is restrained when convergence is closed, outside two panels and outer leading edge 21 constitutes the shape of one section of wing, keeps by-pass air duct jet flow suitable
Channel Group's mistake；Since the planar section fitting of outer 19 outside of convergence diffusion sheet and outer auricle 12 is close, 19 inside of outer convergence diffusion sheet
Close, the convergence diffusion outside four at left and right sides of turbofan by-pass air duct with the planar section fitting of outer extra block 13
When the diffusion of piece 19 is opened, by-pass air duct jet flow will not be revealed between convergence diffusion sheet 19 outside every two panels.
As shown in Fig. 3,4,5,6, the air-flow of the left and right sides of the main duct spout restrains disperser, respectively by before interior
Convergence diffusion sheet 20 forms in edge 22 and two panels, and interior auricle is provided on main duct casing corresponding with above-mentioned three position 2
14, it is provided with interior extra block 18 on corresponding turbine wheel shaft 17, the main part of interior auricle 14 and interior extra block 18 is all plane
Shape, and and horizontal line, 14 rest part of interior auricle with main duct casing 2 is smooth merges, 18 rest part of interior extra block with
17 smooth fusion of turbine wheel shaft, to reduce resistance；Convergence diffusion sheet 20 is all horizontally disposed in interior leading edge 22 and two panels, and interior leading edge 22 is solid
It is scheduled between interior auricle 14 and interior extra block 18, convergence diffusion sheet 20 is arranged by the hinge of root in interior leading edge 22 in two panels
On, the planar section of interior auricle 14 is close in the outside of convergence diffusion sheet 20 in two panels, and the planar portions of interior extra block 18 are close in inside
Point, so that main duct spout is separated into two parts up and down；In two panels convergence diffusion sheet 20 can by the hinge of root inside before
It is opened with upper and lower directions angular spread after edge 22, to spread main duct jet flow；Also it can be closed with upper and lower directions convergence by hinge
It closes, makes the shape of convergence diffusion sheet 20 one section of wing of composition in interior leading edge 22 and two panels so that small to main duct jet flow resistance.
Convergence diffusion sheet 20 is located at the left and right sides of main duct spout in interior leading edge 22 and two panels, with above-mentioned three position phase
It is provided with interior auricle 14 on corresponding main duct casing 2, interior extra block 18, interior auricle 14 are provided on corresponding turbine wheel shaft 17
Main part with interior extra block 18 is all planar shaped, and and horizontal line, 14 rest part of interior auricle and main duct casing 2
Smooth fusion, 18 rest part of interior extra block with turbine wheel shaft 17 is smooth merges, to reduce resistance；Convergence in interior leading edge 22 and two panels
Diffusion sheet 20 is all horizontally disposed, and interior leading edge 22 is fixed between interior auricle 14 and interior extra block 18, and diffusion sheet 20 is restrained in two panels
It is arranged in interior leading edge 22 by the hinge of root, the planar portions of interior auricle 14 are close in the outside of convergence diffusion sheet 20 in two panels
Point, the planar section of interior extra block 18 is close in inside, and main duct spout is made to be separated into two parts up and down；Expand when being restrained in two panels
When discrete piece 20 is opened after interior leading edge 22 with upper and lower directions angular spread by the hinge of root, the jet flow of main duct spout both sides
It can be spread and be separated with upper and lower directions by convergence diffusion sheet 20 in four, main duct jet flow is made to be divided into two bursts of jet flows up and down；When
Convergence diffusion sheet 20 is restrained by the hinge of root with upper and lower directions in two panels when being closed, in two panels convergence diffusion sheet 20 and it is interior before
Edge 22 constitutes the shape of one section of wing, enables main duct jet flow is smooth to flow through；Due to 20 outside of interior convergence diffusion sheet and inner ear
The planar section fitting of piece 14 is close, and the planar section fitting of interior 20 inside of convergence diffusion sheet and interior extra block 18 is close, works as whirlpool
When taking turns convergence diffusion sheet 20 diffusion opening in four at left and right sides of Duct-Burning Turbofan main duct, diffusion sheet 20 is restrained in every two panels
Between will not reveal main duct jet flow.
As shown in Fig. 1,2,3,4,5,6,7,8,5 height of the hanger is relatively low so that restrains diffusion spray in more fish scale chips
In the case that 4 angular spread of pipe will not touch 6 top airfoil of front wing when opening, when the convergence of more fish scale chip convergent divergent nozzles 4 is closed
It closes, turbofan jet flow can carry out power-boosting to 6 top airfoil of front wing.
In the horizontal cruising flight of aircraft, more convergences of fish scale chip convergent divergent nozzle 4 are closed, turbofan
Jet flow sprays backward, and has one section of height distance from 6 top airfoil of front wing, and jet flow is by way of injection surrounding air to front wing 6
Top airfoil carries out power-boosting, in this way, turbofan jet flow would not be washed away to the generation of 6 top airfoil of front wing and ablation.
As shown in Fig. 1,2,3,4,5,6,7,8, the front wing 6 and 8 aspect ratio of rear wing are smaller, and are supercritical airfoil,
The rear of front wing 6 is provided with the rear double slotted flaps being made of the sub- wing 15 and wing flap 7, and the rear of rear wing 7 is provided with by the sub- wing 16
The rear double slotted flaps formed with wing flap 9,8 wingtip of rear wing are provided with spoiler 10.
Since front wing 6 and rear wing 8 are the connection wing, there is enough wing areas, and aircraft is started using turbofan
Machine can reach enough speed, so the aspect ratio of front wing 6 and rear wing 8 can be smaller；Front wing 6 and rear wing 8 use super critical aerofoil
Type, to improve cruising speed；The rear of front wing 6 is provided with the rear double slotted flaps being made of the sub- wing 15 and wing flap 7, rear wing 8
Rear is provided with the rear double slotted flaps being made of the sub- wing 16 and wing flap 9, to improve lift-rising efficiency；Aircraft is in horizontal flight
When, with carrying out roll guidance with the rear double slotted flaps of rear wing 8 being made of the sub- wing 16 and wing flap 9 and spoiler 10.
The invention also discloses a kind of aircraft connecting wing system with this jet-propelled wing flap lift-rising.
As shown in Figure 7,8, aircraft of the present invention, including fuselage 23, cockpit 24, lift fan, empennage, undercarriage, institute
It states cockpit 24 and is located at 23 middle front part of fuselage, jet-propelled wing flap lift-rising connection wing system is two and is symmetrically disposed on cockpit
The wing root portion of 24 front lower place both sides, the front wing 6 of two triangles is connected, and so that the two is formed an entirety, and in front shape
At a wedge angle；Rear wing 8 is connected on fuselage 23, is similar to midsetwing, wing body connecting portion in the lower section of cockpit 24 middle part slightly
Preceding position；6 top airfoil of front wing and there is certain distance between 23 abdomen of fuselage, be connected with intermediate supports piece 25 therebetween,
25 section of intermediate supports piece is in aerofoil profile, and leading edge is the extended line of head, and is intersected in the wedge angle that two connections of front wing 6 are formed, after
Edge sweepback；It is provided with lift fan in 23 tail cone of fuselage；Aircraft is symmetrical.
Aircraft fuselage 23 is streamlined；Cockpit 24 is located at 23 middle front part of fuselage, jet-propelled wing flap lift-rising connection wing system
System is two and is symmetrically disposed on the front lower place both sides of cockpit 24, intermediate supports piece 25 has been arranged between, in this way, four shapes
At frame structure, intensity higher can accordingly reduce construction weight；Due to two jet-propelled wing flap lift-rising connection wing system settings
In the front lower place both sides of cockpit 24, in this way when aircraft needs vertical rise and fall, jet-propelled wing flap lift-rising connects wing system work
Make, upward lift point of resultant force is located at the position between trailing edge flap inclined under front wing 6 and rear wing 8, in this way from rear
Aircraft center of gravity is closer so that the lift fan of trim in 23 tail cone of fuselage needs the aircraft weight loaded smaller, lift
Fan can keep aircraft deadweight in cruising flight small with smaller, lightly；And turbofan is arranged in aircraft head
Portion, lift fan are arranged at aircraft tail portion, vertical rise and fall, and jet cutting car flow is by trailing edge flap inclined under front wing 6 and rear wing 8
Water conservancy diversion sprays to the back lower place, prevents the sundries that lift fan air-flow is blown afloat from being moved to Vehicle nose so that turbofan
Clean air is sucked, work engine and is lengthened the life is advantageous；The wing body connecting portion of rear wing 8 in the lower section of cockpit 24 middle part slightly
Turbofan noise is blocked in preceding position, prevents its incoming cockpit 24 so that aircraft is in vertical rise and fall and level
When cruising flight, noise is relatively small in cockpit 24；Since turbofan is located at Vehicle nose, the rotation of turbine
Face is located at the position before the foot of front-seat driver in cockpit 24, and lift fan is located at aircraft tail portion, from cockpit 24
The back of interior rear passenger, even if there is revolving part injection, is not easy to every numerous structures of fuselage 23 so the two is at work
Driver and passenger in cockpit 24 are damaged.
As shown in Figure 7,8, the lift fan is electronic coaxial lift fan, and being provided at air inlet can be as needed
The lift fan cover board 26 of opening and closing, exhaust ports are provided with the lift fan hatch door that can be opened and closed as needed
27, the duct of lift fan is gradually transitions the square of exhaust outlet from circle, and longitudinal peace is provided in square exhaust outlet
The shutter of dress.
Lift fan is electronic coaxial lift fan, the turbofan on 23 head of fuselage can be used to drive in this way
The electric power that generates of generator, be not necessarily to special engine, simplify structure, and use electric transmission, also easily；Using coaxial
Lift fan not will produce anti-twisted power；When lift fan needs work, after the lift fan cover board 26 being arranged at air inlet
The hinge in portion is axis, is opened to 23 cephalad direction of fuselage, air inlet when in favor of flying before aircraft, meanwhile, exhaust ports setting
Lift fan hatch door 27 also open, enable lift fan work well be vented；The duct of lift fan is from round gradual mistake
The square to exhaust outlet is crossed, shutter longitudinally disposed in exhaust outlet is made to be easy to deflection；Aircraft in vertical rise and fall,
By the deflection of shutter, the yaw control of aircraft can be realized；Four seamed edges of the exhaust outlet of square need
Angle, to reduce resistance when lift fan slip-stream is passed through；After aircraft enters cruising phase, lift fan is stopped,
Lift fan cover board 26 is closed, while lift fan hatch door 27 is also switched off, to reduce resistance.
As shown in Figure 7,8, the empennage is butterfly tail, is arranged in lift fan both sides, respectively by stabilization 28 and rudder
Face 29 forms, butterfly tail sweepback.
Aircraft uses the butterfly tail being made of stabilization 28 and rudder face 29, can meet aircraft pitching and boat
To stability and control under the premise of, reduce weight, reduce resistance.
As shown in Figure 7,8, the undercarriage is tail wheel type landing gear, and rear undercarriage 32 takes in 23 middle and back of fuselage, rises
The front of power fan, main landing gear 33 are taken in front wing 6.
It since aircraft uses vertical rise and fall, is run without sliding, so using tail wheel type landing gear, rear undercarriage 32 is taken in
23 middle and back of fuselage, the front of lift fan, main landing gear 33 are taken in front wing 6, when aircraft is parked in ground, there is small new line
The angle of attack, in this way after undercarriage 32 can reduce weight with shorter.
When aircraft is parked in ground and needs to take off vertically, turbofan, which starts, starts to work, while angular spread
More fish scale chip convergent divergent nozzles 4 on turbine wheel shaft fiaring cone 3 are opened, restrain diffusion sheet outside four of by-pass air duct spout both sides
19 and four of main duct spout both sides in convergence diffusion sheet 20 also angular spread is opened, put down 6 rear of front wing by 15 He of the sub- wing
The rear double slotted flaps that wing flap 7 is constituted, put down the rear double slotted flaps that 8 rear of rear wing is made of the sub- wing 16 and wing flap 9, open simultaneously
Opening lift fan cover board 26 and lift fan hatch door 27, lift fan is started to work, the rudder face 29 of this inclined butterfly tail at present, by
In previous reasons, jet-propelled externally blown flap high-lift system generates upward lift resultant force, since lift fan is started to work,
Trim before and after the lift of the upward lift resultant force of jet-propelled externally blown flap high-lift system and lift fan, and two power are added and surpass
The gravity suffered by aircraft is crossed, aircraft is made slowly to take off vertically；Aircraft is after taking off vertically and rising to certain altitude, suitably
Reduce turbofan and lift fan thrust, aircraft enter floating state；In the process, due to butterfly tail position
In lift fan both sides, and the rudder face of butterfly tail 29 times is partially, and the air-flow of the slip-stream institute injection of lift fan will make butterfly tail
The wing generates lift, this accordingly reduces the load of lift fan.
Aircraft is appropriate to increase turbofan thrust when floating state needs low-speed forward, before appropriate reduction
The aforesaid downward angle degree for the rear double slotted flaps that the wing 6 is made of the sub- wing 15 and wing flap 7, the appropriate rear wing 8 that reduces is by 9 groups of the sub- wing 16 and wing flap
At rear double slotted flaps aforesaid downward angle degree, the jet flow of turbofan more back track sprays, and jet-propelled wing flap increases
It rises the connection forward component of wing system and will be slightly larger than component backward, aircraft is by low-speed forward；Aircraft is needed in floating state
It is appropriate to increase turbofan thrust when wanting ease astern, after appropriate increase front wing 6 is made of the sub- wing 15 and wing flap 7
The aforesaid downward angle degree of edge double slotted flaps, the appropriate aforesaid downward angle for increasing the rear double slotted flaps that rear wing 8 is made of the sub- wing 16 and wing flap 9
Degree, the jet flow of turbofan more turn to lower section and spray, and the component of jet-propelled wing flap lift-rising connection wing system backward will
Slightly larger than forward component, aircraft is by ease astern；Aircraft, such as will be to when floating state needs low speed transverse shifting
Left side transverse shifting, the appropriate turbofan thrust for increasing right side, suitably to increase the jet-propelled wing flap lift-rising on right side
The lift resultant force for connecting wing system, makes aircraft towards left side low-angle roll, and then the appropriate turbofan for reducing right side is started
Machine thrust, the jet-propelled wing flap lift-rising suitably to reduce right side connect the lift resultant force of wing system, at this time the jet-propelled flap of both sides
Wing lift-rising connects the component of wing system to the left by generation, this component makes aircraft transverse shifting to the left；Aircraft will be to
Each component working situation and the above situation are opposite when the movement of right side；Aircraft is appropriate to increase when floating state needs to hover revolution
The thrust of lift fan in big 23 tail portion of fuselage, while into same direction deflection lift fan exhaust outlet longitudinally disposed hundred
Leaf window, since lift fan setting is in 23 tail portion of fuselage, far from aircraft center of gravity, the slip-stream of oblique ejection will make aircraft to phase
Equidirectional hovering revolution；When aircraft needs low-speed forward and yaws, increase turbofan thrust, reduce front wing 6 by
The aforesaid downward angle degree for the rear double slotted flaps that the sub- wing 15 and wing flap 7 form reduces the rear that rear wing 8 is made of the sub- wing 16 and wing flap 9
The aforesaid downward angle degree of double slotted flaps increases 23 tail portion lift fan thrust of fuselage, deflects longitudinally disposed in lift fan exhaust outlet
The method of shutter is applied in combination.
It is appropriate to increase turbofan thrust when aircraft needs switch to horizontal flight from floating state, it fits simultaneously
When the aforesaid downward angle degree for reducing the rear double slotted flaps that front wing 6 is made of the sub- wing 15 and wing flap 7, the appropriate rear wing 8 that reduces is by the sub- wing 16
The jet flow more back track of the aforesaid downward angle degree of the rear double slotted flaps formed with wing flap 9, turbofan sprays, jet
The formula wing flap lift-rising connection forward component of wing system will be slightly larger than component backward, and aircraft will gradually advance；Master is packed up at this time
Undercarriage 33 and rear undercarriage 32；Continue to increase turbofan thrust, while continuing to reduce the rear double slit flap of front wing 6
The aforesaid downward angle degree of the wing continues the aforesaid downward angle degree for reducing the rear double slotted flaps of rear wing 8, and aircraft will continue to fly before accelerating, at this point,
The butterfly tail being made of stabilization 28 and rudder face 29 will gradually increase lift, and gradually generate pitching stability and course-stability
Property, the lift of jet-propelled wing flap lift-rising connection wing system also will gradually increase；Continue to keep this trend, aircraft is made to accelerate to
Level cruise flying speed, the rear double slotted flaps and rear wing 8 for being at this time made of front wing 6 the sub- wing 15 and wing flap 7 are by the sub- wing 16
The rear double slotted flaps formed with wing flap 9 are all packed up, and more fish scale chip convergent divergent nozzles 4 are restrained and are closed, by by-pass air duct
Convergence diffusion sheet 20 in four of diffusion sheet 19 and main duct spout both sides is restrained outside four of spout both sides and also restrains closure, is made
Turbofan jet flow flows to rear, to push aircraft to advance, simultaneously closes off lift fan cover board 26, closes lift wind
Hatch door 27 is fanned, lift fan is stopped, and packs up the rudder face 29 of butterfly tail, and aircraft enters level cruise state of flight, flies
Row device becomes conventional airplane at this time；After aircraft enters level cruise state of flight, suitably reduce turbofan
Thrust, with economically cruising flight；Since the front wing 6 and rear wing 8 of aircraft use supercritical airfoil, after trailing edge flap is packed up,
Center of Pressure is still located on the posterior border position of front wing 6 and rear wing 8, so while butterfly tail wing area is smaller, but still can be with
With the longitudinal trim of front wing 6 and rear wing 8 of aircraft front；Aircraft level flight condition pitching and yaw control by rudder face
29 controls, roll, which is manipulated, to be carried out from the rear double slotted flaps of rear wing 8 being made of the sub- wing 16 and wing flap 9 with spoiler 10..
When aircraft will enter floating state from level flight condition, appropriate reduction turbofan thrust is lower inclined
The rear double slotted flaps that front wing 6 is made of the sub- wing 15 and wing flap 7, under the rear double slit that is made of the sub- wing 16 and wing flap 9 of the wing 8 to the rear
Wing flap, the rudder face 29 of lower inclined butterfly tail, aircraft start gradually to slow down；Angular spread is opened more on turbine wheel shaft fiaring cone 3
Four of fish scale chip convergent divergent nozzle 4, by-pass air duct spout both sides restrain the four of diffusion sheet 19 and main duct spout both sides outside
Convergence diffusion sheet 20 also open by angular spread in piece, and jet-propelled wing flap lift-rising connection wing system starts power-boosting, aircraft after
It is continuous to slow down；Since speed reduces, butterfly tail cannot generate enough lift, open lift fan cover board 26, open lift fan
Hatch door 27, lift fan are started to work to generate thrust；Since speed reduces, jet-propelled wing flap lift-rising connection wing system cannot
Enough lift is generated, it is appropriate to increase turbofan thrust, so that jet-propelled wing flap lift-rising connection wing system is generated and rises enough
Power, aircraft continue to slow down, until entering floating state.
Aircraft needs, from when floating state vertical landing, to put down main landing gear 33 and rear undercarriage 32, suitably reduce whirlpool
Duct-Burning Turbofan thrust is taken turns, the lift of jet-propelled wing flap lift-rising connection wing system is made accordingly to reduce, while corresponding reduction fuselage 23
The thrust of tail portion lift fan, aircraft can be gradually reduced due to suffered gravity more than lift, until main landing gear 33 is with after
Rise and fall 32 bridge joint tread surfaces, and turbofan and lift fan are stopped, more fish scale chips on turbine wheel shaft fiaring cone 3
The convergence of convergent divergent nozzle 4 is closed, and the four of diffusion sheet 19 and main duct spout both sides are restrained outside four of by-pass air duct spout both sides
Also all convergence is closed convergence diffusion sheet 20 in piece, is packed up the rear double slotted flaps that front wing 6 is made of the sub- wing 15 and wing flap 7, is packed up
The rear double slotted flaps that rear wing 8 is made of the sub- wing 16 and wing flap 9 close lift fan cover board 26, close lift fan hatch door 27,
The rudder face 29 of butterfly tail is packed up, aircraft vertical descent terminates.
After being located at the aerodynamic center of front wing 6 and rear wing 8 due to the center of gravity of aircraft, aircraft has static unstability,
So aircraft needs to use fly-by-wire.
4 people can be taken in aircraft cockpit 24, aircraft is household aircraft configurations, suitably can also increase and contract
The shape and power of bug enable aircraft to take less and more personnel, for example can scale up aircraft
Shape and power, make aircraft become business airplane, can also scaled aircraft shape and power, make aircraft at
For individual lift device；After cockpit 24, before butterfly tail, there is parachute compartment, inside have complete machine parachute, there is landing outside
Umbrella hatch door 30, parachute are used for the forced landing of aircraft；Below parachute compartment, there is luggage compartment, there is luggage compartment door 31 outside；Front wing 6
It is interior with wing tank with rear wing 8, fuel oil needed for turbofan can be loaded, is in addition also equipped with oil in fuselage afterbody
Case adjusts aircraft center of gravity jointly with the wing tank with front front wing 6 and rear wing 8.
Aircraft can be changed to military from civilian, or from carrying be changed to loading, can also be changed to unmanned plane and model plane.
Finally illustrate, above example is only to illustrate this programme and unrestricted, although with reference to preferred embodiment pair
The present invention is described in detail, it will be understood by those of ordinary skill in the art that, technical scheme of the present invention can be carried out
Modification or equivalent replacement should all cover the right in the present invention without departing from the objective and range of technical solution of the present invention
In claimed range.
Claims (2)
1. a kind of jet-propelled wing flap lift-rising connects wing system, including turbofan, wing connects turbofan
With the hanger (5) of wing, turbofan has turbine wheel shaft fiaring cone (3), and wing has trailing edge flap, it is characterised in that：Institute
It states turbine wheel shaft fiaring cone (3) and extends a segment length backward, be provided with more fish scale chip convergent divergent nozzles (4), by-pass air duct above
The left and right sides of spout, each air-flow there are one for by-pass air duct jet flow restrain disperser, at left and right sides of main duct spout,
Also each air-flow there are one for main duct jet flow restrains disperser, expands in more fish scale chip convergent divergent nozzle (4) angles
When dissipating opening, restrains disperser for the air-flow of by-pass air duct jet flow and restrain disperser for the air-flow of main duct jet flow
All angular spread is opened so that turbofan is inside and outside to be contained jet flow and blocked radiation backward by above-mentioned three and be diffused in up and down two
Side, the left and right sides does not have jet cutting car flow；When more fish scale chip convergent divergent nozzles (4) are restrained and are closed, sprayed for by-pass air duct
The air-flow of stream restrains disperser and also all restrains closure for the air-flow convergence disperser of main duct jet flow so that engine
Inside and outside culvert jet flow can swimmingly spray backward；Wing be connection the wing, lower section front wing (6) be dalta wing, above after
The wing (8) is straight RECTANGULAR WINGS, and the two is connected by the connecting end surface (11) of wing tip, connecting end surface (11) sweepback from top to bottom, and is had
Height enough, makes rear wing (8) be located at after front wing (6), front wing (6) and rear wing (8) have the trailing edge flap with slat；Turbine wind
Fan engine is arranged by hanger (5) in front wing (6) top airfoil leading edge, and positioned at the medium position of front wing (6) span.
2. jet-propelled wing flap lift-rising according to claim 1 connects wing system, it is characterised in that：The by-pass air duct spout
The air-flow of the left and right sides restrains disperser, and restraining diffusion sheet (19) outside by outer leading edge (21) and two panels respectively forms, and above-mentioned
It is provided with outer auricle (12) on the corresponding by-pass air duct casing (1) in three position, is provided on corresponding main duct casing (2)
The main part of outer extra block (13), outer auricle (12) and outer extra block (13) is all planar shaped, and and horizontal line, external ear
Piece (12) rest part with by-pass air duct casing (1) is smooth merges, outer extra block (13) rest part and main duct casing (2) are smooth
Fusion, to reduce resistance；It is all horizontally disposed that diffusion sheet (19) is restrained outside outer leading edge (21) and two panels, outer leading edge (21) is fixed on outer
Between auricle (12) and outer extra block (13), diffusion sheet (19) is restrained outside two panels and is arranged in outer leading edge (21) by the hinge of root
On, the planar section for being close to outer auricle (12) on the outside of diffusion sheet (19) is restrained outside two panels, outer extra block (13) is close in inside
Planar section makes by-pass air duct spout be separated into two parts up and down；Restraining diffusion sheet (19) outside two panels can be by the hinge of root
Chain is opened after outer leading edge (21) with upper and lower directions angular spread, to spread by-pass air duct jet flow；It also can be by hinge with upper and lower
Direction convergence is closed, and makes to restrain the shape that diffusion sheet (19) forms one section of wing outside outer leading edge (21) and two panels so that externally contain
Road jet flow resistance is small.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510499166.7A CN105035306B (en) | 2015-08-14 | 2015-08-14 | Jet-propelled wing flap lift-rising connection wing system and its aircraft |
| CN201810158254.4A CN108327893A (en) | 2015-08-14 | 2015-08-14 | Jet-propelled wing flap lift-rising connection wing system and its aircraft |
| CN201810158250.6A CN108190006B (en) | 2015-08-14 | 2015-08-14 | Jet flap high lift connection wing system and aircraft thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510499166.7A CN105035306B (en) | 2015-08-14 | 2015-08-14 | Jet-propelled wing flap lift-rising connection wing system and its aircraft |
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| CN201810158250.6A Division CN108190006B (en) | 2015-08-14 | 2015-08-14 | Jet flap high lift connection wing system and aircraft thereof |
| CN201810158254.4A Division CN108327893A (en) | 2015-08-14 | 2015-08-14 | Jet-propelled wing flap lift-rising connection wing system and its aircraft |
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| CN105035306B true CN105035306B (en) | 2018-08-31 |
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| CN201510499166.7A Active CN105035306B (en) | 2015-08-14 | 2015-08-14 | Jet-propelled wing flap lift-rising connection wing system and its aircraft |
| CN201810158250.6A Active CN108190006B (en) | 2015-08-14 | 2015-08-14 | Jet flap high lift connection wing system and aircraft thereof |
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Families Citing this family (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| AU2016338382B2 (en) | 2015-09-02 | 2021-04-01 | Jetoptera, Inc. | Ejector and airfoil configurations |
| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN111727312B (en) | 2017-06-27 | 2023-07-14 | 杰拓普特拉股份有限公司 | Configuration of a vertical take-off and landing system for an aircraft |
| CN108408044A (en) * | 2018-02-10 | 2018-08-17 | 昆明鞘翼科技有限公司 | Utilize the tangential method for realizing aircraft VTOL and flight of blowing of aerofoil |
| CN108275273B (en) * | 2018-03-08 | 2024-04-02 | 东莞理工学院 | Unmanned plane |
| CN109533352A (en) * | 2018-11-07 | 2019-03-29 | 中国航发湖南动力机械研究所 | Aircraft and its engine |
| EP3976470A4 (en) * | 2019-05-29 | 2023-06-21 | Craft Aerospace Technologies, Inc. | A novel aircraft design using tandem wings and a distributed propulsion system |
| CN110588956B (en) * | 2019-10-08 | 2023-03-07 | 江西洪都航空工业集团有限责任公司 | Blowing type rudder effect gain device |
| CN110920862B (en) * | 2019-11-26 | 2022-04-08 | 中国运载火箭技术研究院 | Aircraft and body flap thereof |
| CN111017194B (en) * | 2019-12-24 | 2023-08-04 | 中国航空工业集团公司西安飞机设计研究所 | Power increases wing |
| CN112193403A (en) * | 2020-10-19 | 2021-01-08 | 中南大学 | Short-distance take-off and landing aircraft adopting front-low back-high type double-wing layout |
| CN112193424A (en) * | 2020-10-19 | 2021-01-08 | 中南大学 | External blowing type power lift-increasing system based on unconventional layout |
| CN113291459B (en) * | 2021-07-27 | 2021-11-30 | 中国空气动力研究与发展中心高速空气动力研究所 | Distributed ducted fan high-lift system and application method thereof |
| CN113753221B (en) * | 2021-09-21 | 2023-10-24 | 中国航空工业集团公司西安飞机设计研究所 | Wing lift-increasing system |
| CN113788139B (en) * | 2021-10-26 | 2024-05-24 | 上海磐拓航空科技服务有限公司 | Method for precisely controlling track of aircraft by using multifunctional pneumatic control surface |
| CN117208194B (en) * | 2023-11-09 | 2024-01-09 | 清华大学 | Wing-hair reconfiguration type variant aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2879957A (en) * | 1954-08-02 | 1959-03-31 | Collins Radio Co | Fluid sustained aircraft |
| US2929580A (en) * | 1956-06-18 | 1960-03-22 | Piasecki Aircraft Corp | Aircraft for vertical or short takeoff, and integrated propulsion lifting and propeller slip stream deflecting unit therefor |
| US4365773A (en) * | 1979-04-11 | 1982-12-28 | Julian Wolkovitch | Joined wing aircraft |
| CN101646600A (en) * | 2006-11-30 | 2010-02-10 | 空中客车法国公司 | Aircraft with rear annular tail |
| CN102180258A (en) * | 2011-04-07 | 2011-09-14 | 龙川 | Duct aerofoil system and aerial craft applying duct aerofoil system |
| CN102458988A (en) * | 2009-04-07 | 2012-05-16 | 空中客车西班牙运营有限责任公司 | Aircraft having a lambda-box wing configuration |
| CN103921931A (en) * | 2014-04-28 | 2014-07-16 | 龙川 | Duct wing system and aircraft using same |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2393941B (en) * | 1990-01-26 | 2004-09-29 | Rolls Royce Plc | Vectorable variable area nozzle |
| JPH08301197A (en) * | 1995-05-10 | 1996-11-19 | Mitsubishi Heavy Ind Ltd | Device for reducing resistance of aircraft |
| US6575406B2 (en) * | 2001-01-19 | 2003-06-10 | The Boeing Company | Integrated and/or modular high-speed aircraft |
| US9545993B2 (en) * | 2007-01-12 | 2017-01-17 | John William McGinnis | Aircraft stability and efficient control through induced drag reduction |
| FR2995876B1 (en) * | 2012-07-24 | 2019-05-03 | Rohr, Inc | INTEGRATED VARIABLE SECTION BLOWER ASSEMBLY WITH INTEGRATED PUSH INVERTER |
| CN103234756B (en) * | 2013-04-16 | 2015-09-30 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of large bypass ratio engine net formula distortion device |
| CN104290907B (en) * | 2014-10-15 | 2016-04-13 | 西南科技大学 | Novel hybrid vertical/short take off and landing unmanned vehicle |
-
2015
- 2015-08-14 CN CN201810158254.4A patent/CN108327893A/en not_active Withdrawn
- 2015-08-14 CN CN201510499166.7A patent/CN105035306B/en active Active
- 2015-08-14 CN CN201810158250.6A patent/CN108190006B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2879957A (en) * | 1954-08-02 | 1959-03-31 | Collins Radio Co | Fluid sustained aircraft |
| US2929580A (en) * | 1956-06-18 | 1960-03-22 | Piasecki Aircraft Corp | Aircraft for vertical or short takeoff, and integrated propulsion lifting and propeller slip stream deflecting unit therefor |
| US4365773A (en) * | 1979-04-11 | 1982-12-28 | Julian Wolkovitch | Joined wing aircraft |
| CN101646600A (en) * | 2006-11-30 | 2010-02-10 | 空中客车法国公司 | Aircraft with rear annular tail |
| CN102458988A (en) * | 2009-04-07 | 2012-05-16 | 空中客车西班牙运营有限责任公司 | Aircraft having a lambda-box wing configuration |
| CN102180258A (en) * | 2011-04-07 | 2011-09-14 | 龙川 | Duct aerofoil system and aerial craft applying duct aerofoil system |
| CN103921931A (en) * | 2014-04-28 | 2014-07-16 | 龙川 | Duct wing system and aircraft using same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108190006B (en) | 2023-07-07 |
| CN105035306A (en) | 2015-11-11 |
| CN108190006A (en) | 2018-06-22 |
| CN108327893A (en) | 2018-07-27 |
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