CN101602403A - Vertical take-off and landing aircraft (VTOL aircraft) - Google Patents
Vertical take-off and landing aircraft (VTOL aircraft) Download PDFInfo
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- CN101602403A CN101602403A CNA2008100585217A CN200810058521A CN101602403A CN 101602403 A CN101602403 A CN 101602403A CN A2008100585217 A CNA2008100585217 A CN A2008100585217A CN 200810058521 A CN200810058521 A CN 200810058521A CN 101602403 A CN101602403 A CN 101602403A
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- 230000005540 biological transmission Effects 0.000 claims abstract description 19
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000007373 indentation Methods 0.000 abstract 1
- 108010066114 cabin-2 Proteins 0.000 description 9
- 230000003042 antagnostic effect Effects 0.000 description 8
- 239000007921 spray Substances 0.000 description 3
- 241001538365 Accipiter nisus Species 0.000 description 2
- 241001504664 Crossocheilus latius Species 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 244000144983 clutch Species 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/30—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a kind of vertical take-off and landing aircraft (VTOL aircraft), aim to provide a kind of simple in structure, be easy to manufacture, can vertical takeoff and landing and can put down at a high speed and fly and needn't additionally significantly increase the vertical take-off and landing aircraft (VTOL aircraft) of aeroengine power, comprise driving compartment, fuselage, aero-engine, wing, tailplane, vertical tail and control system, back is equipped with rotor, the rotor automatic positioning equipment is housed on the rotor, rotor is connected with rotor shaft, rotor shaft and retarder, the rotor shaft retractor device connects, the rotor shaft automatic positioning equipment is housed on the rotor shaft, able to turn on or off rotor cabin is equipped with at the fuselage top, aero-engine is through transmission shaft, power-transfer clutch is connected with retarder, the aero-engine rear portion is equipped with and is turned to the vector jet pipe, open in the rotor cabin during aircraft vertical takeoff and landing, rotor and rotor shaft are stretched out the rotor cabin, in rotor shaft and the rotor indentation rotor cabin, the rotor cabin is closed during flat flying, and main application of the present invention provides a kind of energy vertical takeoff and landing can equal the vertical take-off and landing aircraft (VTOL aircraft) that flies at a high speed again.
Description
Technical field
The invention belongs to a kind of aircraft, more particularly, it relates to a kind of vertical take-off and landing aircraft (VTOL aircraft).
Background technology
Up to the present, vertical take-off and landing aircraft (VTOL aircraft) was successively developed five major types: the mixed configuration formula of tailstock formula, the engine installation formula of verting, thrust deflexion formula, special-purpose lift engine installation formula and above-mentioned back three classes, typical case's representative is as the V-22 tiltrotor of Boeing Co., " sparrow hawk " formula deflection jet pipe mode vertical take-off and landing aircraft (VTOL aircraft) of Britain, the F-35 of american lockheed LMT uses lift fan and band to turn to the short takeoff/vertical landing aircraft of the afterburning turbofan engine of vector spray.Above-mentioned several vertical takeoff and landing, short square take off/the equal place in operation of vertical landing aircraft owing to do not need special airport and runway, make rise aspect its manoevreability in increasing war and the alerting ability effect preferably.But many great shortcomings are also arranged simultaneously, tiltrotor is because rotor diameter is big, speed can only be in 400 kilometers/hour during flat flying, " sparrow hawk " formula deflection jet pipe mode vertical take-off and landing aircraft (VTOL aircraft), owing to will realize vertical takeoff and landing, the take-off weight of aircraft can only be the 83%-85% of engine thrust, this just makes the capacity weight of aircraft be restricted greatly, the fuel load and the voyage of aircraft have been influenced, simultaneously, engine operation was at maximum rating when aircraft took off vertically, consumption of fuel is very big, limited the combat radius of aircraft, and the F-35 of american lockheed LMT development adopts lift fan and is with the short takeoff/vertical landing that turns to vector spray, because lift fan and band turn to the lift deficiency of vector spray generation so that aircraft realization vertical takeoff and landing can only very reluctantlyly change short takeoff/vertical takeoff and landing into, the maneuverability of aircraft is had a greatly reduced quality, be difficult under the engineering factor at present and will significantly increase engine power.
Summary of the invention
The present invention has overcome the deficiencies in the prior art, provide a kind of simple in structure, be easy to manufacture, can vertical takeoff and landing also can equal the vertical take-off and landing aircraft (VTOL aircraft) that flies at a high speed, in order to solve the problems of the technologies described above, the present invention is achieved by the following technical solutions, vertical take-off and landing aircraft (VTOL aircraft) of the present invention comprises driving compartment, fuselage, aero-engine, wing, tailplane, vertical tail and aircraft control system, described vertical take-off and landing aircraft (VTOL aircraft) back is equipped with rotor, the rotor automatic positioning equipment is housed on the rotor, rotor is connected with rotor shaft, rotor shaft and retarder, the rotor shaft retractor device connects, the rotor shaft automatic positioning equipment is housed on the rotor shaft, able to turn on or off rotor cabin is equipped with at the fuselage top, aero-engine is through transmission shaft, power-transfer clutch is connected with retarder, and the aero-engine rear portion is equipped with and is turned to the vector jet pipe.
Described vertical take-off and landing aircraft (VTOL aircraft), the rotor structure of back can be the contrarotation bispin wing, and rotor shaft is the contrarotation rotor shaft.
Described vertical take-off and landing aircraft (VTOL aircraft), retarder can be connected with many aero-engine through corresponding transmission shaft, power-transfer clutch with it, and the auxiliary aviation driving engine is housed on the vertical tail.
Described vertical take-off and landing aircraft (VTOL aircraft) is equipped with propeller before its aero-engine, behind the auxiliary aviation driving engine propeller is housed.
Described vertical take-off and landing aircraft (VTOL aircraft), rotor cabin front and rear portions is equipped with the opposite rotor of hand of rotation and corresponding with it bonded assembly rotor automatic positioning equipment, rotor shaft, retarder, rotor shaft automatic positioning equipment, rotor shaft retractor device, transmission shaft, aero-engine respectively, and vertical tail is installed downwards.
The rotor structure of described vertical take-off and landing aircraft (VTOL aircraft) back is a coaxial double-rotary wing, rotor shaft is the contrarotation rotor shaft, the aero-engine front portion is connected with propeller through power-transfer clutch, transmission shaft, and the rear portion is connected with retarder through power-transfer clutch, transmission shaft, and adjustable rotor fixed link is equipped with at rear portion, fuselage top.
Owing to adopt technique scheme, vertical take-off and landing aircraft (VTOL aircraft) beneficial effect provided by the invention is simple and reliable for structure, the aero-engine service efficiency significantly improves, the lift that rotor produces under equal-wattage during vertical takeoff and landing is the several times of existing other form vertical take-off and landing aircraft (VTOL aircraft) even more than ten times, can realize vertical takeoff and landing easily, during revert to level flight, because in the rotor retraction rotor cabin, make it can be with the same speed normal flight of conventional airplane, must the time flying speed can meet or exceed velocity of sound, and needn't additionally significantly increase aeroengine power.
Description of drawings
Fig. 1 is first embodiment theory structure scheme drawing of the present invention;
Fig. 2 is second embodiment theory structure scheme drawing of the present invention;
Fig. 3 is the 3rd an embodiment theory structure scheme drawing of the present invention;
Fig. 4 is the 4th an embodiment theory structure scheme drawing of the present invention;
Fig. 5 is the 5th an embodiment theory structure scheme drawing of the present invention;
Fig. 6 is the 6th an embodiment theory structure scheme drawing of the present invention.
Among the figure: driving compartment 1 rotor cabin 2 rotor shaft, 3 rotor automatic positioning equipments, 4 rotors, 5 vertical tails, 6 tailplanes 7 turn to vector jet pipe 8 wings 9 aero-engine 10 transmission shafts 11 power-transfer clutchs 12 retarders 13 rotor shaft retractor devices 14 rotor shaft automatic positioning equipments 15 fuselages 16 auxiliary aviation driving engines 17 propeller 18 adjustable rotor fixed links 19 can turn to vertical tail 20
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing.
In Fig. 1, vertical take-off and landing aircraft (VTOL aircraft) is by driving compartment 1, fuselage 16, aero-engine 10, wing 9, tailplane 7, vertical tail 6 and control system constitute, rotor 5 is equipped with on fuselage 16 tops, rotor automatic positioning equipment 4 is housed on the rotor 5, rotor 5 is connected with rotor shaft 3, rotor shaft 3 and retarder 13, rotor shaft retractor device 14 connects, rotor shaft automatic positioning equipment 15 is housed on the rotor shaft 3, able to turn on or off rotor cabin 2 is equipped with at fuselage 16 tops, aero-engine 10 is through transmission shaft 11, power-transfer clutch 12 is connected with retarder 13, and aero-engine 10 rear portions are equipped with and are turned to vector jet pipe 8.The configuration design of aircraft is similar to the conventional airplane design substantially, and be provided with able to turn on or off rotor cabin 2 at the aircraft top, open in rotor cabin 2 during the aircraft vertical takeoff and landing, rotor shaft retractor device 14 stretches out rotor shaft 3 and the rotor 5 that is attached thereto outside the rotor cabin 2, rotor shaft 3 is telescopic spline shaft type drive mechanism among the figure, aero-engine 10 work, through transmission shaft 11, power-transfer clutch 12, retarder 13 drives rotor shaft 3 and rotates with rotor shaft 3 bonded assembly rotors 5, rotor 5 is for to be connected with rotor shaft 3 upper end branch levels symmetric offset spread, the rotary blade of two groups of symmetric offset spread of fork constitutes mutually, between corresponding two rotors rotor automatic positioning equipment 4 is housed, rotor automatic positioning equipment 4 is made of elastomeric element and limiting component, during rotor 5 rotations, because powerful centnifugal force makes 5 one-tenth X-shaped rotations of rotor greater than the convergent force of rotor automatic positioning equipment 4, produce to raising force during rotor 5 rotations, drive the aircraft vertical takeoff and landing, simultaneously aircraft is produced an antagonistic force, this antagonistic force turns to the antagonistic force balance of vector jet pipe 8 to antagonistic force opposite sense and downward jet generation by the control of stone roller spiral shell instrument, aircraft is stablized risen and advance, when aircraft is raised to certain altitude and goes to flat flying, through power-transfer clutch 12 retarder 13 and transmission shaft 11 are disconnected, turn to vector jet pipe 8 back tracks, promote aircraft and quicken flight, after retarder 13 disconnects with transmission shaft 11, rotor 5 stops the rotation, rotor 5 loses centnifugal force, rotor automatic positioning equipment 4 draws rotor 5 in automatically, rotor shaft automatic positioning equipment 15 is made of positioning element and locking member, rotor shaft automatic positioning equipment 15 is fixed on rotor 5 with rotor shaft 3 and draws the parallel position in back and rotor cabin 2 in, open rotor cabin 2 then, rotor shaft retractor device 14 is with rotor shaft 3, rotor 5 shrinks and enters in the rotor cabin 2, rotor cabin 2 is closed, aircraft enters normal putting down and flies state, and rotor shaft retractor device 14 is made of hydraulically extensible member and associated components thereof.
To be loaded on rotor 5 versions on fuselage 16 tops be coaxial double-rotary wing to vertical take-off and landing aircraft (VTOL aircraft) among Fig. 2, rotor shaft 3 is the contrarotation rotor shaft, owing to adopt the contrarotation bispin wing, the antagonistic force that rotor produces is cancelled each other, make steadily vertical takeoff and landing of aircraft, turn to this moment 8 need of vector jet pipe to turn to below and rear to provide auxiliary lifting and forward thrust for aircraft.
Among Fig. 3, retarder 13 can be connected with many aero-engine, aero-engine 10 is connected with power-transfer clutch 12, can turn to auxiliary aviation driving engine 17 is housed on the vertical tail 20, retarder 13 is through cooresponding two pairs of transmission shafts 11, power-transfer clutch 12 connects with two aero-engine 10 of parallel placement, power-transfer clutch 12 is loaded on respectively on two aero-engine 10, its vertical takeoff and landing principle of work is identical with Fig. 1, the antagonistic force that rotor 5 produces is loaded on the direction of the auxiliary aviation driving engine 17 that can turn on the vertical tail 20 with control balance and generation forward thrust by the control of stone roller spiral shell instrument, after aircraft is put down and is flown, adjustment is loaded on auxiliary aviation driving engine 17 spouts that can turn on the vertical tail 20 and produces the thrust second-mission aircraft backward and advance, but handle be loaded on the auxiliary aviation driving engine 17 that can turn on the vertical tail 20 direction also second-mission aircraft turn to.
Among Fig. 4, before 4 aero-engine 10 placed side by side propeller 18 is housed, propeller 18 is housed behind the auxiliary aviation driving engine 17, its vertical takeoff and landing, the flat principle of work that flies are identical with embodiment shown in Figure 3, rotor 5 intersects 6 rotors placing up and down by symmetry and constitutes among the figure, rotor increases rotary blade quantity as need, must increase in pairs, so that can stagger when drawing in mutually.
Among Fig. 5,2 front and back, rotor cabin of vertical take-off and landing aircraft (VTOL aircraft) are equipped with hand of rotation opposite two groups of rotors 5 and cooresponding with it rotor automatic positioning equipment 4 respectively, rotor shaft retractor device 14, retarder 13, transmission shaft 11, power-transfer clutch 12, aero-engine 10, two groups of aero-engine 10 minutes, the front is the aero-engine 10 of two parallel placements for one group, power flies before providing fwd rotor 5 vertical takeoff and landing power to reach, the back is the aero-engine 10 that separate unit is positioned over drive end unit, power flies before providing rotor 5 vertical takeoff and landing power in back to reach, front and back rotor 5 is because hand of rotation is opposite, the antagonistic force that rotor 5 produces before and after making is cancelled each other, thereby can make the steady landing of vertical take-off and landing aircraft (VTOL aircraft), because rotor 5 postposition, vertical tail 6 is installed downwards.
Among Fig. 6, rotor 5 versions that vertical take-off and landing aircraft (VTOL aircraft) is loaded on fuselage 16 tops are coaxial double-rotary wing, and rotor shaft 3 is the contrarotation rotor shaft, owing to adopt the contrarotation bispin wing, the antagonistic force that rotor produces is cancelled each other, and makes steadily vertical takeoff and landing of aircraft.Aero-engine 10 front portions are connected with propeller 18 through power-transfer clutch 12, transmission shaft 11, the rear portion is connected with retarder 13 through power-transfer clutch 12, transmission shaft 11, adjustable rotor fixed link 19 is equipped with at rear portion, fuselage 16 top, adjustable rotor fixed link 19 is packed up when the vertical take-off and landing aircraft (VTOL aircraft) vertical takeoff and landing, aircraft is flat to stretch out fixedly rotor 5 rear portions when flying, make its flat rotor 5 that do not allow when flying produce swing.
Claims (6)
1, a kind of vertical take-off and landing aircraft (VTOL aircraft), comprise driving compartment (1), fuselage (16), aero-engine (10), wing (9), tailplane (7), vertical tail (6) and control system, it is characterized in that fuselage (16) top is equipped with rotor (5), rotor automatic positioning equipment (4) is housed on the rotor (5), rotor (5) is connected with rotor shaft (3), rotor shaft (3) and retarder (13), rotor shaft retractor device (14) connects, rotor shaft automatic positioning equipment (15) is housed on the rotor shaft (3), able to turn on or off rotor cabin (2) is equipped with at fuselage (16) top, aero-engine (10) is through transmission shaft (11), power-transfer clutch (12) is connected with retarder (13), and aero-engine (10) rear portion is equipped with and is turned to vector jet pipe (8).
2, vertical take-off and landing aircraft (VTOL aircraft) according to claim 1 is characterized in that rotor (5) structure is the contrarotation bispin wing, and rotor shaft (3) is the contrarotation rotor shaft.
3, vertical take-off and landing aircraft (VTOL aircraft) according to claim 1 is characterized in that retarder (13) can be connected with many aero-engine, and aero-engine (10) is connected with power-transfer clutch (12), can turn to auxiliary aviation driving engine (17) is housed on the vertical tail (20).
4, according to claim 1 or 3 described vertical take-off and landing aircraft (VTOL aircraft), it is characterized in that the preceding propeller (18) that is equipped with of aero-engine (10), propeller (18) is housed behind the auxiliary aviation driving engine (17).
5, according to claim 1 or 3 described vertical take-off and landing aircraft (VTOL aircraft), it is characterized in that rotor cabin (2) front and rear portions is equipped with rotor (5) and corresponding with it rotor shaft (3), rotor automatic positioning equipment (4), retarder (13), rotor shaft automatic positioning equipment (15), rotor shaft retractor device (14), transmission shaft (11), aero-engine (10) respectively, vertical tail (6) is installed downwards.
6, vertical take-off and landing aircraft (VTOL aircraft) according to claim 1 and 2, rotor (5) structure that it is characterized in that fuselage (16) top is a coaxial double-rotary wing, rotor shaft (3) is the contrarotation rotor shaft, aero-engine (10) is anterior to be connected with propeller (18) through power-transfer clutch (12), transmission shaft (11), the rear portion is connected with retarder (13) through power-transfer clutch (12), transmission shaft (11), and adjustable rotor fixed link (19) is equipped with at rear portion, fuselage (16) top.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008100585217A CN101602403A (en) | 2008-06-12 | 2008-06-12 | Vertical take-off and landing aircraft (VTOL aircraft) |
| PCT/CN2008/002094 WO2009149592A1 (en) | 2008-06-12 | 2008-12-26 | Vertical takeoff and landing airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2008100585217A CN101602403A (en) | 2008-06-12 | 2008-06-12 | Vertical take-off and landing aircraft (VTOL aircraft) |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101602403A true CN101602403A (en) | 2009-12-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2008100585217A Pending CN101602403A (en) | 2008-06-12 | 2008-06-12 | Vertical take-off and landing aircraft (VTOL aircraft) |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN101602403A (en) |
| WO (1) | WO2009149592A1 (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103171764A (en) * | 2013-03-29 | 2013-06-26 | 北京航空航天大学 | Perpendicular/short-distance lifting warplane with two retractable rotor wings |
| CN104290906A (en) * | 2014-11-04 | 2015-01-21 | 中国人民解放军国防科学技术大学 | Vertical take-off and landing aircraft |
| CN105173060A (en) * | 2015-11-02 | 2015-12-23 | 佛山市神风航空科技有限公司 | Two-propeller plane capable of taking off and landing vertically |
| WO2017025060A1 (en) * | 2015-08-12 | 2017-02-16 | 刘十一 | Fixed-wing aircraft capable of taking off and landing vertically, and flight control method therefor |
| WO2017048336A3 (en) * | 2015-05-28 | 2017-06-01 | Vetter Eugene H | Devices and methods for in flight transition vtol/fixed wing hybrid aircraft structures and flight modes |
| CN106904266A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | A kind of new fixed wing aircraft |
| CN107745808A (en) * | 2017-11-15 | 2018-03-02 | 孙林青 | A kind of compound helicopter |
| CN108502167A (en) * | 2017-02-24 | 2018-09-07 | 罗傲 | A kind of fixed-wing rotation paddle aircraft with rotor |
| CN109552618A (en) * | 2018-12-01 | 2019-04-02 | 江苏鸿鹄无人机应用科技有限公司 | A kind of unmanned plane emergency back-up flight device |
| CN110641238A (en) * | 2019-11-08 | 2020-01-03 | 孙林青 | An all-round flying car with excellent safety for land, sea and air |
| CN114194388A (en) * | 2021-11-23 | 2022-03-18 | 上海羽天航空科技有限公司 | Novel vertical take-off and landing fixed wing aircraft |
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| US11167845B2 (en) * | 2018-08-27 | 2021-11-09 | Textron Innovations Inc. | High speed rotorcraft propulsion configuration |
| CN110775264B (en) * | 2019-10-28 | 2022-10-18 | 上海交通大学 | Water-air amphibious unmanned aircraft and control method thereof |
| WO2023242448A1 (en) | 2022-06-17 | 2023-12-21 | Podadera Dominguez Francisco | Lift module for vertical take-off and landing aircraft and aircraft incorporating such a module |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2953319A (en) * | 1955-01-05 | 1960-09-20 | United Aircraft Corp | Convertiplane |
| US3370809A (en) * | 1965-06-29 | 1968-02-27 | United Aircraft Corp | Convertiplane |
| IT1297108B1 (en) * | 1997-12-10 | 1999-08-03 | Franco Capanna | SYSTEM FOR THE TRANSFORMATION OF A SELF-SUPPORTED HORIZONTAL FLIGHT AIRCRAFT INTO AN INTEGRATED, HYBRID TAKE-OFF AIRCRAFT |
| US6622962B1 (en) * | 2002-04-29 | 2003-09-23 | Bruce D. White | Fixed wing aircraft having powered rotor VTOL capability with rotor blades stowable during horizontal flight |
| DE10241732A1 (en) * | 2002-09-06 | 2004-03-25 | Hinüber, Edgar v. | Horizontal and vertical take-off and landing combination aircraft used as a rotary wing and fixed-wing aircraft comprises a rotor lift used as a telescopic device for a rotary wing drive lowered into and lifted out of the fuselage |
-
2008
- 2008-06-12 CN CNA2008100585217A patent/CN101602403A/en active Pending
- 2008-12-26 WO PCT/CN2008/002094 patent/WO2009149592A1/en active Application Filing
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103171764A (en) * | 2013-03-29 | 2013-06-26 | 北京航空航天大学 | Perpendicular/short-distance lifting warplane with two retractable rotor wings |
| CN104290906A (en) * | 2014-11-04 | 2015-01-21 | 中国人民解放军国防科学技术大学 | Vertical take-off and landing aircraft |
| WO2017048336A3 (en) * | 2015-05-28 | 2017-06-01 | Vetter Eugene H | Devices and methods for in flight transition vtol/fixed wing hybrid aircraft structures and flight modes |
| WO2017025060A1 (en) * | 2015-08-12 | 2017-02-16 | 刘十一 | Fixed-wing aircraft capable of taking off and landing vertically, and flight control method therefor |
| AU2016305704B2 (en) * | 2015-08-12 | 2019-03-07 | Shanghai Fukun Aviation Technology Co., Ltd | Vertical take-off and landing Fixed-wing aircraft and the flight control method thereof |
| CN105173060A (en) * | 2015-11-02 | 2015-12-23 | 佛山市神风航空科技有限公司 | Two-propeller plane capable of taking off and landing vertically |
| CN108502167A (en) * | 2017-02-24 | 2018-09-07 | 罗傲 | A kind of fixed-wing rotation paddle aircraft with rotor |
| CN106904266A (en) * | 2017-03-21 | 2017-06-30 | 张宏 | A kind of new fixed wing aircraft |
| CN107745808A (en) * | 2017-11-15 | 2018-03-02 | 孙林青 | A kind of compound helicopter |
| CN109552618A (en) * | 2018-12-01 | 2019-04-02 | 江苏鸿鹄无人机应用科技有限公司 | A kind of unmanned plane emergency back-up flight device |
| CN110641238A (en) * | 2019-11-08 | 2020-01-03 | 孙林青 | An all-round flying car with excellent safety for land, sea and air |
| CN114194388A (en) * | 2021-11-23 | 2022-03-18 | 上海羽天航空科技有限公司 | Novel vertical take-off and landing fixed wing aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2009149592A1 (en) | 2009-12-17 |
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Application publication date: 20091216 |