CN106494608A - Many shrouded propeller variable geometry Electric aircrafts - Google Patents

Many shrouded propeller variable geometry Electric aircrafts Download PDF

Info

Publication number
CN106494608A
CN106494608A CN201510555617.4A CN201510555617A CN106494608A CN 106494608 A CN106494608 A CN 106494608A CN 201510555617 A CN201510555617 A CN 201510555617A CN 106494608 A CN106494608 A CN 106494608A
Authority
CN
China
Prior art keywords
wing
tailplane
fuselage
tilting type
shrouded propeller
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201510555617.4A
Other languages
Chinese (zh)
Inventor
陈康
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Suzhou Ru Bote Science And Technology Co Ltd
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to CN201510555617.4A priority Critical patent/CN106494608A/en
Publication of CN106494608A publication Critical patent/CN106494608A/en
Pending legal-status Critical Current

Links

Landscapes

  • Toys (AREA)

Abstract

A kind of many shrouded propeller variable geometry Electric aircrafts, category air material field.Lifting and when parking, wing and tailplane foldable with body on, after lift-off, wing and tailplane are opened, less than on wing, the horizontal plane of tailplane before and after multiple shrouded propellers for verting are symmetrically distributed in wing and in the body left and right sides.Using above-mentioned layout, the machine can VTOL, again can quick flat fly, VTOL and reduce floor space when parking, when flat winged, increased speed and airborne period.Landing process safety reliability, flight attitude are steady.Piloted vehicle can be made, may be made as unmanned plane.

Description

Many shrouded propeller variable geometry Electric aircrafts
Technical field
The present invention relates to a kind of band wing, tailplane, the electricity that vertical tail and multiple shrouded propellers are constituted Dynamic aircraft, category air material field.
Background technology
At present, known helicopter or multi-rotor unmanned aerial vehicle are all to complete to take off vertically by rotary wings, hovering With horizontal flight, due to the presence of rotor, in small space landing, no matter to the pedestrian of surrounding or Itself all has certain danger.Chinese patent literature application number:200420063679.0, title:Vertical The double four spout individual lift devices of duct of row and application number:200920053565.0, title:Double ducts can be vertical Landing hovercar etc. also provides the scheme of some duct aircraft, but the former is fixed-wing, takes off vertically Big with floor space when parking;, without wing, power consumption is big, and airborne period is short for the latter, and during horizontal flight Speed is slow, furthermore produces vertical lift using two shrouded propellers, and safety is also poor, especially inorganic Wing person, in the air, once there is a shrouded propeller to break down, consequence is hardly imaginable.
Content of the invention
In order to overcome prior art floor space big, power consumption, and the deficiency of poor stability, the invention provides A kind of Electric aircraft scheme constituted with multiple tilting type shrouded propellers and variable geometry so that flight During device VTOL, floor space is little, and energy-conservation during horizontal flight, airborne period are long, and during high-speed flight, resistance is little, Flight attitude is stable, and landing is safe and reliable.
The technical solution adopted for the present invention to solve the technical problems is:Design one kind is by fuselage (8), wing (3) what, tailplane (4), vertical tail (5), tilting type shrouded propeller (1), (2) were constituted is more Shrouded propeller variable geometry Electric aircraft, its wing (3), tailplane (4) root are respectively provided with one The rotating mechanism being connected with fuselage (8), rotating mechanism can be detected the reducing motor of rotary position information by band (14) steering wheel (19) for or by wing rotating shaft (17), connecting rod (12), rocking arm (13), control wing rotating Mechanism's composition of composition, the wing tip that can control wing (3) are rotated to the rear portion of fuselage (8), while control Front portion rotation of the wing tip of tailplane (4) to fuselage (8), mounted on top is on fuselage (8);Multiple Before tilting type shrouded propeller (1) is symmetrically distributed in wing (3) or after tailplane (4), another A bit multiple tilting type shrouded propeller (2) be symmetrically distributed in fuselage (8) left and right sides less than wing (3) and On the horizontal plane of tailplane (4);Tilting type shrouded propeller (1), the tiliting axis (7) of (2) are through shaking Arm (13), connecting rod (12) are connected with steering wheel (11), can control tilting type shrouded propeller (1), (2) Rotate to 90 degree around tiliting axis (7), the control signal of steering wheel (11), the position of reducing motor (14) The control signal of the input or steering wheel (19) of signal and control signal is connected respectively to flight controller (20) Corresponding input, output port.
The invention has the beneficial effects as follows:After the folding of wing and tailplane, aircraft can be risen narrow space is vertical Drop and park, after lift-off, wing and tailplane are opened, and can be glided using wing during horizontal flight, are saved Electric energy, extends airborne period, and during high-speed flight, wing, tailplane sweepback reduce air drag. by Be made up of motor and battery in dynamical system, pollution-free, noise is also little, be easy to automatically control with wireless electric-controlled System and regular maintenance, safe and reliable during landing, flight attitude is stable, even if there is indivedual shrouded propellers to occur Failure, also can safe vertical landing or dead-stick landing by remaining shrouded propeller and wing aircraft.
The present invention can be made into manned vehicle, used as civilian traffic instrument;May be made as unmanned plane. with reality Now take photo by plane, investigate and all kinds of civilian and militaries in terms of purposes.
Description of the drawings
The present invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 be the present invention using 6 tilting type shrouded propellers type, two of which of verting tilting type Shrouded propeller carries out the shaft side figure of horizontal flight.
The 1. tilting type shrouded propeller before wing or after tailplane in figure, is 2. located at fuselage both sides Tilting type shrouded propeller, 3. wing, 4. tailplane, 5. vertical tail, 7. tilting type contain Road propeller tiliting axis, 8. body, 10. underpart.
Fig. 2 is axle of the present invention using the type VTOL of 6 tilting type shrouded propellers or when parking Side figure.
The 1. tilting type shrouded propeller before wing or after tailplane in figure, is 2. located at fuselage both sides Tilting type shrouded propeller, 3. wing, 4. tailplane, 8. body.
Fig. 3 be the present invention using 6 tilting type shrouded propellers type, 6 tilting type shrouded propellers All verting carries out the shaft side figure of horizontal flight.
In figure, 2. are located at the tilting type shrouded propeller of fuselage both sides.
Fig. 4 be the present invention using 4 tilting type shrouded propellers type, two of which of verting tilting type Shrouded propeller carries out the shaft side figure of horizontal flight.
In figure, 1. are located at the tilting type shrouded propeller before wing, are 2. located at the tilting type duct of fuselage both sides Propeller, 3. wing, 4. tailplane, 5. vertical tail, 6. dynamic lithium battery group, 7. inclines Rotatable shrouded propeller tiliting axis, 8. body.
Fig. 5 is axle of the present invention using the type VTOL of 4 tilting type shrouded propellers or when parking Side figure.
In figure, 2. are located at the tilting type shrouded propeller of fuselage both sides.
Fig. 6 be the present invention using 4 tilting type shrouded propellers type, 4 tilting type shrouded propellers All verting carries out the shaft side figure of horizontal flight.
In figure, 1. are located at the tilting type shrouded propeller before wing, are 2. located at the tilting type duct of fuselage both sides Propeller, 3. wing, 4. tailplane, 5. vertical tail, 6. dynamic lithium battery group, 7. inclines Rotatable shrouded propeller tiliting axis,
Fig. 7 is the structure chart of wing of the present invention or tailplane and reducing motor connection.
3. wings or tailplane in figure, 14. reducing motors, 18. connection wings or tailplane and wing The fixedly connected part of rotating shaft.
Fig. 8 is the schematic diagram of reducing motor of the present invention and position detecting device.
14. reducing motor in figure, 15. slot optical couplings, 16. brake sacks, 17. wing rotating shafts.
Fig. 9 is the structure chart of wing of the present invention or tailplane and control steering wheel.
3. wing in figure, 12. connecting rods, 13. rocking arms, 17. wing rotating shafts, 19. control wing rotations Steering wheel.
Figure 10 is the structure chart of tilting type shrouded propeller of the present invention and control steering wheel.
1. tilting type shrouded propeller in figure, 7. tilting type shrouded propeller tiliting axis, 11. control flaps Machine, 12. connecting rods, 13. rocking arms.
Figure 11 is the circuit connection block diagram of flight controller of the present invention and associated control element.
6. dynamic lithium battery group in figure, 11. tilting duct propeller steering wheels, 14. reducing motors, 19. can Become wing steering wheel, 20. flight controllers, 21. wireless remotecontrol command receivers, 22. pilot steerings are grasped Vertical mechanism, 23. lifting steering wheels, 24. direction steering wheels, 25. aileron steering wheels, 26. electricity adjust, 27. duct spirals Oar motor.
Specific embodiment
As shown in Figure 1, Figure 2, Fig. 4, Fig. 6, wing (3) and tailplane (4) root are respectively connected with one Rotating mechanism, the mechanism can be made up of the reducing motor with test position information (14), see Fig. 7 and Fig. 8; Can also be made up of wing rotating shaft (17), rocking arm (13), connecting rod (12), steering wheel (19), referring to Fig. 9; Rotating mechanism one end is fixedly connected with wing (3) or tailplane (4), and the other end is fixed on fuselage or machine On body skeleton (8).Drive reducing motor (14) or the steering wheel (19) of control wing rotation make expansion The wing tip of wing (3) is to fuselage afterbody rotary folding;Or the wing (3) of folding is rotated round about Launch, or stop certain angle between.Connect the reducing motor (14) of tailplane (4) in the same manner Or the steering wheel (19) of control wing rotation can be such that the wing tip of the tailplane (3) of expansion revolves to fore-body Turnover is folded, or the tailplane (4) for making to have folded rotary expansion round about, or stops between Certain angle.After folding wing (3) and tailplane (4) can mounted on top on fuselage (8), ginseng See Fig. 2, Fig. 6.Every airfoil root connects the rudder of a reducing motor (14) or a control wing rotation Machine (19), referring to Fig. 7, Fig. 8, Fig. 9.Fig. 8 is constituted using two optocouplers (15) and brake sack (16) Rotary position information detection means, two optocouplers (15) output termination flight controller (20).Fig. 1, Fig. 2 is the type constituted using 6 tilting type shrouded propellers, two of which tilting type shrouded propeller (1) It is symmetrically distributed in wing (3) before and tailplane (4) is higher than machine on the horizontal plane of body center of gravity afterwards After the span is opened, during horizontal flight, two tilting type shrouded propellers (1) are rotated by 90 °, and produce forward Pulling force or thrust;To further increase pulling force forward or thrust, can by two of fuselage (8) both sides or Four tilting type shrouded propellers (2) are also rotated by 90 °, referring to Fig. 3.Four of fuselage (8) both sides incline Rotatable shrouded propeller is symmetrically distributed in the left and right sides of fuselage (8) less than wing (3) and tailplane (4) Horizontal plane on, when taking off vertically, provide the pulling force for taking off vertically with tilting type shrouded propeller (1) together, Referring to Fig. 2;Tilting type shrouded propeller (1), the tiliting axis (7) of (2) pass through rocking arm (13), connecting rod (12) It is connected with steering wheel (11), can pivot 90 degree of pulling force or thrust to provide aircraft horizontal flight. Fig. 4, Fig. 5 and Fig. 6 are the types that the present invention is constituted using 4 tilting type shrouded propellers, and two of which is inclined Before rotatable shrouded propeller (1) is symmetrically distributed in wing (3), two other is distributed in tailplane (4) Before higher than on the horizontal plane of body center of gravity, 4 tilting type shrouded propellers are placed in less than wing and level In tail plane.After wing launches, during horizontal flight, two tilting type shrouded propeller (1) rotations 90 Degree, produces pulling force forward, referring to Fig. 4;To further increase pulling force forward or thrust, can be by fuselage (8) two tilting type shrouded propellers (2) of both sides are also rotated by 90 °, and see Fig. 5.Whether 6 are adopted The type that individual or 4 tilting type shrouded propellers are constituted, each tilting type shrouded propeller (1), (2) All connect a steering wheel (11);The control signal circuit of steering wheel (11) is connected to flight controller (20) I/O ports, can control each tilting type shrouded propeller (1), (2) respectively and vert;Each tilting type duct Propeller (1), (2) all individually connect a motor (27), and they are individually connected to respective electricity and adjust (26) on;Electricity adjusts the outfan and the I/O of flight controller (20) of (26) and dynamic lithium battery group (6) Control end is connected, and can independently control the rotating speed of each motor (27), referring to Figure 11;Flight control The commercially available finished product of device (20) processed using Open Source Code, its interface connect multiple electricity respectively and adjust (26).Manually drive Bench board (22) is sailed for manned (unmanned type is not needed), driver's cabin is placed in.Pilot steering is grasped Vertical platform (22) directly can be reequiped with radio remote controller, and its antenna is connected to after resistance decrement radio The antenna end of receiver (21), and the signal ground of two machines is joined directly together.Flight controller (20) I/O ports are also connected with the output circuit of wireless remotecontrol command receiver (21), and wireless remotecontrol instruction connects Receipts machine (21) wireless remotecontrol command receiver transmitter can adopt the above model airplane remote control transmitting-receiving of commercially available 9 passage Equipment, respectively control tilting type shrouded propeller (1), the verting of (2), wing (3), tailplane (4) Rotation, tilting type shrouded propeller (1), (2) vert and rotating speed and lifting steering wheel (23), rudder Machine (24), the swing of aileron steering wheel (25).During VTOL, flight controller (20) adjust 4 or 6 tilting type shrouded propellers (1), the rotating speeds of (2), keep stablizing for aircraft flight attitude;Level flies During row, flight controller (20) adjusts lifting steering wheel (23), direction steering wheel (24), aileron steering wheel (25) Angle, keep aircraft horizontal flight, climb, decline and course.

Claims (1)

1. one kind is by fuselage (8), wing (3), tailplane (4), vertical tail (5), tilting type duct spiral shell Many shrouded propeller variable geometry Electric aircrafts that rotation oar (1), (2) are constituted, it is characterised in that:Wing (3), tailplane (4) root is respectively provided with a rotating mechanism being connected with fuselage (8), rotating mechanism Can by band detect rotary position information reducing motor (14) or by wing rotating shaft (17), connecting rod (12), Mechanism's composition that rocking arm (13), the steering wheel (19) of control wing rotation are constituted, can control wing (3) Wing tip is rotated to the rear portion of fuselage (8), while the wing tip of control tailplane (4) is to before fuselage (8) Portion rotates, and mounted on top is on fuselage (8);Multiple tilting type shrouded propeller (1) is symmetrically distributed in machine Before the wing (3) or after tailplane (4), other multiple tilting type shrouded propeller (2) are symmetrically divided On horizontal plane of the cloth in fuselage (8) left and right sides less than wing (3) and tailplane (4);Tilting type is contained Road propeller (1), the tiliting axis (7) of (2) are through rocking arm (13), connecting rod (12) and steering wheel (11) phase Even, controllable tilting type shrouded propeller (1), (2) are rotated to 90 degree around tiliting axis (7), steering wheel (11) Control signal, the position signalling of reducing motor (14) and control signal input or steering wheel (19) Control signal is connected respectively to the corresponding input of flight controller (20), output port.
CN201510555617.4A 2015-09-06 2015-09-06 Many shrouded propeller variable geometry Electric aircrafts Pending CN106494608A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201510555617.4A CN106494608A (en) 2015-09-06 2015-09-06 Many shrouded propeller variable geometry Electric aircrafts

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201510555617.4A CN106494608A (en) 2015-09-06 2015-09-06 Many shrouded propeller variable geometry Electric aircrafts

Publications (1)

Publication Number Publication Date
CN106494608A true CN106494608A (en) 2017-03-15

Family

ID=58287549

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201510555617.4A Pending CN106494608A (en) 2015-09-06 2015-09-06 Many shrouded propeller variable geometry Electric aircrafts

Country Status (1)

Country Link
CN (1) CN106494608A (en)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106828904A (en) * 2017-04-07 2017-06-13 东莞市锦明运动器材有限公司 Machine is maked an inspection tour in a kind of new-type unmanned delivery with gliding function
CN107458601A (en) * 2017-09-03 2017-12-12 佛山市龙远科技有限公司 A kind of amphibious unmanned plane of the VTOL with auxiliary power
CN107458579A (en) * 2017-08-01 2017-12-12 中国航空工业集团公司西安飞机设计研究所 A kind of unmanned plane device
CN107539470A (en) * 2017-09-03 2018-01-05 佛山市龙远科技有限公司 A kind of four oars amphibious unmanned plane of VTOL
CN107554783A (en) * 2017-09-03 2018-01-09 佛山市龙远科技有限公司 A kind of amphibious unmanned plane of VTOL
CN107554778A (en) * 2017-09-03 2018-01-09 佛山市海茂聚航科技有限公司 A kind of land and water unmanned plane of VTOL
CN107696811A (en) * 2017-09-03 2018-02-16 佛山市龙远科技有限公司 A kind of VTOL amphibious unmanned plane of more power
CN107972860A (en) * 2017-12-03 2018-05-01 佛山市神风航空科技有限公司 A kind of stabilized flight device
CN108791874A (en) * 2018-06-21 2018-11-13 南京航空航天大学 A kind of tilting duct power unmanned vehicle
CN108791876A (en) * 2017-04-28 2018-11-13 北京领恩科技有限公司 It is a kind of can be with the aircraft of vertical and landing takeoff
WO2018209911A1 (en) * 2017-05-16 2018-11-22 华南理工大学 Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system
CN108995802A (en) * 2017-06-07 2018-12-14 北京领恩科技有限公司 A kind of modular propulsion system and can be with the aircraft of vertical and landing takeoff
CN109159633A (en) * 2018-08-31 2019-01-08 长春工程学院 A kind of amphibious unmanned plane
WO2019026079A1 (en) * 2017-08-02 2019-02-07 Gadfin Ltd. An unmanned aerial vehicle
WO2019052142A1 (en) * 2017-09-12 2019-03-21 深圳光启合众科技有限公司 Flying car
CN109592007A (en) * 2018-11-17 2019-04-09 成都奥克特科技有限公司 Double mode unmanned plane working method and double mode unmanned plane
CN110341951A (en) * 2019-07-22 2019-10-18 中北大学 A kind of unmanned vehicle of folding wing and tilting rotor
CN110891859A (en) * 2017-07-27 2020-03-17 株式会社辰巳菱机 Suspension type mobile device
CN112124569A (en) * 2020-09-17 2020-12-25 西安电子科技大学 Vertical take-off and landing and unmanned aerial vehicle stabilizing system based on launching canister
CN112498679A (en) * 2020-12-14 2021-03-16 江西洪都航空工业股份有限公司 Tilting composite power aircraft
CN112549885A (en) * 2020-12-21 2021-03-26 中国科学院沈阳自动化研究所 Folding wing submerged cross-domain marine robot capable of vertically taking off and landing
CN113002770A (en) * 2021-03-29 2021-06-22 曾成刚 Rotor craft capable of attaching wings to fuselage
CN113104195A (en) * 2021-05-19 2021-07-13 涵涡智航科技(玉溪)有限公司 Double-duct composite wing aircraft
CN113830300A (en) * 2021-11-09 2021-12-24 北京航空航天大学 General structure of duct type aircraft
CN114148506A (en) * 2021-12-06 2022-03-08 浙江大学 Foldable variant unmanned aerial vehicle and control method thereof

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN200995782Y (en) * 2007-01-17 2007-12-26 赵文志 Airplane
US20110168834A1 (en) * 2003-10-27 2011-07-14 Urban Aeronautics Ltd. Ducted fan vtol vehicles
CN102574575A (en) * 2009-09-09 2012-07-11 威罗门飞行公司 Elevon control system
CN102897317A (en) * 2011-07-29 2013-01-30 奥格斯塔韦斯兰股份公司 Convertiplane
CN103043214A (en) * 2012-12-19 2013-04-17 天津全华时代航天科技发展有限公司 Folding type unmanned plane
CN103231805A (en) * 2013-05-21 2013-08-07 吉林大学 Duct type folding wing machine
CN103832585A (en) * 2012-11-22 2014-06-04 上海市浦东新区知识产权保护协会 Cruise aircraft
CN104071336A (en) * 2014-06-30 2014-10-01 中国人民解放军国防科学技术大学 Portable folding wing unmanned aerial vehicle
CN104401480A (en) * 2014-11-06 2015-03-11 南京航空航天大学 Ducted tilt aircraft
US9085355B2 (en) * 2012-12-07 2015-07-21 Delorean Aerospace, Llc Vertical takeoff and landing aircraft

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110168834A1 (en) * 2003-10-27 2011-07-14 Urban Aeronautics Ltd. Ducted fan vtol vehicles
CN200995782Y (en) * 2007-01-17 2007-12-26 赵文志 Airplane
CN102574575A (en) * 2009-09-09 2012-07-11 威罗门飞行公司 Elevon control system
CN102897317A (en) * 2011-07-29 2013-01-30 奥格斯塔韦斯兰股份公司 Convertiplane
CN103832585A (en) * 2012-11-22 2014-06-04 上海市浦东新区知识产权保护协会 Cruise aircraft
US9085355B2 (en) * 2012-12-07 2015-07-21 Delorean Aerospace, Llc Vertical takeoff and landing aircraft
CN103043214A (en) * 2012-12-19 2013-04-17 天津全华时代航天科技发展有限公司 Folding type unmanned plane
CN103231805A (en) * 2013-05-21 2013-08-07 吉林大学 Duct type folding wing machine
CN104071336A (en) * 2014-06-30 2014-10-01 中国人民解放军国防科学技术大学 Portable folding wing unmanned aerial vehicle
CN104401480A (en) * 2014-11-06 2015-03-11 南京航空航天大学 Ducted tilt aircraft

Cited By (38)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106828904A (en) * 2017-04-07 2017-06-13 东莞市锦明运动器材有限公司 Machine is maked an inspection tour in a kind of new-type unmanned delivery with gliding function
CN108791876B (en) * 2017-04-28 2022-01-07 北京领恩科技有限公司 Aircraft capable of vertically taking off and landing
CN108791876A (en) * 2017-04-28 2018-11-13 北京领恩科技有限公司 It is a kind of can be with the aircraft of vertical and landing takeoff
US11634222B2 (en) 2017-05-16 2023-04-25 South China University Of Technology Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system
WO2018209911A1 (en) * 2017-05-16 2018-11-22 华南理工大学 Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system
CN108995802A (en) * 2017-06-07 2018-12-14 北京领恩科技有限公司 A kind of modular propulsion system and can be with the aircraft of vertical and landing takeoff
CN108995802B (en) * 2017-06-07 2022-01-07 北京领恩科技有限公司 Modular propulsion system and aircraft capable of vertical takeoff and landing
CN110891859B (en) * 2017-07-27 2023-03-10 株式会社辰巳菱机 Suspension type mobile device
US10745125B2 (en) 2017-07-27 2020-08-18 Tatsumi Ryoki Co., Ltd Hovering vehicle
CN110891859A (en) * 2017-07-27 2020-03-17 株式会社辰巳菱机 Suspension type mobile device
CN107458579A (en) * 2017-08-01 2017-12-12 中国航空工业集团公司西安飞机设计研究所 A kind of unmanned plane device
CN111295330A (en) * 2017-08-02 2020-06-16 嘉德芬有限公司 Unmanned aerial vehicle
EP3661846A4 (en) * 2017-08-02 2021-08-11 Eyal Regev An unmanned aerial vehicle
US11584524B2 (en) 2017-08-02 2023-02-21 Gadfin Ltd. Unmanned aerial vehicle
WO2019026079A1 (en) * 2017-08-02 2019-02-07 Gadfin Ltd. An unmanned aerial vehicle
EP4043345A1 (en) * 2017-08-02 2022-08-17 Eyal Regev An unmanned aerial vehicle
CN107458601A (en) * 2017-09-03 2017-12-12 佛山市龙远科技有限公司 A kind of amphibious unmanned plane of the VTOL with auxiliary power
CN107554778A (en) * 2017-09-03 2018-01-09 佛山市海茂聚航科技有限公司 A kind of land and water unmanned plane of VTOL
CN107554783A (en) * 2017-09-03 2018-01-09 佛山市龙远科技有限公司 A kind of amphibious unmanned plane of VTOL
CN107539470A (en) * 2017-09-03 2018-01-05 佛山市龙远科技有限公司 A kind of four oars amphibious unmanned plane of VTOL
CN107696811A (en) * 2017-09-03 2018-02-16 佛山市龙远科技有限公司 A kind of VTOL amphibious unmanned plane of more power
WO2019052142A1 (en) * 2017-09-12 2019-03-21 深圳光启合众科技有限公司 Flying car
CN107972860A (en) * 2017-12-03 2018-05-01 佛山市神风航空科技有限公司 A kind of stabilized flight device
CN108791874A (en) * 2018-06-21 2018-11-13 南京航空航天大学 A kind of tilting duct power unmanned vehicle
CN109159633A (en) * 2018-08-31 2019-01-08 长春工程学院 A kind of amphibious unmanned plane
CN109592007A (en) * 2018-11-17 2019-04-09 成都奥克特科技有限公司 Double mode unmanned plane working method and double mode unmanned plane
CN110341951A (en) * 2019-07-22 2019-10-18 中北大学 A kind of unmanned vehicle of folding wing and tilting rotor
CN112124569B (en) * 2020-09-17 2022-04-01 西安电子科技大学 Vertical take-off and landing and unmanned aerial vehicle stabilizing system based on launching canister
CN112124569A (en) * 2020-09-17 2020-12-25 西安电子科技大学 Vertical take-off and landing and unmanned aerial vehicle stabilizing system based on launching canister
CN112498679B (en) * 2020-12-14 2022-10-28 江西洪都航空工业股份有限公司 Tilting composite power aircraft
CN112498679A (en) * 2020-12-14 2021-03-16 江西洪都航空工业股份有限公司 Tilting composite power aircraft
CN112549885A (en) * 2020-12-21 2021-03-26 中国科学院沈阳自动化研究所 Folding wing submerged cross-domain marine robot capable of vertically taking off and landing
CN113002770A (en) * 2021-03-29 2021-06-22 曾成刚 Rotor craft capable of attaching wings to fuselage
CN113104195B (en) * 2021-05-19 2022-03-11 涵涡智航科技(玉溪)有限公司 Double-duct composite wing aircraft
CN113104195A (en) * 2021-05-19 2021-07-13 涵涡智航科技(玉溪)有限公司 Double-duct composite wing aircraft
CN113830300A (en) * 2021-11-09 2021-12-24 北京航空航天大学 General structure of duct type aircraft
CN114148506A (en) * 2021-12-06 2022-03-08 浙江大学 Foldable variant unmanned aerial vehicle and control method thereof
CN114148506B (en) * 2021-12-06 2023-10-13 浙江大学 Foldable variant unmanned aerial vehicle and control method thereof

Similar Documents

Publication Publication Date Title
CN106494608A (en) Many shrouded propeller variable geometry Electric aircrafts
US8733690B2 (en) Lightweight vertical take-off and landing aircraft and flight control paradigm using thrust differentials
CN106882371A (en) A kind of hybrid tilting rotor wing unmanned aerial vehicle
CN106542085A (en) The Electric aircraft of many shrouded propeller retractable wings and fuselage
CN204916182U (en) High -speed vertical take -off and landing aircraft
CN106143895B (en) Thrust type tilt rotor aircraft
CN106915459A (en) A kind of hybrid tilting rotor wing unmanned aerial vehicle
CN105292460A (en) Tilt-rotor based on combination of four rotor wings and fixed wing
CN205022862U (en) Power device and fixed wing aircraft with mechanism of verting
CN214566145U (en) Fixed wing unmanned aerial vehicle with VTOL and hover function
CN201712787U (en) Electric tilt rotor unmanned aircraft
CN101879945A (en) Electric tilting rotor wing unmanned aerial vehicle
CN105109677A (en) Composite aircraft composed of fixed wings and multi-rotary wings and control method of composite aircraft
CN103832584B (en) A kind of with fixed wing, collapsible empennage to switch rotor aircraft
CN205396534U (en) Rotor unmanned aerial vehicle verts
CN108298071A (en) A kind of more rotor flying vehicles of manned duct
CN105173076B (en) A kind of vertical take-off and landing drone
CN204548497U (en) A kind of many rotor flight devices
CN209176908U (en) A kind of rotor fixed-wing unmanned plane of composite drive
CN108298074A (en) The component that verts for the more rotor flying vehicles of manned duct
CN107097949A (en) A kind of VTOL fixed-wing unmanned plane
CN203842313U (en) Novel remote control model with combination of vertical take-off and landing and level fight characteristic of fixed wing
CN205131630U (en) Double -oar vertical lift aircraft
CN105173060B (en) A kind of pair of oar Convertiplane
CN209426502U (en) A kind of hovercar

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
TA01 Transfer of patent application right

Effective date of registration: 20170816

Address after: Wusong Road Wuzhong Economic Development Zone of Suzhou City, Jiangsu province 215127 No. 988 building 3 floor five

Applicant after: Suzhou Ru Bote science and Technology Co Ltd

Address before: 100029 Beijing City, Chaoyang District Hui North Building 4, room 908

Applicant before: Chen Kang

TA01 Transfer of patent application right
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20170315

WD01 Invention patent application deemed withdrawn after publication