CN103587683A - Small-sized aircraft with tiltable rotor wings - Google Patents
Small-sized aircraft with tiltable rotor wings Download PDFInfo
- Publication number
- CN103587683A CN103587683A CN201310564111.0A CN201310564111A CN103587683A CN 103587683 A CN103587683 A CN 103587683A CN 201310564111 A CN201310564111 A CN 201310564111A CN 103587683 A CN103587683 A CN 103587683A
- Authority
- CN
- China
- Prior art keywords
- power unit
- rotor
- wing
- aircraft
- front power
- 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
Links
Images
Landscapes
- Transmission Devices (AREA)
Abstract
The invention belongs to an aircraft design technology, and relates to arrangement improvement of a small-sized aircraft with tiltable rotor wings. The small-sized aircraft is characterized in that a wing adopts a straight high monowing; four power units are divided into two groups, a first group is a front power unit group, fixed ends of front power unit tilting mechanisms (7c) in front power units (7) are connected with the front edge of the wing (5), and front power unit rotor wings (7a) are haul-in paddles; and a second group is a rear power unit group, fixed ends of rear power unit tilting mechanisms (6c) in rear power units (6) are connected with the rear edge of the wing (5), and rear power unit rotor wings (7a) are boosting paddles. With the adoption of the small-sized aircraft with the tiltable rotor wings, pneumatic disturbance of front and rear wings in the flying process can be eliminated, flying postures and control can be maintained without conventional manipulation of a control plane and a stabilizing plane, so that the aircraft structure is simplified, and the aircraft weight is reduced.
Description
Technical field
The invention belongs to airplane design technology, relate to the improvement to tiltrotor aircraft layout.
Background technology
Can tiltrotor aircraft because it possesses short distance/vertical takeoff and landing ability of helicopter and the high-performance cruise ability of Fixed Wing AirVehicle simultaneously, there is good task compatibility and wide application prospect.
Now a kind of layout that can tiltrotor aircraft is referring to Fig. 1, this layout is the verted quadrotor QTR(Quad Tilt Rotor of Boeing and Bell Co.'s joint research and development), it by fuselage 1, two groups of parallel high mounted wings front wing 2 form with rear wing 3 and four identical power units 4 of structure.Front wing 2 and rear wing 3 are connected to integral body with fuselage 1.Four power units 4 are divided into two groups and are arranged on respectively on front wing 2 and rear wing 3.Each power unit 4 is comprised of rotor 4a, driving engine 4b and inclining rotary mechanism 4c.The fixed end of power unit inclining rotary mechanism 4c is connected with front wing 2 or rear wing 3, and the end that verts of power unit inclining rotary mechanism 4c is connected with driving engine 4b, and rotor 4a is arranged on the output shaft of driving engine 4b, and rotor 4a is for drawing in oar.Its principle of work is: when carrying out vertical takeoff and landing, four power units 4 are all in vertical position, and the lift of this aircraft takeoff is provided by the rotor 4a of four power units 4.When cruising flight, four power units 4 are all horizontal, and rotor 4a is all positioned at the place ahead of each power unit 4, for this aircraft provides the pulling force advancing.
The shortcoming of existing scheme is: 1, adopting two groups of wings, is tandem wing layout, and the front and back wing exists disadvantageous aerodynamic interference in flight course, and structural weight is larger; 2, when vertical takeoff and landing, four rotors are in same plane, and four rotors are subject to the impact of the factors such as arrangement space and aerodynamic interference, cannot low coverage arrange; 3, when flying with fixed-wing form, need conventional primary control surface and stabilator to maintain attitude and the control of flight, mechanism is complicated; 4, power unit is arranged in wing wing tip, and the span of wing can not design too greatly, has affected the lifting resistance characteristic of cruising condition aircraft, the 1ift-drag ratio that particularly cruises, and then limited the raising of aircraft voyage with the economy of cruising.
Summary of the invention
The object of the invention is: propose a kind of improvement layout of tiltrotor aircraft, so that the aerodynamic interference that before and after eliminating, the wing exists in flight course is simplified aircaft configuration, alleviate aircraft weight.
Technical scheme of the present invention is: a kind of can tilting rotor small aircraft, comprise fuselage 1, wing and four power units that structure is identical, wing and fuselage 1 are connected to integral body, and four power units are arranged on wing, and each power unit is comprised of rotor, driving engine and inclining rotary mechanism; It is characterized in that: said wing is a straight high mounted wing; Four power units are divided into two groups, first group is front power unit group, it is comprised of two front power units 7, the fixed end of front power unit inclining rotary mechanism 7c in front power unit 7 is connected with the leading edge of wing 5, two front power units 7 are symmetrical with respect to the plane of symmetry of aircraft, the end that verts of front power unit inclining rotary mechanism 7c is connected with driving engine 7b, and front power unit rotor 7a is arranged on the output shaft of front power unit driving engine 7b, and front power unit rotor 7a is for drawing in oar; Second group is rear power unit group, it is comprised of power unit 6 after two, the fixed end of rear power unit inclining rotary mechanism 6c in rear power unit 6 is connected with the trailing edge of wing 5, after two, power unit 6 is symmetrical with respect to the plane of symmetry of aircraft, the end that verts of rear power unit inclining rotary mechanism 6c is connected with rear power unit driving engine 6b, rear power unit rotor 6a is arranged on the output shaft of driving engine, and rear power unit rotor 6a is for advancing oar; When after two front power units 7 and two, the axis of power unit 6 is all in level attitude or is all in upright position, two front power units 7 are parallel with the axis of power unit 6 after two, front power unit inclining rotary mechanism 7c can drive front power unit 7 to rotate, rear power unit inclining rotary mechanism 6c can drive rear power unit 6 to rotate, the maximum angle that front power unit 7 upwards verts from level attitude is 90 °, and the maximum angle that front power unit 7 verts downwards from level attitude is 30 °; The maximum angle that rear power unit 6 verts downwards from level attitude is 90 °, and the maximum angle that rear power unit 6 upwards verts from level attitude is 30 °.
Advantage of the present invention is: the improvement layout that has proposed a kind of tiltrotor aircraft, the aerodynamic interference that before and after eliminating, the wing exists in flight course, do not need conventional primary control surface and stabilator can maintain attitude and the control of flight, simplified aircaft configuration, alleviated aircraft weight.
Accompanying drawing explanation
Fig. 1 is present a kind of schematic layout pattern that can tiltrotor aircraft.
Fig. 2 is schematic layout pattern of the present invention.In figure, the axis of four power units is all horizontal.
Fig. 3 is schematic layout pattern of the present invention.In figure, two front power unit axis are all in vertical position, and front power unit rotor upwards; After two, power unit axis is all in vertical position, and rear power unit rotor is downward.
The specific embodiment
Below the present invention is described in further detail.Referring to Fig. 2,3, a tilting rotor small aircraft, comprises fuselage 1, wing 5 and four power units that structure is identical, and wing 5 is connected to integral body with fuselage 1, four power units are arranged on wing 5, and each power unit is comprised of rotor, driving engine and inclining rotary mechanism; It is characterized in that: said wing 5 is a straight high mounted wing, selectable, that wing 5 also can be designed to is as required trapezoidal, sweepback, sweepforward or other forms; Four power units are divided into two groups, first group is front power unit group, it is comprised of two front power units 7, the fixed end of front power unit inclining rotary mechanism 7c in front power unit 7 is connected with the leading edge of wing 5, two front power units 7 are symmetrical with respect to the plane of symmetry of aircraft, the end that verts of front power unit inclining rotary mechanism 7c is connected with driving engine 7b, and front power unit rotor 7a is arranged on the output shaft of front power unit driving engine 7b, and front power unit rotor 7a is for drawing in oar; Second group is rear power unit group, it is comprised of power unit 6 after two, the fixed end of rear power unit inclining rotary mechanism 6c in rear power unit 6 is connected with the trailing edge of wing 5, after two, power unit 6 is symmetrical with respect to the plane of symmetry of aircraft, the end that verts of rear power unit inclining rotary mechanism 6c is connected with rear power unit driving engine 6b, rear power unit rotor 6a is arranged on the output shaft of driving engine, and rear power unit rotor 6a is for advancing oar; When after two front power units 7 and two, the axis of power unit 6 is all in level attitude or is all in upright position, two front power units 7 are parallel with the axis of power unit 6 after two, front power unit inclining rotary mechanism 7c can drive front power unit 7 to rotate, rear power unit inclining rotary mechanism 6c can drive rear power unit 6 to rotate, the maximum angle that front power unit 7 upwards verts from level attitude is 90 °, and the maximum angle that front power unit 7 verts downwards from level attitude is 30 °; The maximum angle that rear power unit 6 verts downwards from level attitude is 90 °, and the maximum angle that rear power unit 6 upwards verts from level attitude is 30 °.
Principle of work of the present invention is: four rotors measure-alike.The hand of rotation of two front power unit rotor 7a is contrary; After two, the hand of rotation of power unit rotor 6a is contrary; Be positioned at the front power unit 7a of fuselage plane of symmetry the same side contrary with the hand of rotation of rear power unit 6a.
When current power unit 7 and rear power unit 6 are all positioned at horizontal direction, front power unit rotor 7a is vertical with gravity direction with pulling force/thrust that rear power unit rotor 6a produces, and can realize and can tilting rotor small aircraft in the mode of similar conventional fixed wing aircraft, complete landing and flight.Under described model of flight, two front power units 7 vert in the same way and after two power unit 6 do not vert, or after two, power unit 6 verts and two front power units 7 do not vert in the same way, and tilt angle (direction vector of pulling force/thrust and the angle of horizontal surface) is less than ± and 30 ° time, two power units of the side of verting can be for providing pitching trim and control torque by tilting rotor small aircraft.Two front power units 7 oppositely vert and after two power unit 6 do not vert, or after two, power unit 6 oppositely verts and two front power units 7 do not vert, and tilt angle (direction vector of pulling force/thrust and the angle of horizontal surface) is less than ± and 30 ° time, two power units of the side of verting can be for providing rolling trim and control torque by tilting rotor small aircraft.The front power unit rotor 7a differential of two front power units 7 rotate or two after the rear power unit rotor 6a differential of power unit 6 rotate, pulling force/the thrust producing due to slow-revving rotor is less, pulling force/thrust that high-revolving rotor produces is larger, can be for providing driftage trim and control torque by tilting rotor small aircraft.Especially, when adopted rotor self rotor inertia is larger, when producing yawing moment, also can induce can tilting rotor small aircraft generation rolling, therefore need to adopt the less rotor of rotation rotor inertia, or go off course utilize homonymy rotor when controlling oppositely vert to suppress being cross-linked of driftage and rolling.
Current power unit 7 upwards verts, rear power unit 6 verts downwards, and when tilt angle (direction vector of pulling force/thrust and the angle of horizontal surface) equals 90 °, pulling force/thrust that front power unit rotor 7a and rear power unit rotor 6a produce will completely for overcoming gravity, and then the vertical takeoff and landing that realization can tilting rotor small aircraft.Under described model of flight, after two front power unit rotor 7a and two, power unit rotor 6a improves rotating speed simultaneously, and the lift that rotor produces is greater than gravity that can tilting rotor small aircraft, can move vertically upward by tilting rotor small aircraft; After two front power unit rotor 7a and two, power unit rotor 6a reduces rotating speed simultaneously, and the lift that rotor produces is less than gravity that can tilting rotor small aircraft, can move vertically downward by tilting rotor small aircraft; Reduce the front power unit rotor 7a that is positioned at fuselage 1 plane of symmetry one side and the rotating speed that is positioned at the rear power unit rotor 6a of fuselage 1 plane of symmetry opposite side, while increasing the rotating speed of two other power unit rotor, can realize control that can the yawing rotation of tilting rotor small aircraft simultaneously; After increasing/reduce by two front power unit rotor 7a or two during the rotating speed of power unit rotor 6a, can realize control that can the luffing of tilting rotor small aircraft; When increase/reduce be positioned at front power unit rotor 7a of fuselage plane of symmetry homonymy and one after during the rotating speed of power unit rotor 6a, can realize control that can tilting rotor small aircraft rolling movement;
Current power unit 7 upwards verts, rear power unit 6 verts downwards, and when tilt angle (direction vector of pulling force/thrust and the angle of horizontal surface) is less than 90 °, a part for pulling force/thrust that front power unit rotor 7a and rear power unit rotor 6a produce is assigned to the direction at gravity place, can realize can tilting rotor small aircraft short take-off and landing (STOL), the needed landing airdrome length of landing reduces with the increase of the tilt angle of power unit; The required power providing in process medium power unit that simultaneously can tilting rotor small aircraft takes off/land also increases with the increase of power unit tilt angle.
Claims (1)
- One kind can tilting rotor small aircraft, comprise fuselage (1), wing and four power units that structure is identical, wing and fuselage (1) are connected to integral body, and four power units are arranged on wing, and each power unit is comprised of rotor, driving engine and inclining rotary mechanism; It is characterized in that: said wing is a straight high mounted wing; Four power units are divided into two groups, first group is front power unit group, it is comprised of two front power units (7), the fixed end of the front power unit inclining rotary mechanism (7c) in front power unit (7) is connected with the leading edge of wing (5), two front power units (7) are symmetrical with respect to the plane of symmetry of aircraft, the end that verts of front power unit inclining rotary mechanism (7c) is connected with driving engine (7b), front power unit rotor (7a) is arranged on the output shaft of front power unit driving engine (7b), and front power unit rotor (7a) is for drawing in oar; Second group is rear power unit group, it is comprised of power unit (6) after two, the fixed end of the rear power unit inclining rotary mechanism (6c) in rear power unit (6) is connected with the trailing edge of wing (5), power unit after two (6) is symmetrical with respect to the plane of symmetry of aircraft, the end that verts of rear power unit inclining rotary mechanism (6c) is connected with rear power unit driving engine (6b), rear power unit rotor (6a) is arranged on the output shaft of driving engine, and rear power unit rotor (6a) is for advancing oar; When after two front power units (7) and two, the axis of power unit (6) is all in level attitude or is all in upright position, two front power units (7) are parallel with the axis of power unit (6) after two; Front power unit inclining rotary mechanism (7c) can drive front power unit (7) to rotate, rear power unit inclining rotary mechanism (6c) can drive rear power unit (6) to rotate, the maximum angle that front power unit (7) upwards verts from level attitude is 90 °, and the maximum angle that front power unit (7) verts downwards from level attitude is 30 °; The maximum angle that rear power unit (6) verts downwards from level attitude is 90 °, and the maximum angle that rear power unit (6) upwards verts from level attitude is 30 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310564111.0A CN103587683A (en) | 2013-11-13 | 2013-11-13 | Small-sized aircraft with tiltable rotor wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310564111.0A CN103587683A (en) | 2013-11-13 | 2013-11-13 | Small-sized aircraft with tiltable rotor wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103587683A true CN103587683A (en) | 2014-02-19 |
Family
ID=50078070
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310564111.0A Pending CN103587683A (en) | 2013-11-13 | 2013-11-13 | Small-sized aircraft with tiltable rotor wings |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103587683A (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738496A (en) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
| CN103935509A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilted four-rotor aircraft cooperative lifting and transporting device |
| CN104058093A (en) * | 2014-06-20 | 2014-09-24 | 吴智勇 | Novel tiltable rotor wing vertical take-off and landing plane |
| CN104626904A (en) * | 2015-02-24 | 2015-05-20 | 丁乃祥 | Multifunctional flying saucer |
| GB2521216A (en) * | 2013-12-16 | 2015-06-17 | Hung-Fu Lee | Helicopter with H-pattern structure |
| CN105480416A (en) * | 2016-01-18 | 2016-04-13 | 南京信息工程大学 | Unmanned aerial vehicle with tilted rotors |
| CN105667780A (en) * | 2016-04-14 | 2016-06-15 | 刘海涛 | Multi-rotor aircraft |
| CN105711834A (en) * | 2016-02-02 | 2016-06-29 | 深圳市高端玩具有限公司 | Rotor wing propelling vertical takeoff type glider and flying control method thereof |
| CN107054634A (en) * | 2017-03-23 | 2017-08-18 | 沈阳无距科技有限公司 | Multiaxis unmanned plane |
| EP3466813A1 (en) * | 2017-10-04 | 2019-04-10 | Bell Helicopter Textron Inc. | Tiltrotor aircraft having interchangeable payload modules |
| JP2020040660A (en) * | 2014-03-18 | 2020-03-19 | ジョビー エイビエイション インクＪｏｂｙ Ａｖｉａｔｉｏｎ， Ｉｎｃ． | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
| US10676188B2 (en) | 2017-10-04 | 2020-06-09 | Textron Innovations Inc. | Tiltrotor aircraft having a downwardly tiltable aft rotor |
| CN112744352A (en) * | 2021-02-07 | 2021-05-04 | 之江实验室 | Distributed tilting multi-rotor aircraft and flight control method |
| EP3998209A1 (en) * | 2021-03-05 | 2022-05-18 | Lilium eAircraft GmbH | Wing and engine structure for a vertical take-off and landing aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030094537A1 (en) * | 2000-07-28 | 2003-05-22 | Austen-Brown John Frederick | Personal hoverplane with four tiltmotors |
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| RU2448869C1 (en) * | 2010-12-03 | 2012-04-27 | Дмитрий Сергеевич Дуров | Multipurpose multi-tiltrotor helicopter-aircraft |
| US20120261523A1 (en) * | 2010-10-06 | 2012-10-18 | Donald Orval Shaw | Aircraft with Wings and Movable Propellers |
| CN103043212A (en) * | 2011-10-17 | 2013-04-17 | 田瑜 | Combined aircraft composed of fixed wing and electric multi-rotor wing |
-
2013
- 2013-11-13 CN CN201310564111.0A patent/CN103587683A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030094537A1 (en) * | 2000-07-28 | 2003-05-22 | Austen-Brown John Frederick | Personal hoverplane with four tiltmotors |
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| US20120261523A1 (en) * | 2010-10-06 | 2012-10-18 | Donald Orval Shaw | Aircraft with Wings and Movable Propellers |
| RU2448869C1 (en) * | 2010-12-03 | 2012-04-27 | Дмитрий Сергеевич Дуров | Multipurpose multi-tiltrotor helicopter-aircraft |
| CN103043212A (en) * | 2011-10-17 | 2013-04-17 | 田瑜 | Combined aircraft composed of fixed wing and electric multi-rotor wing |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2521216A (en) * | 2013-12-16 | 2015-06-17 | Hung-Fu Lee | Helicopter with H-pattern structure |
| GB2521216B (en) * | 2013-12-16 | 2018-05-23 | Hung Fu Lee | Helicopter with H-pattern structure |
| CN103738496A (en) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
| JP2020040660A (en) * | 2014-03-18 | 2020-03-19 | ジョビー エイビエイション インクＪｏｂｙ Ａｖｉａｔｉｏｎ， Ｉｎｃ． | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
| CN103935509B (en) * | 2014-04-15 | 2016-06-29 | 西安交通大学 | One vert quadrotor coordinate hoisting transportation device |
| CN103935509A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilted four-rotor aircraft cooperative lifting and transporting device |
| CN104058093A (en) * | 2014-06-20 | 2014-09-24 | 吴智勇 | Novel tiltable rotor wing vertical take-off and landing plane |
| CN104626904A (en) * | 2015-02-24 | 2015-05-20 | 丁乃祥 | Multifunctional flying saucer |
| CN105480416A (en) * | 2016-01-18 | 2016-04-13 | 南京信息工程大学 | Unmanned aerial vehicle with tilted rotors |
| CN105711834A (en) * | 2016-02-02 | 2016-06-29 | 深圳市高端玩具有限公司 | Rotor wing propelling vertical takeoff type glider and flying control method thereof |
| CN105667780A (en) * | 2016-04-14 | 2016-06-15 | 刘海涛 | Multi-rotor aircraft |
| CN107054634A (en) * | 2017-03-23 | 2017-08-18 | 沈阳无距科技有限公司 | Multiaxis unmanned plane |
| US10618656B2 (en) | 2017-10-04 | 2020-04-14 | Textron Innovations Inc. | Tiltrotor aircraft having interchangeable payload modules |
| EP3564123A1 (en) * | 2017-10-04 | 2019-11-06 | Bell Helicopter Textron Inc. | Tiltrotor aircraft having interchangeable payload modules |
| CN109606673A (en) * | 2017-10-04 | 2019-04-12 | 贝尔直升机德事隆公司 | Tilting rotor formula aircraft with interchangeable payload module |
| EP3466813A1 (en) * | 2017-10-04 | 2019-04-10 | Bell Helicopter Textron Inc. | Tiltrotor aircraft having interchangeable payload modules |
| US10676188B2 (en) | 2017-10-04 | 2020-06-09 | Textron Innovations Inc. | Tiltrotor aircraft having a downwardly tiltable aft rotor |
| US11198509B2 (en) | 2017-10-04 | 2021-12-14 | Textron Innovations Inc. | Tiltrotor aircraft having tiltable forward and aft rotors |
| US11492116B2 (en) | 2017-10-04 | 2022-11-08 | Textron Innovations Inc. | Tiltrotor aircraft having tiltable forward and aft rotors |
| CN112744352A (en) * | 2021-02-07 | 2021-05-04 | 之江实验室 | Distributed tilting multi-rotor aircraft and flight control method |
| CN112744352B (en) * | 2021-02-07 | 2022-03-15 | 之江实验室 | Distributed tilting multi-rotor aircraft and flight control method |
| EP3998209A1 (en) * | 2021-03-05 | 2022-05-18 | Lilium eAircraft GmbH | Wing and engine structure for a vertical take-off and landing aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| CN106864746A (en) | It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN201712787U (en) | Electric tilt rotor unmanned aircraft | |
| CN108528692B (en) | Folding wing dual-rotor aircraft and control method thereof | |
| CN106938701A (en) | It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula four | |
| CN105083551A (en) | Tilt rotary-wing aircraft and control method thereof | |
| CN205022861U (en) | VTOL fixed wing aircraft | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| CN101879945A (en) | Electric tilting rotor wing unmanned aerial vehicle | |
| CN106927040A (en) | It is a kind of can VTOL the rotor tailless configuration aircraft of tailstock formula four | |
| CN105480416A (en) | Unmanned aerial vehicle with tilted rotors | |
| CN106915459A (en) | A kind of hybrid tilting rotor wing unmanned aerial vehicle | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN103158856A (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN205661659U (en) | Electronic multiaxis rotor unmanned aerial vehicle system of verting | |
| CN107352029A (en) | A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system | |
| CN105460215A (en) | Fixed-wing air vehicle achieving vertical or short-distance take-off and landing | |
| CN206327567U (en) | A kind of compound unmanned vehicle | |
| CN206187340U (en) | Aircraft | |
| CN103754360A (en) | Similar flying saucer type rotaplane | |
| CN105173076A (en) | VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) | |
| CN106828919A (en) | It is a kind of can VTOL the coaxial Fan Jiang tailless configurations aircraft of tailstock formula | |
| CN112027073A (en) | Combined type tilting wing longitudinal rotation double-rotor aircraft | |
| CN105346725A (en) | Vertical take-off and landing unmanned aerial vehicle |
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 | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140219 |