CN103332293A - Tilting double-duct subminiature unmanned plane - Google Patents
Tilting double-duct subminiature unmanned plane Download PDFInfo
- Publication number
- CN103332293A CN103332293A CN2013102326538A CN201310232653A CN103332293A CN 103332293 A CN103332293 A CN 103332293A CN 2013102326538 A CN2013102326538 A CN 2013102326538A CN 201310232653 A CN201310232653 A CN 201310232653A CN 103332293 A CN103332293 A CN 103332293A
- Authority
- CN
- China
- Prior art keywords
- duct
- tilting
- fuselage
- aircraft
- formula fan
- 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
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
The invention discloses a tilting double-duct subminiature unmanned plane adopting a vector boosting principle. The tilting double-duct subminiature unmanned plane is characterized in that a central inner cavity of a machine body is provided with a control system of the whole aircraft, double-duct fan aircrafts are connected with a machine body through a tilting shaft and are symmetrically distributed on the two sides of the machine body; and duct tilting mechanisms are distributed at positions of the machine body connected with the tilting shaft, a lifting frame is arranged below the machine body, and the duct tilting mechanisms and the duct fan aircrafts are respectively connected with a flight control system. The tilting double-duct subminiature unmanned plane provided by the invention has the advantages that left and right ducts are symmetrically distributed relative to the machine body, so as to respectively generate pull force for enabling the aircrafts to ascend, the left and right ducts can rotate relative to the machine body under the control of the tilting system, so that the aircrafts can change postures conveniently; since the ducts adopt rotor ring design, the plane has higher flying efficiency and higher safety; and the tilting double-duct subminiature unmanned plane has wide application prospect in the fields such as low-altitude reconnaissance and atmospheric environmental monitoring under complex environment in a city.
Description
Technical field
The present invention relates to a kind of micro-miniature flying robot, particularly the two duct micro-miniature unmanned planes of a kind of tilting type.
Background technology
Unmanned Aircraft Systems (UAS) has that cost is low, volume is little, easy to carry, advantage such as the landing place of taking off is little, and have certain load-carrying capacity and a wind loading rating, therefore, extra small unmanned plane is used very extensive in fields such as anti-terrorism, fire-fighting, the disaster relief, aerological sounding, Environmental Studies, traffic patrolling and supervision of the cities.
At present, the micro-miniature unmanned plane of comparative maturity mainly contains fixed-wing and two kinds of versions of rotor, two kinds of micro-miniature unmanned planes have different characteristics, for example, fixed-wing micro-miniature unmanned plane have flying speed soon, advantage such as highly high, distance, but manoevreability exists not enough, in addition, also needs broad taking off and landing platform.Rotor micro-miniature unmanned plane has good maneuvering performance, and hover in the low latitude of can realizing fixing a point, can carry out the low-latitude flying operation of various complexity, but the micro-miniature unmanned plane rotor size of rotor is big, rotating speed is high, and maneuvering system is also complicated, belong to single failpoint system, abnormally dangerous during operation, especially in the city operation of crowd than comparatively dense.
So along with the demand of numerous areas to the micro-miniature Unmanned Aircraft Systems (UAS) constantly increases, and existing micro-miniature unmanned plane type is used and also had problems, be difficult to satisfy actual application requirements in complex environments such as city.Therefore, carry out the research of novel micro-miniature Unmanned Aircraft Systems (UAS), not only be with a wide range of applications, and have important scientific meaning.
And in recent years, many research institutions carry out the research of course of new aircraft, a lot of aircraft types have been researched and developed, wherein tilt rotor aircraft and duct formula fan aircraft are two relatively successful research directions, more successful case is all arranged, have higher reference function for the research of novel micro-miniature Unmanned Aircraft Systems (UAS).
The tilt rotor aircraft housing construction is the same with conventional airplane, but the wing tip at aircraft both sides wing is symmetrically installed with engine nacelle and the rotor that can vert, this aircraft both can have functions such as autogyro vertical and landing takeoff, the characteristics such as high-speed flight that can have fixed-wing are arranged, but it also exists some problems, the steering unit complexity of wing wing tip rotor system for example, control is difficulty, two air-flow meeting phase mutual interference that rotor system produces, especially when descending at a high speed, disturb bigger, when taking off vertically, aircraft pitch control is provided by rotor fully, and driving efficiency is low etc.
The principal character of duct formula fan aircraft is that dress fan system in the by-pass air duct adopts duct vector principle of propeller to realize the posture changing of Unmanned Aircraft Systems (UAS), and then realizes the various state of flights of Unmanned Aircraft Systems (UAS).This structure aircraft has many advantages, for example, fan is surrounded by duct, and system safety improves greatly, and the slurry point eddy current that the package action of duct has intercepted blade forms, reduce the loss, obtain higher thrust-weight ratio, thereby can carry heavier load, improved efficient, this aircraft has compact conformation in addition, advantage such as be easy to carry about with one, so duct formula fan aircraft can be widely used in the various operations in the complex environment; But also there are some problems in duct formula fan aircraft, duct formula fan vector propulsion system is to have increased the control blade on the basis of duct formula fan system, the obstruction of control blade rudder face the fan blade wake, wake flow is deflected, make the aerodynamic force of duct and body that complicated the variation be taken place thereupon, causing total system to start complexity increases greatly.Therefore, can't obtain relatively accurately math modeling by the method for Analysis on Mechanism.
Summary of the invention
At the defective that prior art exists, the purpose of this invention is to provide the two duct micro-miniature unmanned planes of a kind of tilting type.On the basis to tilt rotor aircraft and two kinds of course of new aircraft analyses of duct formula fan aircraft, in conjunction with both advantages, study a kind of course of new aircraft type, to solve two rotor interferences in air flow of existing tilt rotor aircraft, problems such as the low and safety of efficient, and problems such as the pneumatic complexity of existing duct aircraft vector propulsion system have been improved, and it is serious to have overcome traditional unmanned helicopter flight control coupling, rotor blade exposes and causes poor stability, and noise is big, a series of problems such as cost height, and based on aircraft being carried out the research of micro-miniature Unmanned Aircraft Systems (UAS), finally this micro-miniature Unmanned Aircraft Systems (UAS) is applied to complex environments such as city, such environment requires not high relatively to the flying speed of micro-miniature Unmanned Aircraft Systems (UAS), performances such as the safety of micro-miniature Unmanned Aircraft Systems (UAS) and flight efficiency are then proposed higher requirement.
For achieving the above object, the present invention adopts following technical scheme:
The two duct micro-miniature unmanned planes of a kind of tilting type, comprise fuselage, two duct formula fan aircraft, tiliting axis, rotating mechanism, duct inclining rotary mechanism, alighting gear and flight control system, described fuselage central lumen is equipped with flight control system, described pair of duct formula fan aircraft links to each other with rotating mechanism by tiliting axis, described rotating mechanism is installed on the fuselage, duct formula fan aircraft distributes in the fuselage bilateral symmetry, the duct inclining rotary mechanism links to each other with duct formula fan aircraft, duct formula inclining rotary mechanism is installed on the fuselage, and the fuselage lower end is equipped with alighting gear; Two duct formula fan aircraft, duct inclining rotary mechanism connect flight control system respectively, the two duct formula fan aircraft of two of described left-right symmetric all can be under the control of duct inclining rotary mechanism relatively fuselage carry out front and back and vert, realize flying before the unmanned plane, after fly, left side flight, right side flight and turn and the adjustment air-flow.
The described pair of duct formula fan aircraft comprises by-pass air duct, is fixed on bracing frame, drive motor, the vane sheet mechanism of by-pass air duct inside, and drive motor and vane sheet mechanism all are installed on the bracing frame.
Described rotating mechanism is bearing.
Described duct inclining rotary mechanism is four-bar mechanism, it comprises base, rocking bar, two connecting rods, base is fixed on the fuselage, rocking bar links to each other with base by hinge, two connecting rods are connected by spherical hinge with rocking bar and are symmetrically distributed, and the other end of two connecting rods is connected with duct formula fan aircraft by spherical hinge.
The vane sheet mechanism of described pair of duct formula fan aircraft comprises three vane sheets.
Compared with prior art, the present invention has following outstanding substantive distinguishing features and progressive significantly:
Adopt two relative fuselage symmetric configurations of duct, have good startability; The function that this unmanned plane has the landing of taking off vertically and hovers, and can realize the function that high/low speed moves forward and backward again, have the advantage of depopulated helicopter and fixed-wing unmanned plane concurrently; This unmanned plane also has good aerial gearshift performance, can change or floating state from the high-speed flight state to low-speed condition; Two duct attitude control designs of symmetrical expression, the power system of each duct and control system are independent fully, have overcome the coupled problem of UAV Flight Control, so flight control system has good reliability and stability; In the duct rotor design, whole blades all is placed in the duct, so just improved the safety performance of aircraft flight in complex environment.
Description of drawings
Fig. 1 is structural representation of the present invention.
Fig. 2 is duct formula fan Flight Vehicle Structure scheme drawing.
Fig. 3 is the thin portion structural representation of duct inclining rotary mechanism.
The specific embodiment
As shown in Figure 1, the two duct micro-miniature unmanned planes of a kind of tilting type, comprise fuselage 1, two duct formula fan aircraft 2, tiliting axis 3, rotating mechanism 4, duct inclining rotary mechanism 5, alighting gear 6 and flight control system, described fuselage 1 central lumen is equipped with flight control system, described pair of duct formula fan aircraft 2 links to each other with rotating mechanism 4 by tiliting axis 3, described rotating mechanism 4 is installed on the fuselage 1, duct formula fan aircraft 2 distributes in fuselage 1 bilateral symmetry, duct inclining rotary mechanism 5 links to each other with duct formula fan aircraft 2, duct formula inclining rotary mechanism 5 is installed on the fuselage 1, and fuselage 1 lower end is equipped with alighting gear 6; Two duct formula fan aircraft 2, duct inclining rotary mechanism 5 connect flight control system respectively, the two duct formula fan aircraft 2 of two of described left-right symmetric all can be under 5 controls of duct inclining rotary mechanism relatively fuselage carry out front and back and vert, realize flying before the unmanned plane, after fly, left side flight, right side flight and turn and the adjustment air-flow.
As shown in Figure 2, the described pair of duct formula fan aircraft 2 comprises by-pass air duct 21, is fixed on bracing frame 22, drive motor 23, the vane sheet mechanism 24 of by-pass air duct 21 inside, and drive motor 23 and vane sheet mechanism 24 all are installed on the bracing frame 22.Described rotating mechanism 4 is bearing.
As shown in Figure 3, described duct inclining rotary mechanism 5 is four-bar mechanisms, it comprises base 51, rocking bar 52, two connecting rods 53, base 51 is fixed on the fuselage 1, rocking bar 52 links to each other with base 51 by hinge, two connecting rods 53 are connected by spherical hinge with rocking bar 52 and are symmetrically distributed, and the other end of two connecting rods 53 is connected with duct formula fan aircraft 2 by spherical hinge.
The vane sheet mechanism 24 of described pair of duct formula fan aircraft 2 comprises three vane sheets 25.
What the present invention adopted is the two ducted fan vector principle of propellers of tilting type, and it is as follows that it becomes appearance mechanism:
1, aircraft becomes appearance by system's lift vector variation and produces, and system's lift vector is combined by left and right sides duct pulling force;
2, the relative body lateral variation of variation feasible system lift vector of left and right sides duct pulling force size, and the variation of duct pulling force size is realized by the rotating speed of engine control ducted fan;
3, the relative body of variation feasible system lift vector of left and right sides duct pulling force size vertically changes, and the variation of duct pulling force size is carried out front and back rotation realization by the system's control duct that verts;
Based on above-mentioned change appearance mechanism, unmanned plane of the present invention can be realized the multiple inclination combination of two ducts, for being described below of the three kinds of exemplary operation states of unmanned plane among the present invention:
1, two ducts are with turning forward: about aircraft two ducts with turning forward, the lift vector of two ducts in the same way, and equal directed forward, left and right sides duct pulling force can make aircraft be tilted to preceding flight.
2, two duct differences tilt:, two duct differences tilt about aircraft, and the lift vector of two ducts tilts mutually, can make aircraft to anticlockwise or to right rotation, realizes the turning of aircraft.
3, two ducts are with retreating: two ducts are with retreating about aircraft, and the lift vector of two ducts and all points to the rear in the same way, and left and right sides duct pulling force can make aircraft be tilted to back flight.
Claims (5)
1. two duct micro-miniature unmanned planes of a tilting type, comprise fuselage (1), two duct formula fan aircraft (2), tiliting axis (3), rotating mechanism (4), duct inclining rotary mechanism (5), alighting gear (6) and flight control system, it is characterized in that, described fuselage (1) central lumen is equipped with flight control system, described pair of duct formula fan aircraft (2) links to each other with rotating mechanism (4) by tiliting axis (3), described rotating mechanism (4) is installed on the fuselage (1), duct formula fan aircraft (2) distributes in fuselage (1) bilateral symmetry, duct inclining rotary mechanism (5) links to each other with duct formula fan aircraft (2), duct formula inclining rotary mechanism (5) is installed on the fuselage (1), and fuselage (1) lower end is equipped with alighting gear (6); Two duct formula fan aircraft (2), duct inclining rotary mechanism (5) connect flight control system respectively, the two duct formula fan aircraft (2) of two of described left-right symmetric all can duct inclining rotary mechanism (5) control down relative fuselage carry out front and back and vert, realize flying before the unmanned plane, after fly, left side flight, right side flight and turning and adjustment air-flow.
2. two duct micro-miniature unmanned planes of tilting type according to claim 1, it is characterized in that, described pair of duct formula fan aircraft (2) comprises by-pass air duct (21), is fixed on by-pass air duct (21) inner bracing frame (22), drive motor (23), vane sheet mechanism (24), and drive motor (23) and vane sheet mechanism (24) all are installed on the bracing frame (22).
3. the two duct micro-miniature unmanned planes of tilting type according to claim 1 is characterized in that described rotating mechanism (4) is bearing.
4. two duct micro-miniature unmanned planes of tilting type according to claim 1, it is characterized in that, described duct inclining rotary mechanism (5) is four-bar mechanism, it comprises base (51), rocking bar (52), two connecting rods (53), base (51) is fixed on the fuselage (1), rocking bar (52) links to each other with base (51) by hinge, two connecting rods (53) are connected by spherical hinge with rocking bar (52) and are symmetrically distributed, and the other end of two connecting rods (53) is connected with duct formula fan aircraft (2) by spherical hinge.
5. the two duct micro-miniature unmanned planes of tilting type according to claim 1 and 2 is characterized in that the vane sheet mechanism (24) of described pair of duct formula fan aircraft (2) comprises three vane sheets (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102326538A CN103332293A (en) | 2013-06-13 | 2013-06-13 | Tilting double-duct subminiature unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2013102326538A CN103332293A (en) | 2013-06-13 | 2013-06-13 | Tilting double-duct subminiature unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103332293A true CN103332293A (en) | 2013-10-02 |
Family
ID=49240523
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013102326538A Pending CN103332293A (en) | 2013-06-13 | 2013-06-13 | Tilting double-duct subminiature unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103332293A (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104044742A (en) * | 2014-05-05 | 2014-09-17 | 北京理工大学 | Bypass type vector thrust device suitable for small unmanned aerial vehicle |
| CN105292466A (en) * | 2015-11-06 | 2016-02-03 | 东莞华南设计创新院 | Differential motion vector propulsion servo system |
| CN106114852A (en) * | 2016-06-29 | 2016-11-16 | 饶大林 | A kind of cross-arranging type dual-culvert vertical take-off and landing Spacecraft Attitude Control |
| CN106347655A (en) * | 2016-09-11 | 2017-01-25 | 珠海市磐石电子科技有限公司 | Duct power device and aircraft |
| CN107521665A (en) * | 2017-09-08 | 2017-12-29 | 中国民航大学 | Aerial turbo fan engine bilayer " D " shape nozzle |
| CN107585294A (en) * | 2016-07-08 | 2018-01-16 | 袁洪跃 | A kind of interior rotor craft structure |
| CN108622422A (en) * | 2018-05-08 | 2018-10-09 | 成都军融项目管理有限公司 | A kind of aircraft system promoting angle regulating function with propeller |
| CN108791874A (en) * | 2018-06-21 | 2018-11-13 | 南京航空航天大学 | A kind of tilting duct power unmanned vehicle |
| CN109367762A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | Tilting duct aircraft auxiliary rudder surface control device |
| WO2019047429A1 (en) * | 2017-09-05 | 2019-03-14 | 北京工业大学 | Multi-rotor unmanned aerial vehicle-based duct propulsion system |
| WO2019073417A1 (en) * | 2017-10-11 | 2019-04-18 | Hangzhou Zero Zero Technology Co., Ltd. | Aerial system including foldable frame architecture |
| WO2019073415A1 (en) * | 2017-10-11 | 2019-04-18 | Hangzhou Zero Zero Technology Co., Ltd. | Aerial system including foldable frame architecture |
| CN110254703A (en) * | 2019-06-28 | 2019-09-20 | 福州大学 | One kind DCB Specimen that verts hovers T-type UAV system automatically |
| CN110723288A (en) * | 2019-10-22 | 2020-01-24 | 北京深醒科技有限公司 | Small aircraft capable of being used for security patrol |
| CN112009680A (en) * | 2020-08-26 | 2020-12-01 | 中国民航大学 | Double-duct fan vertical take-off and landing aircraft |
| CN112337003A (en) * | 2020-10-23 | 2021-02-09 | 李庆磊 | Unmanned fire control unit based on 5G network |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101857086A (en) * | 2010-06-03 | 2010-10-13 | 哈尔滨盛世特种飞行器有限公司 | Dual-culvert vertical take-off and landing unmanned aerial vehicle |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
| CN202080435U (en) * | 2011-05-12 | 2011-12-21 | 张思远 | Ranked dual-rotor vertically-lifted unmanned aerial vehicle (UAV) |
| CN102363445A (en) * | 2011-06-21 | 2012-02-29 | 杨朝习 | Tilting dynamic vertical take-off and landing land-air amphibious aircraft |
| CN202319771U (en) * | 2011-11-07 | 2012-07-11 | 上海工程技术大学 | Air-land dual-purpose aircraft |
| CN202863763U (en) * | 2012-11-10 | 2013-04-10 | 柴睿 | Longitudinal-row double-duct rotary-wing single/double-person flying motorcycle |
-
2013
- 2013-06-13 CN CN2013102326538A patent/CN103332293A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101857086A (en) * | 2010-06-03 | 2010-10-13 | 哈尔滨盛世特种飞行器有限公司 | Dual-culvert vertical take-off and landing unmanned aerial vehicle |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
| CN202080435U (en) * | 2011-05-12 | 2011-12-21 | 张思远 | Ranked dual-rotor vertically-lifted unmanned aerial vehicle (UAV) |
| CN102363445A (en) * | 2011-06-21 | 2012-02-29 | 杨朝习 | Tilting dynamic vertical take-off and landing land-air amphibious aircraft |
| CN202319771U (en) * | 2011-11-07 | 2012-07-11 | 上海工程技术大学 | Air-land dual-purpose aircraft |
| CN202863763U (en) * | 2012-11-10 | 2013-04-10 | 柴睿 | Longitudinal-row double-duct rotary-wing single/double-person flying motorcycle |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104044742B (en) * | 2014-05-05 | 2016-04-27 | 北京理工大学 | Be applicable to the culvert type vectored thrust device of SUAV (small unmanned aerial vehicle) |
| CN104044742A (en) * | 2014-05-05 | 2014-09-17 | 北京理工大学 | Bypass type vector thrust device suitable for small unmanned aerial vehicle |
| CN105292466A (en) * | 2015-11-06 | 2016-02-03 | 东莞华南设计创新院 | Differential motion vector propulsion servo system |
| CN106114852A (en) * | 2016-06-29 | 2016-11-16 | 饶大林 | A kind of cross-arranging type dual-culvert vertical take-off and landing Spacecraft Attitude Control |
| CN107585294A (en) * | 2016-07-08 | 2018-01-16 | 袁洪跃 | A kind of interior rotor craft structure |
| CN106347655A (en) * | 2016-09-11 | 2017-01-25 | 珠海市磐石电子科技有限公司 | Duct power device and aircraft |
| CN106347655B (en) * | 2016-09-11 | 2019-11-29 | 珠海市磐石电子科技有限公司 | A kind of duct power device and aircraft |
| WO2019047429A1 (en) * | 2017-09-05 | 2019-03-14 | 北京工业大学 | Multi-rotor unmanned aerial vehicle-based duct propulsion system |
| CN107521665A (en) * | 2017-09-08 | 2017-12-29 | 中国民航大学 | Aerial turbo fan engine bilayer " D " shape nozzle |
| US10974825B2 (en) | 2017-10-11 | 2021-04-13 | Hangzhou Zero Zero Technology Co., Ltd . | Aerial system including foldable frame architecture |
| WO2019073417A1 (en) * | 2017-10-11 | 2019-04-18 | Hangzhou Zero Zero Technology Co., Ltd. | Aerial system including foldable frame architecture |
| WO2019073415A1 (en) * | 2017-10-11 | 2019-04-18 | Hangzhou Zero Zero Technology Co., Ltd. | Aerial system including foldable frame architecture |
| US11267568B2 (en) | 2017-10-11 | 2022-03-08 | Hangzhou Zero Zero Technology Co., Ltd. | Aerial system including foldable frame architecture |
| CN108622422A (en) * | 2018-05-08 | 2018-10-09 | 成都军融项目管理有限公司 | A kind of aircraft system promoting angle regulating function with propeller |
| CN108791874A (en) * | 2018-06-21 | 2018-11-13 | 南京航空航天大学 | A kind of tilting duct power unmanned vehicle |
| CN109367762A (en) * | 2018-10-17 | 2019-02-22 | 江西洪都航空工业集团有限责任公司 | Tilting duct aircraft auxiliary rudder surface control device |
| CN110254703A (en) * | 2019-06-28 | 2019-09-20 | 福州大学 | One kind DCB Specimen that verts hovers T-type UAV system automatically |
| CN110254703B (en) * | 2019-06-28 | 2023-09-12 | 福州大学 | Tilting double-rotor wing automatic hovering T-shaped unmanned aerial vehicle system |
| CN110723288A (en) * | 2019-10-22 | 2020-01-24 | 北京深醒科技有限公司 | Small aircraft capable of being used for security patrol |
| CN112009680A (en) * | 2020-08-26 | 2020-12-01 | 中国民航大学 | Double-duct fan vertical take-off and landing aircraft |
| CN112009680B (en) * | 2020-08-26 | 2022-11-01 | 中国民航大学 | Double-duct fan vertical take-off and landing aircraft |
| CN112337003A (en) * | 2020-10-23 | 2021-02-09 | 李庆磊 | Unmanned fire control unit based on 5G network |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103332293A (en) | Tilting double-duct subminiature unmanned plane | |
| CN107839875B (en) | Wing extension winglet for tiltrotor aircraft | |
| CN205707297U (en) | Fixed-wing unmanned plane | |
| CN103144769B (en) | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct | |
| CN202754143U (en) | Rotating engine vertical take-off and landing aircraft | |
| US10005554B2 (en) | Unmanned aerial vehicle | |
| CN204452934U (en) | The double mode aircraft of rotor, fixed-wing | |
| CN103979104B (en) | One can variant X-type wing vertical landing minute vehicle | |
| CN104743112B (en) | Novel tilt wing aircraft | |
| CN204750564U (en) | Three rotor VTOL unmanned aerial vehicle on Y type | |
| CN111332465B (en) | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode | |
| CN202011472U (en) | Tilting duct unmanned aerial vehicle | |
| CN102120489A (en) | Tilt ducted unmanned aerial vehicle | |
| CN105083550A (en) | Fixed-wing aircraft realizing vertical take-off and landing | |
| CN205022862U (en) | Power device and fixed wing aircraft with mechanism of verting | |
| CN112937849A (en) | Vertical take-off and landing aircraft with combined layout of tilting type propeller and fixed propeller | |
| CN113212753A (en) | Imitative dragonfly multi-mode conversion microminiature unmanned aerial vehicle of upset airfoil | |
| CN107878747B (en) | Fixed wing aircraft capable of taking off and landing vertically | |
| CN103754360B (en) | One kind flying disc type gyroplane | |
| CN205396534U (en) | Rotor unmanned aerial vehicle verts | |
| CN105173076B (en) | A kind of vertical take-off and landing drone | |
| CN113371190A (en) | Combined type high-speed helicopter based on conventional rotor wing configuration | |
| CN206719540U (en) | Tilting rotor type VUAV based on Flying-wing | |
| US20200391859A1 (en) | Vtol aircraft with leading edge tilting ducted fans | |
| CN211281472U (en) | Duct tail sitting posture VTOL unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into 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: 20131002 |