CN108569399B - Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power - Google Patents
Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power Download PDFInfo
- Publication number
- CN108569399B CN108569399B CN201810315808.7A CN201810315808A CN108569399B CN 108569399 B CN108569399 B CN 108569399B CN 201810315808 A CN201810315808 A CN 201810315808A CN 108569399 B CN108569399 B CN 108569399B
- Authority
- CN
- China
- Prior art keywords
- wing
- unmanned aerial
- aerial vehicle
- wings
- duct 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.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/08—Aircraft not otherwise provided for having multiple wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/60—Take-off or landing of UAVs from a runway using their own power
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Wind Motors (AREA)
- Supply And Distribution Of Alternating Current (AREA)
Abstract
The invention provides a short-distance take-off and landing unmanned aerial vehicle adopting distributed duct power, and relates to the technical field of unmanned aerial vehicles, wherein two fuselages are provided, front wings are communicated and cross the front parts of the two fuselages, rear wings are communicated and cross the tail parts of the two fuselages, and vertical tail wings are respectively arranged right above the tail parts of the two fuselages; the pneumatic efficiency of the wing is improved by sucking the boundary layer on the upper surface of the wing through the duct power set distributed on the upper surface of the wing trailing edge flap; the distributed arrangement of the power system avoids the problem that the unmanned aerial vehicle is out of control due to the failure of a single engine, and improves the safety of the unmanned aerial vehicle; the trailing edge flap drives the ducted power unit to deflect and change the thrust direction, so that the sliding distance of the unmanned aerial vehicle in the take-off and landing stage is shortened, the take-off and landing performance of the unmanned aerial vehicle is improved, and the application range of the unmanned aerial vehicle is expanded.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a short-distance take-off and landing unmanned aerial vehicle.
Background
At present unmanned aerial vehicle's power form mainly divide into oil and moves and electronic two kinds, and oil moves unmanned aerial vehicle duration but the weight of engine, vibrations and noise are all very big for a long time to the tail gas of emission can cause the pollution to the environment. The electric unmanned aerial vehicle is green and clean, light in weight and small in noise, but is limited by the current battery technology level, and driving system power is less and the time of endurance is short. In addition, present unmanned aerial vehicle adopts single shot form more, and the engine is installed in aircraft nose or fuselage afterbody, and the driving system redundancy is low, in case break down very easily leads to unmanned aerial vehicle crash out of control. In order to solve the problems, the Chinese invention patent of the prior patent technology such as application number 201710123934.8 discloses a variant efficient small-sized vertical take-off and landing unmanned aerial vehicle adopting distributed hybrid power, which provides electric energy for propellers distributed on wings by generating electricity through an internal combustion engine, so that the unmanned aerial vehicle has the advantages of both an oil-driven unmanned aerial vehicle and an electric unmanned aerial vehicle. The problem that the single propeller fails to work and the unmanned aerial vehicle is out of control is avoided by adopting a distributed propeller scheme. However, the distributed power system is not favorably coupled with the aerodynamic components such as wings of the unmanned aerial vehicle, so that the aerodynamic efficiency and the propulsion efficiency of the unmanned aerial vehicle are improved.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a short-distance take-off and landing unmanned aerial vehicle adopting distributed duct power, the scheme of an oil-electricity hybrid power system is adopted, the pneumatic layout adopts a double-body serial wing layout mode, duct power sets are distributed on the upper wing surfaces of the trailing edge flaps of front and rear wings, and the pneumatic efficiency and the propulsion efficiency of the unmanned aerial vehicle are improved through the coordinated arrangement of the wings and the duct power sets. The thrust direction of the ducted power group is changed by deflecting the wing trailing edge flaps of the ducted power group to realize the short-distance take-off and landing of the unmanned aerial vehicle.
The technical scheme adopted by the invention for solving the technical problem is as follows:
a short-distance take-off and landing unmanned aerial vehicle adopting distributed duct power comprises two airframes, two front wings, two rear wings, two trailing edge flaps, elevators, ailerons, two front undercarriages, two main undercarriages, two vertical empennages, two rudder, a duct power set and a generator cabin, wherein the distance between the airframes is smaller than the span length of the front wings;
the elevator is arranged at the position of the rear edge of the left and right outer sides of the front wing, the ailerons are arranged at the position of the rear edge of the left and right outer sides of the rear wing, the number of the rear edge flaps is 4, the rear edge flaps are respectively arranged at the position of the rear edge of the inner wing section of the front wing, the position of the rear edge of the inner wing section of the rear wing and the position of the rear edge of the left and right outer wing sections of the rear wing in a hinged mode, the rear edge flaps rotate for 0-90 degrees relative to the wing surfaces of the wings through a driving mechanism in the wings, the rudder is arranged at the rear side of the vertical tail wing, the generator cabin is arranged at the root part of the vertical tail wing, the turbine generator is arranged in the generator cabin, and the turbine engine burns fuel oil to drive the generator to serve as a ducted power group to provide electric energy.
The ducted power unit is total 4 groups, installs respectively at the last airfoil of four trailing edge flaps, and every ducted power unit of group all contains 4 ~ 10 ducted power unit, and every ducted power unit includes duct, motor, electronic governor and screw, and ducted power unit is followed the deflection of trailing edge flaps and is changed thrust direction.
The front wing and the rear wing are in a high-aspect-ratio straight wing form, the aspect ratio is 8-16, the sweepback angle is 0 degree, and the dihedral angle is 0-10 degrees.
The invention adopts the oil-electricity hybrid power scheme to improve the endurance time of the unmanned aerial vehicle and reduce the weight, vibration and oil consumption rate of a power system; the pneumatic efficiency of the wing is improved by the aid of the boundary layer of the upper surface of the suction wing of the ducted power unit distributed on the upper surface of the wing trailing edge flap; the distributed arrangement of the power system avoids the problem that the unmanned aerial vehicle is out of control due to the failure of a single engine, and improves the safety of the unmanned aerial vehicle; the trailing edge flap drives the ducted power unit to deflect and change the thrust direction, so that the sliding distance of the unmanned aerial vehicle in the take-off and landing stage is shortened, the take-off and landing performance of the unmanned aerial vehicle is improved, and the application range of the unmanned aerial vehicle is expanded.
Drawings
Fig. 1 is a schematic structural diagram of an unmanned aerial vehicle in an efficient cruise state;
FIG. 2 is a structural bottom view of the unmanned aerial vehicle in the efficient cruise state;
fig. 3 is a schematic structural view of the unmanned aerial vehicle in a vertical take-off and landing state;
fig. 4 is a structural bottom view of the unmanned aerial vehicle in a vertical take-off and landing state.
In the figure: 1-fuselage, 2-front wing, 3-rear wing, 4-rear edge flap, 5-elevator, 6-aileron, 7-front landing gear, 8-main landing gear, 9-vertical empennage, 10-rudder, 11-duct power unit and 12-generator cabin.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
A short-distance take-off and landing unmanned aerial vehicle adopting distributed duct power comprises two airframes, two front wings, two rear wings, two trailing edge flaps, elevators, ailerons, two front undercarriages, two main undercarriages, two vertical empennages, two rudder, a duct power set and a generator cabin, wherein the distance between the airframes is smaller than the span length of the front wings;
the elevators are arranged at the positions of the rear edges of the left and right outer sides of the front wing and are used for controlling the pitching direction of the unmanned aerial vehicle during taking off and landing and flying; the ailerons are arranged at the rear edge positions of the left and right outer sides of the rear wing and are used for taking off and landing of the unmanned aerial vehicle and rolling operation in flight; the number of the trailing edge flaps is 4, the trailing edge flaps are respectively arranged at the trailing edge position of the inner wing section of the front wing, the trailing edge position of the inner wing section of the rear wing and the trailing edge positions of the left outer wing section and the right outer wing section of the rear wing in a hinged mode, and the trailing edge flaps rotate by 0-90 degrees relative to the wing surfaces of the wings through a driving mechanism in the wings.
The ducted power unit is total 4 groups, installs respectively at the last airfoil of four trailing edge flaps, and every ducted power unit of group all contains 4 ~ 10 ducted power unit, and every ducted power unit includes duct, motor, electronic governor and screw, and ducted power unit is followed the deflection of trailing edge flaps and is changed thrust direction.
And a rudder is arranged on the rear side of the vertical tail wing and is used for controlling the taking-off and landing and the flying course of the unmanned aerial vehicle.
The power generation cabin is arranged at the root part of the vertical tail wing, the turbine generator is arranged in the power generation cabin, and the turbine generator burns fuel oil to drive the power generation machine to provide electric energy as a duct power set arranged on the wing.
The distributed duct power short take-off and landing unmanned aerial vehicle comprises a short take-off stage, an efficient cruise stage and a short landing stage, and the flight process comprises the following steps:
a. in the short takeoff stage, energy storage batteries in the airplane body provide electric energy for four groups of ducted power groups on the front and rear wings, and the four groups of ducted power groups all work in a maximum power state; the control mechanism in the wing drives the trailing edge flaps of the inner wing sections of the front wing and the rear wing and two groups of ducted power sets arranged on the trailing edge flaps to deflect 90 degrees downwards to be vertical to the horizontal plane, so that the thrust in the vertical direction is provided for the unmanned aerial vehicle; two ducted power sets mounted on the trailing edge flaps of the left and right outer wing sections of the rear wing keep horizontal to provide forward thrust for the unmanned aerial vehicle; after the unmanned aerial vehicle climbs to a preset height, the trailing edge flaps of the inner wing sections of the front wing and the rear wing and two groups of ducted power sets arranged on the trailing edge flaps are controlled to deflect to horizontal positions by a control mechanism arranged in the wings, and the four groups of power sets gradually reduce power to power required by cruising.
b. In the efficient cruising stage, a turbine engine in a generator cabin drives a generator to work, one part of generated electric energy flows into an energy storage battery in a fuselage to be charged, the other part of the generated electric energy supplies energy to four groups of duct power groups on front and rear wings, and the duct power groups at the rear edge positions of the wings improve the aerodynamic efficiency of the wings by sucking boundary layer airflow on the upper surfaces of the wings.
c. In the short landing stage, the control mechanism in the wing controls the trailing edge flaps of the inner wing sections of the front wing and the rear wing to drive the ducted power sets on the inner wing sections to deflect 90 degrees downwards to be vertical to the horizontal plane, so that the vertical thrust is provided for the unmanned aerial vehicle, and the power of the two ducted power sets on the trailing edge flaps of the left outer wing section and the right outer wing section of the rear wing is gradually reduced, so that the unmanned aerial vehicle gradually decelerates and reduces the altitude to the ground to complete the landing work.
The front wing and the rear wing are in a high aspect ratio straight wing form, the aspect ratio is 8-16, the sweepback angle is 0 degree, and the dihedral angle is 0-10 degrees.
As shown in fig. 1 to 4, the short-distance take-off and landing unmanned aerial vehicle adopting distributed duct power in the embodiment is composed of a fuselage, a front wing, a rear wing, a trailing edge flap, an elevator, an aileron, a front landing gear, a main landing gear, a vertical empennage, a rudder, a duct power set and a generator cabin; the section of the middle part of the machine body is a rounded rectangle, and the machine head and the machine tail are respectively gradually contracted forwards and backwards; the front wings are simultaneously arranged below the front parts of the two airframes, the aspect ratio of the front wings is 8.93, the sweepback angle is 0 degree, and the dihedral angle is 0 degree; the rear wings are simultaneously arranged above the tails of the two airframes, the aspect ratio of the rear wings is 13.60, the sweepback angle is 0 degree, and the dihedral angle is 0 degree; the elevators are arranged at the positions of the rear edges of the left and right outer sides of the front wing; the ailerons are arranged at the positions of the rear edges of the left and right outer sides of the rear wing; the 4 trailing edge flaps are respectively arranged at the trailing edge position of the inner wing section of the front wing, the trailing edge position of the inner wing section of the rear wing and the trailing edge positions of the left outer wing section and the right outer wing section of the rear wing in a hinged mode, and the trailing edge flaps rotate by 0-90 degrees relative to the wing surfaces of the wings through a driving mechanism in the wings; the upper wing surface of each trailing edge flap is provided with a group of ducted power groups, each group of ducted power groups comprises 6 ducted power units, each ducted power unit comprises a duct, a motor, an electronic speed regulator and a propeller, and the ducted power groups deflect the trailing edge flaps to change the thrust direction; the two vertical tail wings are respectively arranged above the tails of the two machine bodies; a rudder is arranged at the rear part of the vertical tail wing; the two generator cabins are respectively arranged at the roots of the two vertical tail wings; the two nose landing gears are respectively arranged below the front parts of the two airframes, and the two main landing gears are respectively arranged below the rear parts of the two airframes.
When a certain motor on the duct power set breaks down in the flying process, the short-distance take-off and landing unmanned aerial vehicle adopting the distributed duct power can keep the thrust on the left side and the thrust on the right side of the unmanned aerial vehicle balanced by adjusting the output power of the rest motors, so that the flying safety of the unmanned aerial vehicle is ensured.
Claims (2)
1. The utility model provides an adopt short distance take-off and landing unmanned aerial vehicle of distributed duct power which characterized in that:
the distributed duct power short-distance take-off and landing unmanned aerial vehicle comprises two bodies, front wings, rear wings, trailing edge flaps, elevators, ailerons, nose landing gears, main landing gears, vertical empennages, rudder, duct power units and generator cabins, wherein the space between the bodies is smaller than the span length of the front wings;
the elevator is arranged at the position of the rear edge of the left and right outer sides of the front wing, the ailerons are arranged at the position of the rear edge of the left and right outer sides of the rear wing, the number of the rear edge flaps is 4, the rear edge flaps are respectively arranged at the position of the rear edge of the inner wing section of the front wing, the position of the rear edge of the inner wing section of the rear wing and the position of the rear edge of the left and right outer wing sections of the rear wing in a hinged mode, the rear edge flaps rotate by 0-90 degrees relative to the wing surfaces of the wings through a driving mechanism in the wings, the rear side of the vertical tail wing is provided with a rudder, the generator cabin is arranged at the root part of the vertical tail wing, a turbine generator is arranged in the generator cabin, and the turbine engine burns fuel oil to drive the generator to serve as a ducted power group to provide electric energy;
the total 4 groups of duct power pack install the upper surface at four trailing edge flaps respectively, and every group duct power pack all contains 4 ~ 10 duct power unit, and every duct power unit includes duct, motor, electronic governor and screw, and duct power pack follows the deflection of edge flaps and changes thrust direction.
2. The unmanned aerial vehicle that takes off and land for a short distance that adopts distributed duct power of claim 1, characterized in that:
the front wing and the rear wing are in a high aspect ratio straight wing form, the aspect ratio is 8-16, the sweepback angle is 0 degree, and the dihedral angle is 0-10 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810315808.7A CN108569399B (en) | 2018-04-10 | 2018-04-10 | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810315808.7A CN108569399B (en) | 2018-04-10 | 2018-04-10 | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108569399A CN108569399A (en) | 2018-09-25 |
| CN108569399B true CN108569399B (en) | 2022-07-26 |
Family
ID=63574879
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810315808.7A Active CN108569399B (en) | 2018-04-10 | 2018-04-10 | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108569399B (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110143282B (en) * | 2019-06-18 | 2023-07-04 | 中国空气动力研究与发展中心计算空气动力研究所 | Aircraft adopting high aspect ratio double-fuselage flying wing layout |
| CN110228590A (en) * | 2019-06-30 | 2019-09-13 | 郑州航空工业管理学院 | A kind of detachable cargo hold connection wing twin fuselage logistics unmanned plane |
| CN110450949A (en) * | 2019-08-19 | 2019-11-15 | 西安因诺航空科技有限公司 | A kind of twin fuselage vertically taking off and landing flyer |
| CN110450948A (en) * | 2019-08-19 | 2019-11-15 | 西安因诺航空科技有限公司 | A kind of vertically taking off and landing flyer |
| CN110510116A (en) * | 2019-09-20 | 2019-11-29 | 北京大学 | Rotor and vector propulsion system combined type aircraft |
| CN111268120B (en) * | 2020-03-11 | 2022-03-22 | 西北工业大学 | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power |
| CN111619823A (en) * | 2020-06-02 | 2020-09-04 | 西北工业大学 | Short-distance/vertical take-off and landing aircraft distributed propulsion system test bed |
| CN112722243B (en) * | 2021-01-19 | 2022-11-11 | 西北工业大学 | Distributed electric ducted fan power system for short-distance/vertical take-off and landing |
| CN112896529B (en) * | 2021-03-10 | 2022-07-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Auxiliary propulsion device and electric aircraft |
| FR3135705A1 (en) * | 2022-05-19 | 2023-11-24 | Institut Supérieur De L'aéronautique Et De L'espace | POWERTRAIN, AIRCRAFT AND IMPLEMENTATION AT THE TIME OF TAKEOFF |
| FR3135703A1 (en) * | 2022-05-20 | 2023-11-24 | Institut Supérieur De L'aéronautique Et De L'espace | METHOD FOR ACTIVE CONTROL OF WAKE-NACEL INTERACTION AND CORRESPONDING AIRCRAFT |
| CN115489716B (en) * | 2022-09-22 | 2023-12-29 | 中国商用飞机有限责任公司 | Wing and electric aircraft integrated with distributed ducted fans |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5071088A (en) * | 1989-11-29 | 1991-12-10 | The United States Of America As Represented By The Secretary Of The Navy | High lift aircraft |
| CN102826215A (en) * | 2012-09-11 | 2012-12-19 | 北京航空航天大学 | Light and small flying-wing manned aircraft with short takeoff and landing capacity |
| CN103158856A (en) * | 2013-04-12 | 2013-06-19 | 北京航空航天大学 | Light airscrew flying wing aircraft capable of taking off and landing in short distance |
| CN103192981A (en) * | 2013-04-12 | 2013-07-10 | 北京航空航天大学 | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105109695A (en) * | 2015-08-25 | 2015-12-02 | 西安交通大学 | Multifunctional aircraft with hybrid of oil and electricity |
| CN205770120U (en) * | 2016-05-23 | 2016-12-07 | 龙川 | A kind of continuous distributed electric ducted fan wing flap high-lift system |
| CN107215452A (en) * | 2017-05-22 | 2017-09-29 | 龙川 | The new distributed electric ducted fan wing flap high-lift system of continuous type |
-
2018
- 2018-04-10 CN CN201810315808.7A patent/CN108569399B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5071088A (en) * | 1989-11-29 | 1991-12-10 | The United States Of America As Represented By The Secretary Of The Navy | High lift aircraft |
| CN102826215A (en) * | 2012-09-11 | 2012-12-19 | 北京航空航天大学 | Light and small flying-wing manned aircraft with short takeoff and landing capacity |
| CN103158856A (en) * | 2013-04-12 | 2013-06-19 | 北京航空航天大学 | Light airscrew flying wing aircraft capable of taking off and landing in short distance |
| CN103192981A (en) * | 2013-04-12 | 2013-07-10 | 北京航空航天大学 | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108569399A (en) | 2018-09-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108569399B (en) | Adopt short distance unmanned aerial vehicle that takes off and land of distributed duct power | |
| CN102133926B (en) | Tailstock type vertical take-off and landing unmanned aerial vehicle | |
| CN107089328B (en) | Control method of hybrid tail-seat type vertical take-off and landing long-endurance unmanned aerial vehicle | |
| CN111268120B (en) | Vertical take-off and landing unmanned aerial vehicle adopting distributed duct power | |
| CN105173075B (en) | A kind of hybrid power can tilt wing aircraft | |
| CN107499506B (en) | Distributed propulsion tailstock type vertical take-off and landing fixed-wing aircraft | |
| US20210206487A1 (en) | Aircraft and Modular Propulsion Unit | |
| CN114126966A (en) | Novel aircraft design using tandem wings and distributed propulsion system | |
| CN106586001A (en) | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration | |
| US20130099065A1 (en) | Tilt-wing aircraft | |
| CN211468780U (en) | Short-distance take-off and landing unmanned conveyor | |
| CN104918853A (en) | Convertible aircraft provided with two ducted rotors at the wing tips and with a horizontal fan in the fuselage | |
| CN105059542A (en) | Vertical take-off and landing fixed wing long-endurance air vehicle | |
| CN202728574U (en) | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function | |
| CN103287576A (en) | Tailless layout single tail seat type vertical take-off and landing aircraft | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN206857002U (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft | |
| CN104973234A (en) | Aircraft using distributed electric ducted fan flap lift-rising system | |
| CN103192981A (en) | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft | |
| WO2024060633A1 (en) | Aircraft wing having integrated distributed ducted fan, and electric aircraft | |
| CN101367436B (en) | Miniature hybrid power flying platform and implementing method thereof | |
| CN106167096A (en) | Modified model level of approximation rotates propeller wing flap lift-rising and connects wing aircraft | |
| CN105109695A (en) | Multifunctional aircraft with hybrid of oil and electricity | |
| CN205203366U (en) | Approximate level is rotated propeller wing flap lift -rising and is connected wing aircraft | |
| US11524778B2 (en) | VTOL aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |