CN206012959U - A kind of how culvert vertical take-off and landing unmanned machine - Google Patents
A kind of how culvert vertical take-off and landing unmanned machine Download PDFInfo
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- CN206012959U CN206012959U CN201621043907.7U CN201621043907U CN206012959U CN 206012959 U CN206012959 U CN 206012959U CN 201621043907 U CN201621043907 U CN 201621043907U CN 206012959 U CN206012959 U CN 206012959U
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- ducted fan
- unmanned machine
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Abstract
The utility model discloses a kind of how culvert vertical take-off and landing unmanned machine, the unmanned plane includes：Fuselage；Undercarriage；Wing, including central wing and outer section of wing, is connected using fast assembling disassembling structure；Lift ducted fan, its by-pass air duct and outer section of wing adopt integrally formed structure；Propelling screws, positioned at the afterbody of fuselage；Vertical tail, and tailplane composition twin-finned layout；Trim ducted fan.During high-performance cruise vertical landing of taking off vertically, trim ducted fan is used for providing the new line and nose-down pitching moment needed for the longitudinal direction pitching of VTOL stage, by deflecting the yawing for providing the VTOL stage；Lift when lift ducted fan is used for providing VTOL；Propelling screws are used for providing the thrust needed for flat flying.Unmanned plane of the present utility model can take off landing in narrow space, it is adaptable to the scene such as electric inspection process, environmental inspection, with fast assembling-disassembling, portable, the advantages of voyage is big, flying quality is good.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, particularly a kind of how culvert vertical take-off and landing unmanned machine.
Background technology
Electronic unmanned plane has safe and reliable property height, light and flexible, the low advantage of use cost, but there is endurance
This fatal defects weak, limit the development of electronic unmanned plane.The dynamic unmanned plane complex operation of oil, stability are poor.Fixed-wing nobody
Machine cannot realize VTOL and hovering.Rotor wing unmanned aerial vehicle has very big restriction in load-carrying, boat, in the speed of a ship or plane, voyage.
Fixed-wing VUAV takes into account high-speed flight, big voyage, heavy－duty and the rotor wing unmanned aerial vehicle of fixed-wing unmanned plane
VTOL ability.Therefore, fixed-wing VUAV has very strong practicality in technical grade and army grade unmanned plane field
It is worth.
Unmanned plane plays an important role in fields such as electric inspection process, environmental monitorings, and these fields require that unmanned plane should
High maneuverability, possesses larger flying radius again.Existing unmanned plane scheme is difficult to take into account VTOL, big load, length
The performance such as during boat, it is impossible to which the lasting monitoring for solving the scenes such as landing and electric inspection process, environmental inspection of taking off of small space is asked
Topic.
Utility model content
For the problems referred to above of the prior art, the utility model provide a kind of both can with VTOL, hovering,
Simultaneously again the lift using wing carries out high-performance cruise and puts down winged how culvert vertical take-off and landing unmanned machine, for solving existing unmanned plane
VTOL, loaded speed voyage etc. cannot meet the problem of existing requirement.
For achieving the above object, the utility model provides a kind of how culvert vertical take-off and landing unmanned machine, and many ducts hang down
Straight landing unmanned plane includes：Fuselage；Undercarriage, the undercarriage are two, are arranged on former and later two positions of fuselage bottom, and phase
For fuselage length direction middle vertical plane symmetrical；Wing, the wing are arranged at the postmedian of fuselage, are fixed on the top of fuselage；
Lift ducted fan, the lift ducted fan are two, and are arranged at the apical location of wing；Propelling screws, described
Propelling screws are located at the afterbody of fuselage；Vertical tail, the vertical tail are two, perpendicular to tailplane, are located at respectively
Tailplane two ends, vertical tail trailing edge are provided with rudder；Tailplane, the tailplane rear portion are provided with elevator；
Unidirectional vector ducted fan, the unidirectional vector ducted fan are two, in the middle part of tailplane, on the axis of fuselage.
The how culvert vertical take-off and landing unmanned machine taking off vertically-high-performance cruise-vertical landing during, the unidirectional arrow
Amount ducted fan is used for providing the new line and nose-down pitching moment needed for the longitudinal direction pitching of VTOL stage, is provided by deflection vertical
The yawing in landing stage；Lift ducted fan is used for providing lift during VTOL；Propelling screws are flat for providing
Thrust needed for flying.
Preferably, the fuselage and wing constitute the high mounted wing aerodynamic arrangement of high aspect ratio.
Preferably, the fuselage is streamlined cylinder.
Preferably, the wing includes central wing and outer section of wing, adopts between the central wing and outer section of wing
Fast assembling disassembling structure connects, and the outer section of wing rear portion is provided with aileron.
Preferably, the by-pass air duct of the outer section of wing and lift ducted fan is merged, and takes integrally formed knot
Structure.
Preferably, the undercarriage is using the full carbon fiber structural of double π types.
Preferably, the tailplane is made up of two parallel shoes and tailplane main body, and two parallel shoes are solid
It is scheduled on the central wing front and rear beam position of wing.
Preferably, the tailplane and vertical tail constitute twin-finned layout, have suffered empennage positioned at propelling screws it
Afterwards.
Preferably, the lift ducted fan and unidirectional vector ducted fan are two-by-two relative to fuselage length direction middle vertical plane
Symmetrically.
Preferably, the lift ducted fan and unidirectional vector ducted fan adopt Motor drive, propelling screws to adopt
Internal combustion engine drives.
The beneficial effect of the utility model unmanned plane：The unmanned plane adopts ducted fan and propelling screws for power, can
To realize VTOL, hovering, and efficiency high of taking off, with ultrahigh maneuverability；And in cruising flight, with big load
When weight, higher flying speed, long boat, big voyage and higher security performance.Wing employs fast assembling disassembling structure simultaneously,
Memory space is saved, easy accessibility is transported.Take off landing and the electric inspection process environment prison of small space are preferably solved
The lasting monitoring problem of scene such as examine.
Description of the drawings
Fig. 1 is the structural representation of the how culvert vertical take-off and landing unmanned machine according to the utility model first embodiment.
Fig. 2 is the top view of the how culvert vertical take-off and landing unmanned machine according to the utility model first embodiment.
Figure acceptance of the bid note is respectively：1st, fuselage；2nd, undercarriage；3rd, wing；4th, central wing；5th, fast assembling disassembling structure；6th, outer
Section wing；7th, aileron；8th, lift ducted fan；9th, propelling screws；10th, vertical tail；11st, rudder；12nd, tailplane；
13rd, elevator；14th, unidirectional vector ducted fan.
Specific embodiment
For making purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, is further described in more detail to the technical scheme in the utility model embodiment.Described enforcement
Example is a part of embodiment of the utility model, rather than whole embodiments.Embodiment below with reference to Description of Drawings is
Exemplary, it is intended to for explaining the utility model, and it is not intended that to restriction of the present utility model.It is based on the utility model
In embodiment, the every other enforcement obtained under the premise of creative work is not made by those of ordinary skill in the art
Example, belongs to the scope of the utility model protection.Below in conjunction with the accompanying drawings embodiment of the present utility model is described in detail.
As shown in Fig. 1 Fig. 2, the how culvert vertical take-off and landing unmanned machine that the present embodiment is provided includes：Fuselage 1；Undercarriage 2 is
Two, former and later two positions of 1 bottom of fuselage are arranged on, and symmetrical relative to 1 length direction middle vertical plane of fuselage；Wing 3 is arranged at
The postmedian of fuselage 1, is fixed on the top of fuselage 1；Lift ducted fan 8 is two, and is arranged at the tip position of wing 3
Put；Propelling screws 9 are located at the afterbody of fuselage 1；Vertical tail 10 is two, perpendicular to tailplane 12, is located at level respectively
12 two ends of empennage, 10 trailing edge of vertical tail are provided with rudder 11；12 rear portion of tailplane is provided with elevator 13；Unidirectional vector
Ducted fan 14, is located in the middle part of tailplane 12, on the axis of fuselage 1 respectively.
The how culvert vertical take-off and landing unmanned machine taking off vertically-high-performance cruise-vertical landing during, the unidirectional arrow
Amount ducted fan 14 is used for providing the new line and nose-down pitching moment needed for the longitudinal direction pitching of VTOL stage, vertical to provide by deflecting
The yawing in straight landing stage；Lift ducted fan 8 is used for providing lift during VTOL；Propelling screws 9 are used for carrying
For equalling the thrust needed for flying.
In the present embodiment, fuselage 1 and wing 3 constitute the high mounted wing aerodynamic arrangement of high aspect ratio.
In the present embodiment, fuselage 1 be long 1.2m, the streamlined cylinder of 0.4 meter of maximum gauge.It is understood that
Above-mentioned size is only in one embodiment, the concrete chi of the electric mixed VUAV fuselage of many ducts oil of the application
Very little can sets itself as desired.For example, fuselage 1 be long 1.5m, the streamlined cylinder of 0.5 meter of maximum gauge or its
His size.
In the present embodiment, wing 3 includes central wing 4 and outer section of wing 6, adopts between central wing 4 and outer section of wing 6
With fast assembling disassembling structure 5, outer section of 6 rear portion of wing is provided with aileron 7.
In the present embodiment, the by-pass air duct of outer section of wing 6 and lift ducted fan 8 is merged, and is taken integrally formed
Structure.
In the present embodiment, unmanned plane is 2.5 meters from the size of head to tail, 4 meters of wing span.May be appreciated
It is that above-mentioned size is only in one embodiment, the concrete chi of the electric mixed VUAV of many ducts oil of the application
Very little can sets itself as desired.For example, it is 3 meters from the size of head to tail, 5 meters of wing span or other chis
Very little.
In the present embodiment, undercarriage 2 is using the full carbon fiber structural of double π types.
In the present embodiment, tailplane 9 is made up of two parallel shoes and tailplane main body, two parallel tails
The support other end is fixed on the 4 front and rear beam position of central wing of wing 3.
In the present embodiment, tailplane 12 and vertical tail 10 constitute twin-finned layout, and empennage is located at propelling screws 9
Afterwards.
In the present embodiment, lift ducted fan 8 and unidirectional vector ducted fan 14 are two-by-two relative to 1 length direction of fuselage
Middle vertical plane is symmetrical.
In the present embodiment, lift ducted fan and unidirectional vector ducted fan adopt Motor drive, propelling screws to adopt
Driven with internal combustion engine.
Beneficial effect using above scheme：As a result of the Design of Aerodynamic Configuration of the fixed-wing of many ducted fans, nothing
The man-machine vertical tension for both providing using lift ducted fan realizes vertical and landing takeoff and efficiency high of taking off, again can profit
The pressure reduction lift provided with fixed wing obtains higher flying speed and power operation efficiency in the flat winged stage.Make unmanned plane collection
When VTOL, hovering and long boat, heavy－duty performance.The unmanned plane is using ducted fan and propulsion spiral simultaneously
Oar is power, and three ducted fans using electronic mode, realize simply by VTOL, and propelling screws are using oily flowing mode, continuous
Boat ability is strong, and flying speed is fast.And wing employs fast assembling disassembling structure, memory space is saved, transport easy accessibility.Compared with
The lasting monitoring of the take off scenes such as landing and electric inspection process environmental inspection of small space is solved the problems, such as well.
Above example is only in order to further describing the technical solution of the utility model, it is impossible to assert the utility model
Specific embodiment be confined to these explanations.For the utility model person of an ordinary skill in the technical field,
The other embodiment drawn under without departing from the technical solution of the utility model, should be included in protection model of the present utility model
In enclosing.
Claims (10)
1. a kind of how culvert vertical take-off and landing unmanned machine, it is characterised in that the how culvert vertical take-off and landing unmanned machine includes：
Fuselage（1）；
Undercarriage（2）, the undercarriage（2）For two, fuselage is arranged on（1）Former and later two positions of bottom, and relative to fuselage
（1）Length direction middle vertical plane is symmetrical；
Wing（3）, the wing（3）It is arranged at fuselage（1）Postmedian, be fixed on fuselage（1）Top；
Lift ducted fan（8）, the lift ducted fan（8）For two, and it is arranged at wing（3）Tip location；
Propelling screws（9）, the propelling screws（9）It is located at fuselage（1）Afterbody；
Vertical tail（10）, the vertical tail（10）For two, perpendicular to tailplane（12）, it is located at tailplane respectively
（12）Two ends, vertical tail（10）Trailing edge is provided with rudder（11）；
Tailplane（12）, the tailplane（12）Rear portion is provided with elevator（13）；
Unidirectional vector ducted fan（14）, the unidirectional vector ducted fan（14）It is located at tailplane（12）Middle part, fuselage（1）
Axis on；
The how culvert vertical take-off and landing unmanned machine taking off vertically-high-performance cruise-vertical landing during, the unidirectional vector is contained
Road fan（14）It is used for providing the new line and nose-down pitching moment needed for the longitudinal direction pitching of VTOL stage, is provided by deflection vertical
The yawing in landing stage；Lift ducted fan（8）For providing lift during VTOL；Propelling screws（9）For carrying
For equalling the thrust needed for flying.
2. how culvert vertical take-off and landing unmanned machine according to claim 1, it is characterised in that the fuselage（1）And wing（3）
The high mounted wing aerodynamic arrangement of composition high aspect ratio.
3. how culvert vertical take-off and landing unmanned machine according to claim 2, it is characterised in that the fuselage（1）For streamlined
Cylinder.
4. how culvert vertical take-off and landing unmanned machine according to claim 3, it is characterised in that the wing（3）Including central authorities
Wing（4）With outer section of wing（6）, the central wing（4）With outer section of wing（6）Between adopt fast assembling disassembling structure（5）Connection,
The outer section of wing（6）Rear portion is provided with aileron（7）.
5. how culvert vertical take-off and landing unmanned machine according to claim 4, it is characterised in that the outer section of wing（6）And liter
Power ducted fan（8）By-pass air duct merge, take integrally formed structure.
6. how culvert vertical take-off and landing unmanned machine according to claim 5, it is characterised in that the undercarriage（2）Using double π
The full carbon fiber structural of type.
7. how culvert vertical take-off and landing unmanned machine according to claim 6, it is characterised in that the tailplane（12）By two
The parallel shoe of root and tailplane main body composition, two parallel shoes are fixed on wing（3）Central wing（4）Beam portion in front and back
Position.
8. how culvert vertical take-off and landing unmanned machine according to claim 7, it is characterised in that the tailplane（12）With hang down
Fin（10）Twin-finned layout is constituted, empennage is located at propelling screws（9）Afterwards.
9. how culvert vertical take-off and landing unmanned machine according to claim 8, it is characterised in that the lift ducted fan（8）
With unidirectional vector ducted fan（14）Two-by-two relative to fuselage（1）Length direction middle vertical plane is symmetrical.
10. how culvert vertical take-off and landing unmanned machine according to claim 9, it is characterised in that the lift ducted fan（8）
With the unidirectional vector ducted fan（14）Using Motor drive, the propelling screws（9）Driven using internal combustion engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621043907.7U CN206012959U (en) | 2016-09-08 | 2016-09-08 | A kind of how culvert vertical take-off and landing unmanned machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621043907.7U CN206012959U (en) | 2016-09-08 | 2016-09-08 | A kind of how culvert vertical take-off and landing unmanned machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206012959U true CN206012959U (en) | 2017-03-15 |
Family
ID=58259489
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621043907.7U Expired - Fee Related CN206012959U (en) | 2016-09-08 | 2016-09-08 | A kind of how culvert vertical take-off and landing unmanned machine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107628244A (en) * | 2017-09-29 | 2018-01-26 | 清华大学 | A kind of double lift culvert vertical take-off and landing aircrafts based on tilting duct |
| CN107804456A (en) * | 2016-09-08 | 2018-03-16 | 朗星无人机系统有限公司 | A kind of how culvert vertical take-off and landing unmanned machine |
| CN108100252A (en) * | 2018-01-19 | 2018-06-01 | 北京韩品航通科技发展有限公司 | A kind of three paddle culvert types vert bimodulus flight unmanned plane |
| CN108502168A (en) * | 2018-05-31 | 2018-09-07 | 江苏常探机器人有限公司 | The rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust |
| CN108528700A (en) * | 2018-05-31 | 2018-09-14 | 江苏常探机器人有限公司 | With without the rear single screw folding composite wing manned vehicle for pushing away the compound auxiliary wing |
| CN108725772A (en) * | 2018-05-31 | 2018-11-02 | 江苏常探机器人有限公司 | A kind of band is without the rear single-screw paddle composite wing aircraft for pushing away the compound auxiliary wing |
| CN108750088A (en) * | 2018-05-31 | 2018-11-06 | 江苏常探机器人有限公司 | Rear single screw folding composite wing cargo aircraft with the compound auxiliary wing of thrust |
| CN108750096A (en) * | 2018-05-31 | 2018-11-06 | 江苏常探机器人有限公司 | A kind of band is without the rear single-screw paddle composite wing cargo aircraft for pushing away the compound auxiliary wing |
| CN108750095A (en) * | 2018-05-31 | 2018-11-06 | 江苏常探机器人有限公司 | A kind of rear single-blade formula composite wing airfreighter of the compound auxiliary wing of double duct thrusts |
| CN108773482A (en) * | 2018-05-31 | 2018-11-09 | 江苏常探机器人有限公司 | With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle |
| CN108791861A (en) * | 2018-05-31 | 2018-11-13 | 江苏常探机器人有限公司 | With without the rear single ducted fan formula composite wing manned vehicle for pushing away the compound auxiliary wing |
| 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 |
| CN108928473A (en) * | 2018-05-31 | 2018-12-04 | 江苏常探机器人有限公司 | A kind of folding composite wing manned vehicle of the compound auxiliary wing of twin screw thrust |
| CN108945422A (en) * | 2018-05-31 | 2018-12-07 | 江苏常探机器人有限公司 | A kind of spiral shell with the auxiliary wing of twin screw and the attached wing pushes away composite wing airfreighter |
| CN108974351A (en) * | 2018-05-31 | 2018-12-11 | 江苏常探机器人有限公司 | Rear single ducted fan formula composite wing manned vehicle of double compound auxiliary wings of ducted fan |
| CN108974349A (en) * | 2017-05-31 | 2018-12-11 | 大鹏航太有限公司 | Vertical lift can be had both and determine the simple pitch control device of aircraft of wing flight |
| CN109747819A (en) * | 2017-11-05 | 2019-05-14 | 西安倾云无人机技术有限公司 | A kind of vertically taking off and landing flyer that lift fan is merged with tilting duct |
| CN110217391A (en) * | 2019-05-31 | 2019-09-10 | 沈阳迪智科技有限公司 | A kind of oil electric mixed dynamic VTOL sweepforward fixed-wing unmanned plane |
| CN110816809A (en) * | 2019-12-11 | 2020-02-21 | 歌尔股份有限公司 | Arm subassembly and unmanned aerial vehicle |
| EP3656669A1 (en) | 2018-11-26 | 2020-05-27 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A vertical take-off and landing multirotor aircraft with at least eight thrust producing units |
| CN111361727A (en) * | 2020-03-31 | 2020-07-03 | 厦门恰再注包装有限公司 | A delivery unmanned aerial vehicle for rural equidistance area |
| EP3702277A1 (en) | 2019-02-27 | 2020-09-02 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A multirotor aircraft that is adapted for vertical take-off and landing (vtol) |
| EP3702276A1 (en) | 2019-02-27 | 2020-09-02 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A multirotor joined-wing aircraft with vtol capabilities |
| US20230264838A1 (en) * | 2020-06-26 | 2023-08-24 | Ucal Fuel Systems Limited | Multipurpose and long endurance hybrid unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107804456A (en) * | 2016-09-08 | 2018-03-16 | 朗星无人机系统有限公司 | A kind of how culvert vertical take-off and landing unmanned machine |
| 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 |
| 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 |
| CN108974349A (en) * | 2017-05-31 | 2018-12-11 | 大鹏航太有限公司 | Vertical lift can be had both and determine the simple pitch control device of aircraft of wing flight |
| CN107628244A (en) * | 2017-09-29 | 2018-01-26 | 清华大学 | A kind of double lift culvert vertical take-off and landing aircrafts based on tilting duct |
| CN109747819A (en) * | 2017-11-05 | 2019-05-14 | 西安倾云无人机技术有限公司 | A kind of vertically taking off and landing flyer that lift fan is merged with tilting duct |
| CN108100252A (en) * | 2018-01-19 | 2018-06-01 | 北京韩品航通科技发展有限公司 | A kind of three paddle culvert types vert bimodulus flight unmanned plane |
| CN108100252B (en) * | 2018-01-19 | 2023-09-05 | 北京韩品航通科技发展有限公司 | Three-oar duct formula bimodulus unmanned aerial vehicle that verts |
| CN108974351A (en) * | 2018-05-31 | 2018-12-11 | 江苏常探机器人有限公司 | Rear single ducted fan formula composite wing manned vehicle of double compound auxiliary wings of ducted fan |
| CN108528700A (en) * | 2018-05-31 | 2018-09-14 | 江苏常探机器人有限公司 | With without the rear single screw folding composite wing manned vehicle for pushing away the compound auxiliary wing |
| CN108791861A (en) * | 2018-05-31 | 2018-11-13 | 江苏常探机器人有限公司 | With without the rear single ducted fan formula composite wing manned vehicle for pushing away the compound auxiliary wing |
| CN108750095A (en) * | 2018-05-31 | 2018-11-06 | 江苏常探机器人有限公司 | A kind of rear single-blade formula composite wing airfreighter of the compound auxiliary wing of double duct thrusts |
| CN108928473A (en) * | 2018-05-31 | 2018-12-04 | 江苏常探机器人有限公司 | A kind of folding composite wing manned vehicle of the compound auxiliary wing of twin screw thrust |
| CN108945422A (en) * | 2018-05-31 | 2018-12-07 | 江苏常探机器人有限公司 | A kind of spiral shell with the auxiliary wing of twin screw and the attached wing pushes away composite wing airfreighter |
| CN108750096A (en) * | 2018-05-31 | 2018-11-06 | 江苏常探机器人有限公司 | A kind of band is without the rear single-screw paddle composite wing cargo aircraft for pushing away the compound auxiliary wing |
| CN108750088A (en) * | 2018-05-31 | 2018-11-06 | 江苏常探机器人有限公司 | Rear single screw folding composite wing cargo aircraft with the compound auxiliary wing of thrust |
| CN108725772A (en) * | 2018-05-31 | 2018-11-02 | 江苏常探机器人有限公司 | A kind of band is without the rear single-screw paddle composite wing aircraft for pushing away the compound auxiliary wing |
| CN108502168A (en) * | 2018-05-31 | 2018-09-07 | 江苏常探机器人有限公司 | The rear compound rotor aircraft of single-blade folding with the compound auxiliary wing of airscrew thrust |
| CN108773482A (en) * | 2018-05-31 | 2018-11-09 | 江苏常探机器人有限公司 | With the compound auxiliary wing of turbofan and additional fin without back pressure formula composite wing manned vehicle |
| EP3656669A1 (en) | 2018-11-26 | 2020-05-27 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A vertical take-off and landing multirotor aircraft with at least eight thrust producing units |
| US11554862B2 (en) | 2018-11-26 | 2023-01-17 | Airbus Helicopters Deutschland GmbH | Vertical take-off and landing multirotor aircraft with at least eight thrust producing units |
| EP3702277A1 (en) | 2019-02-27 | 2020-09-02 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A multirotor aircraft that is adapted for vertical take-off and landing (vtol) |
| EP3702276A1 (en) | 2019-02-27 | 2020-09-02 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A multirotor joined-wing aircraft with vtol capabilities |
| US10981650B2 (en) | 2019-02-27 | 2021-04-20 | Airbus Helicopters Deutschland GmbH | Multirotor joined-wing aircraft with VTOL capabilities |
| US11691722B2 (en) | 2019-02-27 | 2023-07-04 | Airbus Urban Mobility Gmbh | Multirotor aircraft that is adapted for vertical take-off and landing |
| CN110217391A (en) * | 2019-05-31 | 2019-09-10 | 沈阳迪智科技有限公司 | A kind of oil electric mixed dynamic VTOL sweepforward fixed-wing unmanned plane |
| CN110816809A (en) * | 2019-12-11 | 2020-02-21 | 歌尔股份有限公司 | Arm subassembly and unmanned aerial vehicle |
| CN111361727A (en) * | 2020-03-31 | 2020-07-03 | 厦门恰再注包装有限公司 | A delivery unmanned aerial vehicle for rural equidistance area |
| US20230264838A1 (en) * | 2020-06-26 | 2023-08-24 | Ucal Fuel Systems Limited | Multipurpose and long endurance hybrid unmanned aerial vehicle |
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