CN106218887A - A kind of vertically taking off and landing flyer of distributed-power device layout - Google Patents
A kind of vertically taking off and landing flyer of distributed-power device layout Download PDFInfo
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- CN106218887A CN106218887A CN201610712566.6A CN201610712566A CN106218887A CN 106218887 A CN106218887 A CN 106218887A CN 201610712566 A CN201610712566 A CN 201610712566A CN 106218887 A CN106218887 A CN 106218887A
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- wing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
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Abstract
The invention discloses the vertically taking off and landing flyer of a kind of distributed-power device layout, including fuselage, wing, empennage and propeller, described fuselage is semi-monocoque structure, described fuselage includes head, stage casing and tail, middle fuselage is cargo hold, it is provided with symmetrical wing in described fuselage both sides, described wing is that twin beams semi-monocoque structure and wing are connected by strengthening bulkhead with fuselage, it is provided with elevon at described trailing edge, the wingtip of wing is provided with end plate type winglet, the present invention uses distributed propulsion plant layout, aircraft is made to possess relatively low disk loading when VTOL, there is higher propulsive efficiency；Use the compound operating pattern of motor speed/airscrewpiston+propellerslip rudder, handle effect high；Fixing aerofoil uses anury Flying-wing, reduces the size of aircraft so that structure is compacter, it is easy to demolition and maintenance, and good in VTOL stage more conventional layout and canard configuration wind resistance.
Description
Technical field
The present invention relates to minute vehicle, particularly relate to the VTOL flight of a kind of distributed-power device layout
Device.
Background technology
Vertically taking off and landing flyer generally includes helicopter, gyroplane, flapping-wing aircraft, tiltrotor, tailstock formula VTOL
The schemes such as the vertically taking off and landing flyer of aircraft and configuration lift fan or vector propulsion device.Tailstock formula VTOL flies
Row device simple in construction, vertical flight and horizontal flight use the same set of dynamical system being fixed on body, reliability high and
The useless weight that not many set dynamical systems are brought.
Vertically taking off and landing flyer can be summed up down and be had the disadvantage that: conventional helicopters flight speed when flight is low, voyage
Short, rotor system is complicated；When plus tilted propeller/tilting rotor, relatively conventional helicopters flight speed improves, and voyage is prolonged
Long, however it is necessary that complexity, heavy high pulling torque inclining rotary mechanism, the most even vert together with wing, this causes VTOL
Wind resistance is poor, and transition flight wing is in advanced stall state, and control and stability is poor；And other are through the VTOL flight integrated
Device can be provided simultaneously with lift engine, propelling motor, both deadweight or parasitic drags each other in different state of flights, and
Doing the wing of cruise carrying lift, this aircraft is the heaviest in the VTOL stage.
And conventional tail sitting posture aircraft, it is to be nearly all provided without 6 or more distributed propelling currently on the market
Device, its flying quality does not the most get a promotion, and they are only bad by the control and stability of propellerslip rudder, and conventional
Aerofoil layout or canard configuration make Flight Vehicle Structure weight big, and when VTOL, wind resistance is poor, because aircraft geometry
Oversize, so handling, poorly especially tail is sat aircraft and is used wing load flying method in the horizontal flight stage, thus
High speed, high efficiency horizontal flight can be realized by the optimization design of wing, and have higher load-carrying ability.
Summary of the invention
The present invention is directed to that flight speed in prior art is low, rotor system is complicated and housing construction is complicated huge etc. lacks
Point, it is provided that the vertically taking off and landing flyer of a kind of distributed-power device layout.
In order to solve above-mentioned technical problem, the present invention is addressed by following technical proposals:
The vertically taking off and landing flyer of a kind of distributed-power device layout, including fuselage, wing, empennage and propeller, institute
Stating fuselage is semi-monocoque structure, and described fuselage includes head, stage casing and tail, and middle fuselage is cargo hold, at described fuselage
Both sides are provided with symmetrical wing, are provided with elevon on described wing, are provided with end plate type wingtip on the wingtip of wing
Winglet；Described empennage includes that vertical fin and abdomeinal fin, described vertical fin are provided with wingtip, and described abdomeinal fin is provided with abdomeinal fin wingtip, at described wing
Being provided with power set, vertical fin is provided with power set, and abdomeinal fin is provided with power set, and described power plant output shaft connects spiral
Oar, described winglet, wingtip and abdomeinal fin wingtip do undercarriage during VTOL as aircraft.Acting as of elevon
When aircraft hovering is with VTOL, differential deflection carries out vehicle yaw assist control；Carry out flat flying at aircraft to cruise
Time, differential deflection carries out rolling control, and deflection carries out pitch control in the same direction.At wing wingtip, there is end plate type winglet, be
Fly induced drag for reducing to put down, wait aircraft can regard the undercarriage of aircraft when doing VTOL.
The vertically taking off and landing flyer of a kind of distributed-power device layout, including fuselage, wing, empennage and propeller, institute
Stating fuselage is semi-monocoque structure, and described fuselage includes head, stage casing and tail, and middle fuselage is cargo hold, at described fuselage
Both sides are provided with symmetrical wing, are provided with elevon on described wing, are provided with end plate type wingtip on the wingtip of wing
Winglet；Described empennage includes that vertical fin and abdomeinal fin, described vertical fin are provided with wingtip, and described abdomeinal fin is provided with abdomeinal fin wingtip, at described fuselage
Or airfoil root is provided with power set, described power set are connected propeller with power transmission shaft, in fuselage or institute by gear-box
State winglet, wingtip does undercarriage during VTOL with abdomeinal fin wingtip as aircraft.
As preferably, described wing is twin beams semi-monocoque structure and wing is connected by strengthening bulkhead with fuselage.
As preferably, described wing is swept-back wing, and described wing control section is in " S ", and wing root to wingtip is provided with 3 ° to 5 °
Negative twist turns.Wing is divided into left and right wing, here, use medium aspect ratio and the swept-back wing of medium taper ratio, medium aspect ratio
Scope is 4.5 to 7, and medium taper ratio is in the range of 0.5 to 0.7.
As preferably, described head and tail are respectively Demountable.
As preferably, described propeller uses constant pitch airscrew or variable-pitch propeller.The unalterable propeller of blade angle
Being constant pitch airscrew, the propeller that blade angle can change is variable-pitch propeller, and constant pitch airscrew is relatively to be suitable for fixing
In velocity interval, and variable-pitch propeller can be suitable for various speed.So constant pitch airscrew can only be in selected velocity interval
Efficiency is higher.
As preferably, variable-pitch propeller connects machinery pitch-changing mechanism.The velocity interval being suitable for due to variable-pitch propeller is extensive,
But as unmanned plane, need a fixing velocity interval value, it is therefore desirable to control device to change the pitch of propeller,
Therefore, carry machinery pitch-changing mechanism to variable-pitch propeller, be used for changing the pitch of propeller.
As preferably, described power set are electromotor, and described each wing is respectively equipped with two electromotors.
As preferably, described winglet is spatial vertical state with wingtip and abdomeinal fin wingtip respectively.
As preferably, in head with tail, it is provided with electronic equipment and power supply.
Due to the fact that and have employed above technical scheme that there is significant technique effect:
The present invention uses distributed propulsion plant layout, 6 power output propellers so that aircraft is when VTOL
Possess relatively low disk loading, simultaneously in the cruising flight of fixed-wing carrying, there is higher propulsive efficiency；The present invention is patrolling
During boat, using fixed-wing carrying flight, lift-drag ratio is big, and can reach quickly to cruise with relatively low power consumption；Use motor speed/spiral shell
The compound operating pattern of rotation oar pitch+propellerslip rudder, handles effect high；Fixing aerofoil uses anury Flying-wing, reduces
The size of aircraft so that structure is compacter, number of components is few, it is easy to demolition and maintenance, and more normal in the VTOL stage
Rule layout and canard configuration wind resistance are good；Power set also serve as lift engine and propelling motor, and wing also serves as lifting surface, behaviour
Vertical face, electromotor cantilever and the force transferring part of undercarriage, it is achieved that zero deadweight；The present invention is not only suitable for the little of 6 platform independent motors
Type unmanned plane scheme, puts the Large Scale Space Vehicle scheme of high-power piston and turbogenerator in being also adaptable for.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to embodiment or existing
In having technology to describe, the required accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is only this
Some embodiments of invention, for those of ordinary skill in the art, on the premise of not paying creative work, also may be used
To obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is the overall structure schematic diagram of the present invention.
Fig. 2 is the profile of wing of the present invention.
Label declaration: 1 fuselage, 2 wings, 3 propellers, 4 elevons, 5 winglets, 6 vertical fins,
7 abdomeinal fins, 8 wingtips, 9 abdomeinal fin wingtips, 10 power set.
Detailed description of the invention
Below in conjunction with embodiment, the present invention is described in further detail, following example be explanation of the invention and
The invention is not limited in following example.
Embodiment 1:
The vertically taking off and landing flyer of a kind of distributed-power device layout, as it is shown in figure 1, vertically taking off and landing flyer includes machine
Body 1, is symmetrically arranged on two with two wings 2 in left and right at fuselage, is properly termed as port wing and starboard wing in an embodiment, but left and right
Not doing protection domain to limit at this, the afterbody of each wing 2 is provided with empennage, arranges propeller 3 in wing 2 upper end, and fuselage 1 is adopted
With semi-monocoque structure, fuselage 1 has three parts: including head, stage casing and tail, the stage casing of fuselage 1 uses as cargo hold, at machine
Body 1 both sides are provided with symmetrical wing 2, and the afterbody at each wing 2 is designed with elevon 4, and elevon 4 is by hinge
The mode connect is hinged on the trailing edge of wing 2 and can realize aircraft pitching (longitudinally) and the main control surface of roll guidance simultaneously, and
And the function that can also use as elevator and aileron.End at each wing 2 is exactly i.e. that to be provided with wingtip on wingtip little
The wing 5, is used for reducing and flat flies induced drag, also serves as undercarriage during VTOL simultaneously；Empennage includes vertical fin 6 and abdomeinal fin 7, is hanging down
The tip of tail 6 is provided with wingtip 8, the tip of abdomeinal fin 7 be provided with abdomeinal fin wingtip 9, vertical fin 6 and abdomeinal fin 7 be have bigger angle of sweep and
The vertical fin 6 of low aspect ratio and abdomeinal fin 7, vertical fin 6 and the structure of the version of abdomeinal fin 7 Yu wing 2 be the same but vertical fin 6 and
Abdomeinal fin 7 is to use NACA series of symmetric aerofoil profile, and wingtip 8 and abdomeinal fin wingtip 9 are as the undercarriage used during VTOL, Mei Geji
The winglet 5 of the wing 2 end and wingtip 8 and abdomeinal fin wingtip 9 in space in orthogonal state, winglet 5 and wingtip 8
A ground supports face is provided when aircraft takeoff to aircraft with abdomeinal fin wingtip 9.Each wing 2 is provided with two move
Power apparatus 10, vertical fin 3 is provided with general power set 10, and abdomeinal fin 12 is provided with power set 10, and each power set 10 are
Propeller 3, rising when winglet 5, wingtip 8 do VTOL with abdomeinal fin wingtip 9 as aircraft is connected by output shaft
Fall frame.
Winglet 5 respectively with wingtip 8 and abdomeinal fin wingtip 9 in spatial vertical state.
Embodiment 2 (this embodiment does not has schematic diagram):
The vertically taking off and landing flyer of a kind of distributed-power device layout, vertically taking off and landing flyer includes fuselage 1, at fuselage
1 is symmetrically arranged on two with two wings 2 in left and right, is properly termed as port wing and starboard wing in an embodiment, but left and right is not done at this
Protection domain limits, and the afterbody of each wing 2 is provided with empennage, is provided with propeller 3, in the present embodiment, machine in the upper end of wing 2
Body 1 uses semi-monocoque structure, fuselage 1 to have three parts: head, stage casing and tail, and the stage casing of fuselage 1 uses as cargo hold,
Head and stage casing employing are opened dismountable mode and are connected, and stage casing is also adopted by detachable mode and is connected with tail, and fuselage 1 both sides are provided with
Symmetrical wing 2, the afterbody at each wing 2 is provided with elevon 4, and elevon 4 is hinged by the way of hinged
At the trailing edge of wing 2 and aircraft pitching (longitudinally) and the main control surface of roll guidance can be realized simultaneously, and also can regard
The function that elevator and aileron use.End at each wing 2 is exactly i.e. to be provided with winglet 5 on wingtip, is used for reducing
Put down and fly induced drag, also serve as undercarriage during VTOL simultaneously；Empennage includes vertical fin 6 and abdomeinal fin 7, and the tip at vertical fin 6 sets
Having wingtip 8, the tip of abdomeinal fin 7 to be provided with abdomeinal fin wingtip 9, vertical fin 6 and abdomeinal fin 7 is to have hanging down of bigger angle of sweep and low aspect ratio
Tail 6 and abdomeinal fin 7, vertical fin 6 and the structure of the version of abdomeinal fin 7 Yu wing 2 are the same but vertical fin 6 and abdomeinal fin 7 are to use
NACA series of symmetric aerofoil profile, wingtip 8 and abdomeinal fin wingtip 9 are as the undercarriage used during VTOL, the wing of each wing 2 end
Tip winglet 5 and wingtip 8 and abdomeinal fin wingtip 9 in space in orthogonal state, winglet 5 and wingtip 8 and abdomeinal fin wingtip 9
A ground supports face is provided to aircraft when aircraft takeoff.
In the present invention, it is power set 10 to be set to fuselage 1 or is respectively provided with one on each wing 2
Power set 10, or wing 2 root arranges power set 10, and power set 10 are connected propeller by gear-box with power transmission shaft,
Winglet 5, wingtip 1 on fuselage 9 do undercarriage during VTOL with abdomeinal fin wingtip 13 as aircraft.
In embodiment 1 with embodiment 2:
Wing 2 uses the wing 2 of twin beams semi-monocoque structure to be more firmly logical at this wing 2 with fuselage 1 to connect
Cross reinforcement bulkhead to link together.
Wing 2 wing profile uses medium aspect ratio and the swept-back wing of taper ratio, here, medium aspect ratio in the range of
4.5 to 7, medium taper ratio, in the range of 0.5 to 0.7, uses the aerofoil profile of slight S-shaped state mean camber line to control section as profile,
And there are from wing root to wingtip 3 ° to 5 ° negative twists turn.
Propeller 3 uses constant pitch airscrew or variable-pitch propeller.The unalterable propeller of blade angle constant pitch airscrew,
The propeller that blade angle can change is variable-pitch propeller, and constant pitch airscrew is that comparison is suitable in fixing velocity interval, and
Variable-pitch propeller can be suitable for various speed.So constant pitch airscrew can only be higher in selected velocity interval internal efficiency.If
It is necessary to connect machinery pitch-changing mechanism to variable-pitch propeller if using variable-pitch propeller.
Embodiment 1 is with embodiment 2, and power set 10 are all electromotor, in embodiment 1, each wing 2 is sent out for two
Motivation, each electromotor is connected with propeller 3 by engine output shaft, is provided with electronic equipment and electricity in head with tail
Source.
In embodiment 1 with embodiment 2, the motion mode of aircraft is:
Aircraft the turning to as (from tail in terms of heading) of propeller when taking off: left wing's wingtip is counterclockwise, left wing
Wing root is counterclockwise, and right flank wing root is counterclockwise, and right flank wingtip is clockwise, and vertical fin is clockwise, and abdomeinal fin is clockwise.
Aircraft, when VTOL and hovering, can carry out aircraft by the rotating speed and pitch that control propeller
Gesture stability and flight path control, and concrete operations are as follows:
When rising decline on board the aircraft: all revolution speed of propeller or pitch synchronize to be increased or decreased；
When aircraft carries out rolling: port wing revolution speed of propeller or pitch change, starboard wing propeller inverse change；
When aircraft carries out pitching: vertical fin revolution speed of propeller or pitch change, abdomeinal fin propeller inverse change；
When aircraft is gone off course: vertical fin and abdomeinal fin revolution speed of propeller or pitch change, left and right airfoil root propeller
Inverse change (the differential deflection of elevon assists).
Flat when flying cruise, all propellers maintain same rotational speed, vertical fin and abdomeinal fin propeller the most reversely to become substantially
Change carrys out assistance for lifting aileron and carries out aircraft fore-and-aft control and trim.
Furthermore, it is necessary to explanation, the specific embodiment described in this specification, the shape of its parts and components, it is named
Titles etc. can be different.All equivalences done according to structure, feature and the principle of design described in patent of the present invention or simple change, all wrap
Include in the protection domain of patent of the present invention.Described can be embodied as by those skilled in the art
Example is made various amendment or supplements or use similar mode to substitute, without departing from the structure of the present invention or surmount this
Scope as defined in the claims, all should belong to protection scope of the present invention.
Claims (10)
1. a vertically taking off and landing flyer for distributed-power device layout, including fuselage (1), wing (2), empennage and propeller
(13), it is characterised in that: described fuselage (1) is semi-monocoque structure, and described fuselage (1) includes head, stage casing and tail, machine
Body (1) stage casing is cargo hold, is provided with symmetrical wing (2) in described fuselage (1) both sides, is provided with liter on described wing (2)
Fall aileron (4), is provided with winglet (5) on the wingtip of wing (2)；Described empennage includes vertical fin (6) and abdomeinal fin (7), described
Vertical fin (6) is provided with wingtip (8), and described abdomeinal fin (7) is provided with abdomeinal fin wingtip (9), is provided with power set on described wing (2)
(10), vertical fin (6) is provided with power set (10), and abdomeinal fin (7) is provided with power set (10), and described power set (10) output shaft is even
Connect propeller (3), rising and falling when described winglet (5), wingtip (8) do VTOL with abdomeinal fin wingtip (9) as aircraft
Frame.
2. a vertically taking off and landing flyer for distributed-power device layout, including fuselage (1), wing (2), empennage and propeller
(3), it is characterised in that: described fuselage (1) is semi-monocoque structure, and described fuselage (1) includes head, stage casing and tail, machine
Body (1) stage casing is cargo hold, is provided with symmetrical wing (2) in described fuselage (1) both sides, is provided with liter on described wing (2)
Fall aileron (4), is provided with winglet (5) on the wingtip of wing (2)；Described empennage includes vertical fin (6) and abdomeinal fin (7), described
Vertical fin (6) is provided with wingtip (8), and described abdomeinal fin (7) is provided with abdomeinal fin wingtip (9), is provided with at described fuselage (1) or wing (2) root
Power set (10), described power set (10) are connected propeller by gear-box with power transmission shaft, the described wing on fuselage (1)
Tip winglet (5), wingtip (8) and abdomeinal fin wingtip (9) do undercarriage during VTOL as aircraft.
The vertically taking off and landing flyer of a kind of distributed-power device layout the most according to claim 1 and 2, its feature exists
It is twin beams semi-monocoque structure and wing (2) is connected by strengthening bulkhead with fuselage (1) in: described wing (2).
The vertically taking off and landing flyer of a kind of distributed-power device layout the most according to claim 1 and 2, its feature exists
In: described wing (2) is swept-back wing, and described wing (2) control section is in " S ", and wing root to wingtip is provided with 3 ° to 5 ° negative twists and turns.
The vertically taking off and landing flyer of a kind of distributed-power device layout the most according to claim 1 and 2, its feature exists
In: described head and tail are respectively Demountable.
The vertically taking off and landing flyer of a kind of distributed-power device layout the most according to claim 1 and 2, its feature exists
In: described propeller (3) uses constant pitch airscrew or variable-pitch propeller.
The vertically taking off and landing flyer of a kind of distributed-power device layout the most according to claim 4, it is characterised in that: become
Machinery pitch-changing mechanism is connected away from propeller.
The vertically taking off and landing flyer of a kind of distributed-power device layout the most according to claim 1 and 2, its feature exists
In: described power set (10) are electromotor, and described each wing (2) is respectively equipped with two electromotors.
The vertically taking off and landing flyer of a kind of distributed-power device layout the most according to claim 1 and 2, its feature exists
In: described winglet (5) respectively with wingtip (8) and abdomeinal fin wingtip (9) in spatial vertical state.
10. fly according to the VTOL of in claim 1 or 2 any one described a kind of distributed-power device layout
Device, it is characterised in that: in head with tail, it is provided with electronic equipment and power supply.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610712566.6A CN106218887A (en) | 2016-08-22 | 2016-08-22 | A kind of vertically taking off and landing flyer of distributed-power device layout |
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| CN201610712566.6A CN106218887A (en) | 2016-08-22 | 2016-08-22 | A kind of vertically taking off and landing flyer of distributed-power device layout |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986001A (en) * | 2016-12-30 | 2017-07-28 | 马晓辉 | A kind of three-stage fixed-wing unmanned plane |
| CN107097949A (en) * | 2017-04-25 | 2017-08-29 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN107323660A (en) * | 2017-06-30 | 2017-11-07 | 马鞍山市赛迪智能科技有限公司 | A kind of VTOL method of dalta wing unmanned plane |
| CN107499506A (en) * | 2017-07-07 | 2017-12-22 | 清华大学 | A kind of distributed propulsion tailstock formula VTOL Fixed Wing AirVehicle |
| CN109760832A (en) * | 2019-03-28 | 2019-05-17 | 四川阿坝天铁翼科技有限公司 | A kind of VTOL fixed-wing unmanned vehicle |
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| CN110562433A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | X wing unmanned aerial vehicle |
| CN110562448A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | Tailstock type unmanned aerial vehicle |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| US20140217229A1 (en) * | 2011-09-27 | 2014-08-07 | Singapore Technologies Aerospace Ltd | Unmanned aerial vehicle |
| WO2016013933A1 (en) * | 2014-07-24 | 2016-01-28 | Atmos Uav B.V. | Aircraft with wing-borne flight mode and hover flight mode |
| US20160144957A1 (en) * | 2014-11-26 | 2016-05-26 | XCraft Enterprises, LLC | High speed multi-rotor vertical takeoff and landing aircraft |
| CN105730676A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN206202685U (en) * | 2016-08-22 | 2017-05-31 | 杭州迅蚁网络科技有限公司 | A kind of vertically taking off and landing flyer of distributed-power device layout |
-
2016
- 2016-08-22 CN CN201610712566.6A patent/CN106218887A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| US20140217229A1 (en) * | 2011-09-27 | 2014-08-07 | Singapore Technologies Aerospace Ltd | Unmanned aerial vehicle |
| WO2016013933A1 (en) * | 2014-07-24 | 2016-01-28 | Atmos Uav B.V. | Aircraft with wing-borne flight mode and hover flight mode |
| US20160144957A1 (en) * | 2014-11-26 | 2016-05-26 | XCraft Enterprises, LLC | High speed multi-rotor vertical takeoff and landing aircraft |
| CN105730676A (en) * | 2016-03-22 | 2016-07-06 | 王一 | Aircraft |
| CN206202685U (en) * | 2016-08-22 | 2017-05-31 | 杭州迅蚁网络科技有限公司 | A kind of vertically taking off and landing flyer of distributed-power device layout |
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106986001A (en) * | 2016-12-30 | 2017-07-28 | 马晓辉 | A kind of three-stage fixed-wing unmanned plane |
| CN107097949A (en) * | 2017-04-25 | 2017-08-29 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| US11479351B2 (en) | 2017-05-09 | 2022-10-25 | ST Engineering Aerospace Ltd. | Aerial vehicle |
| IL270521B (en) * | 2017-05-09 | 2022-09-01 | St Eng Aerospace Ltd | Aerial vehicle |
| EP3621875A4 (en) * | 2017-05-09 | 2021-01-27 | St Engineering Aerospace Ltd. | Aerial vehicle |
| CN107323660B (en) * | 2017-06-30 | 2020-01-17 | 马鞍山市赛迪智能科技有限公司 | Vertical take-off and landing method of delta-wing unmanned aerial vehicle |
| CN107323660A (en) * | 2017-06-30 | 2017-11-07 | 马鞍山市赛迪智能科技有限公司 | A kind of VTOL method of dalta wing unmanned plane |
| CN107499506A (en) * | 2017-07-07 | 2017-12-22 | 清华大学 | A kind of distributed propulsion tailstock formula VTOL Fixed Wing AirVehicle |
| CN111051197B (en) * | 2017-07-18 | 2023-04-04 | 新科宇航 | Asymmetric aircraft |
| CN111051197A (en) * | 2017-07-18 | 2020-04-21 | 新科宇航 | Asymmetric aircraft |
| IL272101B (en) * | 2017-07-18 | 2022-11-01 | St Eng Aerospace Ltd | Asymmetric aerial vehicle |
| IL272101B2 (en) * | 2017-07-18 | 2023-03-01 | St Eng Aerospace Ltd | Asymmetric aerial vehicle |
| EP3655318A4 (en) * | 2017-07-18 | 2021-03-03 | ST Engineering Aerospace Ltd. | Asymmetric aerial vehicle |
| US11358719B2 (en) | 2017-07-18 | 2022-06-14 | ST Engineering Aerospace Ltd. | Asymmetric aerial vehicle |
| CN109760832A (en) * | 2019-03-28 | 2019-05-17 | 四川阿坝天铁翼科技有限公司 | A kind of VTOL fixed-wing unmanned vehicle |
| CN110254720A (en) * | 2019-05-31 | 2019-09-20 | 中国航天空气动力技术研究院 | A kind of Flying-wing's solar energy unmanned plane |
| CN112141328A (en) * | 2019-06-27 | 2020-12-29 | 沃科波特有限公司 | Aircraft with a flight control device |
| CN112141328B (en) * | 2019-06-27 | 2023-11-24 | 沃科波特有限公司 | Aircraft |
| CN110562448A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | Tailstock type unmanned aerial vehicle |
| CN110562433A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | X wing unmanned aerial vehicle |
| CN113002764A (en) * | 2019-12-18 | 2021-06-22 | 上海峰飞航空科技有限公司 | Multi-rotor aircraft with multi-axis staggered layout |
| CN113002764B (en) * | 2019-12-18 | 2023-09-05 | 上海峰飞航空科技有限公司 | Multi-rotor aircraft with multi-axis staggered layout |
| CN115562040A (en) * | 2022-11-03 | 2023-01-03 | 清华大学 | Optimal design method for vertical take-off and landing fixed wing aircraft electric propulsion system |
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