CN108639328A - A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone - Google Patents
A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone Download PDFInfo
- Publication number
- CN108639328A CN108639328A CN201810462467.6A CN201810462467A CN108639328A CN 108639328 A CN108639328 A CN 108639328A CN 201810462467 A CN201810462467 A CN 201810462467A CN 108639328 A CN108639328 A CN 108639328A
- Authority
- CN
- China
- Prior art keywords
- wing
- fuselage
- unmanned plane
- component
- head
- 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
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
Abstract
The invention discloses a kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone.Scheme includes：Frame assembly, head-shield, hood component, power spin paddle component, symmetrical wing components.Its main feature is that four wings are laid out relative to fuselage in cruciform symmetry, a power spin paddle component is separately included on four wings, the undercarriage with damping device is used in the lower part of its wing；In addition head-shield hood component is located at air drag of the fuselage both ends for reducing cruising level flight process.The unmanned plane ensures its attitude stabilization in VTOL or hovering phase by the Differential Control to four airscrew thrusts, and in horizontal flight, unmanned machine rolling, the maneuvers such as yaw are controlled by trailing edge flap and aileron；Present invention is particularly suitable for application in Shipborne UAV, the fields such as electric power line inspection or higher to maneuverability requirement, speed, the higher occasion of safety.
Description
Technical field
The present invention relates to technical field of aerospace, more particularly to a kind of tailstock formula vertical take-off and landing drone.
Background technology
The unmanned plane of country's mainstream includes two major classes at present, and one kind directly provides the gyroplane of lift by propeller, another
Class generates the fixed-wing aircraft of lift by wing.This two classes unmanned plane respectively has its advantage and disadvantage, and gyroplane biggest advantage is can be real
Existing VTOL, the operations such as hovering, disadvantage are that cruising speed is relatively low, and energy efficiency is low, and the cruise time is short etc.；Fixed-wing
Unmanned plane has speed fast, and the cruise time is long, the high advantage of energy efficiency, but it cannot achieve VTOL and relies on certain
The airstrips of distance can not hover；Therefore there is scholar by fixed-wing unmanned plane during flying is efficient and gyroplane can be real in recent years
The advantages of existing VTOL and hovering, which combines, designs the novel vertical take-off and landing drone of many types.Such as application No. is
Scheme described in CN201510492472.8, when unmanned plane takes off or needs hovering, underbelly can revolve more folding and unfolding
Wing component is unfolded, to provide VTOL and hovering ability；When unmanned plane cruises, more rotor assemblies take in fuselage interior, lean on tail
Portion's actuating unit provides the thrust needed for unmanned plane flight forward, this scheme be only realize fixed-wing unmanned plane and rotor without
Man-machine simple combination, the trust engine of its tail portion becomes extra component when the unmanned plane of the program hovers, and increases hovering
When additional heavy burden, in horizontal flight, the fixed-wing component taken in cabin then becomes extra component, when equally increasing flat fly
Additional heavy burden, can not give full play to the function of unmanned plane various components.For another example application No. is 201710178417.0
Tilting rotor wing unmanned aerial vehicle, when taking off with hovering, rotor plane is perpendicular to aircraft gravity direction, and in horizontal flight, rotor is flat
Face and the earth horizontal plane, this kind of unmanned plane needs to change self structure during flight attitude switches, for structure
Changed system is increasingly complex when carrying out design of control law, and in addition it is flat when flying equally to influence it for variable rotor structure
Aerodynamic quality, increase additional air drag.
In addition, conventional VTOL fixed-wing unmanned plane effective operating mechanism when hovering is with horizontal flight is only each other
It is vertical, when unusual condition occurs in the type unmanned plane, such as occur some control rudder face failure in flat fly, unmanned plane just needs
Task can not be continued to execute by being forced landing, therefore its fault-tolerance is relatively low；Secondly, the type unmanned plane is only about passing through fuselage
Perpendicular is symmetrical, is divided into up and down in flat fly, and be difficult to realize high maneuverability and complicated maneuver, therefore
How to realize that high maneuverability and complicated maneuver become the widely applied key of unmanned plane.The machine of axially symmetric structure of the present invention
Wing solution realizes the high maneuverability of unmanned plane and the maneuver of complexity and enhances its fault-tolerance.
Invention content
Present invention seek to address that its topology layout of existing vertical take-off and landing drone aerodynamic drag in horizontal flight is larger, patrol
Speed of a ship or plane degree is relatively low, and maneuverability cannot be satisfied the defect of special occasions demand with safety, such as in carrier-borne scounting aeroplane
A safe, the mobility strong of middle needs, cruising speed height can VTOL unmanned plane.
To achieve the goals above, the present invention is laid out using a kind of wing aerodynamic of cross axially symmetric structure to improve its machine
Dynamic flexibility, reduces air drag when horizontal flight, using four symmetrical power spins using streamline fuselage
Paddle puts down winged onward impulse to realize VTOL and provide, and scheme includes frame assembly, head-shield, hood component, power spiral shell
Paddle component is revolved, symmetrical wing components symmetrically have a two layers of meaning here, and it with respect to the installation site of fuselage is symmetrical side that one, which is wing,
Formula is installed, secondly be aerofoil profile used in wing being symmetrical airfoil.
Further, the unmanned plane is in VTOL and hovering stage, by the propeller of four similar quadrotors
Static thrust is provided, the stabilization of unmanned plane is kept；Directly pass through fuselage in the process for switching to cruising level flight by hovering flight state
Vert to realize, the design of axisymmetric aerodynamic arrangement can vert to any direction realizes cruising level flight；It is flat in cruise
Fly power before being provided by four propellers during flying.
The frame assembly can be effectively increased load storage capacity using cylindrical structure to fuselage interior, for fuselage outside
Portion can reduce aerodynamic drag, and be arranged symmetrically four wing mounting bases on the outside, and fuselage is the main load of unmanned plane and load
Component, in addition frame assembly also act as connection wing components, head-shield, the effect of hood component.
The hood assembly, including unmanned nose shell and air speed flowmeter sensor, head-shield are having the same with unmanned aerial vehicle body
Maximum radius is installed on front fuselage, for reducing air drag head-on, and provides pitot meter sensor mounting hole seat.
The hood component is installed on back body with unmanned aerial vehicle body maximum radius having the same, for weakening machine
The air separation effect of body tail portion, and then air drag when horizontal flight is reduced, in addition hood component also includes that near-earth senses
Device exploration hole position.
The power spin paddle component, including four brshless DC motors, four electricity are adjusted, four motor mounting racks and four
A propeller, each brushless motor configure a propeller and on U-shaped electric machine supports, and four electricity are adjusted passes through magic respectively
It is viscous to be attached to u-bracket side, it is used for fixing brushless motor on the upside of U-shaped electric machine support；Holder is consolidated by installing screw
It is scheduled on wing.
The symmetrical wing components are mounted in the corresponding wing mounting base of fuselage, and using symmetrical airfoil angle of sweep
Mode is provided with U-shaped electric machine support mounting hole in wing middle section position, is located along the same line in the lower end of wing with mounting hole
Unmanned plane with cushioning effect is installed to rise and fall holder, four holders that rise and fall are separately mounted to the middle section position of four wings, are
Unmanned plane provides stable support when ground is stopped, and in addition wing components also include a trailing edge flap close to fuselage side
It is each right in order to reduce aerodynamic drag with the aileron close to wing tip side, and the steering engine of responsible driving aileron and wing flap deflection
Two steering engines on the wing are claimed to be inlaid in inside wing by steering engine mounting groove.
By above-mentioned design organization mode, head is directed toward above the ground this unmanned plane before take-off, and is relied on and be installed on
The undercarriage that wing interrupts provides stabilization support force when stop, and after take off, unmanned plane can be with first as quadrotor
It realizes hovering, then realizes horizontal flight by verting fuselage；In the aerodynamic configuration and symmetrical airfoil of cruciform symmetry structure
It chooses, its unmanned plane can be made not have to distinguish face up and down in horizontal flight, also assume that a certain moment unmanned plane court
A direction horizontal flight, if unmanned plane needs rearward to reverse end for end at this time, this unmanned plane can be acted by half of somersault come real
Existing, i.e., unmanned plane comes back 90 degree first, and head points into the sky at this time, and and then unmanned plane, which continues to swing back 90 degree, can be realized u-turn
Maneuvering flight；Due to axisymmetric Design of Aerodynamic Configuration, so that it is not had upper and lower point, need to only be operated at this time by suitable rudder face
It can realize continuation horizontal flight, action is leveled off without carrying out 180 degree rolling again as Conventional pneumatic airplane；
Stalling angle of unmanned plane during Posture exchange can be effectively increased using trailing edge flap, to reduce Posture exchange process
Difficulty and increase the safety of Posture exchange, in addition, the present invention is while ensureing unmanned plane super flexible nature, using making it
The pneumatic structure layout that air drag is preferably minimized.
Description of the drawings
Below by attached drawing, the present invention will be described
Fig. 1 New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone overall schematics
Fig. 2 New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone frame assembly schematic diagrames
Fig. 3 New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone hood assembly schematic diagrames
Fig. 4 New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone hood component diagrams
Fig. 5 New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone power spin paddle component diagrams
Fig. 6 New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone wing components schematic diagrames
Fig. 7 New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone hovering posture schematic diagram
Specific implementation mode
The present invention is described in detail below in conjunction with the accompanying drawings.
As shown in Figure 1, New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone of the present invention, including frame assembly
102, hood assembly 101, hood component 104, power spin paddle component 103, symmetrical wing components 105.Wing components are in cross
Symmetrical structure is uniformly mounted on fuselage surrounding, and the aerodynamic arrangement of this symmetrical structure can make this unmanned plane have very strong machine
Dynamic performance, head-shield and hood component are separately mounted to the rear and front end of fuselage, and power spin paddle component passes through on wing
Mounting groove position 601 is fixed on wing middle section position, and this mounting means of symmetrical wing and power spin paddle component makes power
Propeller component is equally in that cruciform symmetry is laid out relative to fuselage.
It is illustrated in figure 2 frame assembly, there are four duplicate symmetrical wing mounting bases 201 respectively for surrounding, every
Skeleton in a mounting base comprising three location holes for symmetrical wing and fuselage is attached, in order to be more convenient arrangement load and
The inside for increasing the structural strength fuselage of fuselage is arranged using cubic space.
It needs to configure suitable head-shield and tail for unmanned aerial vehicle body in the flat aerodynamic drag for flying over journey to reduce unmanned plane
Shade assembly, as shown in Figure 3, Figure 4, respectively the head-shield of unmanned plane and hood component, head-shield and hood pass through glue bond mode
It is connected with frame assembly.The air speed flowmeter sensor 301 for including in hood assembly is located at head-shield hub head end position, out of head-shield
Portion is inserted into installation outward.In hood component totally four near-earth sensor exploration holes 402 be be distributed in hood component 401 after
End position.
Power spin paddle component as shown in figure 5, comprising propeller 501, brshless DC motor 502, electron speed regulator 503,
Motor mounting and fixing bracket 504.Propeller is directly connected with brshless DC motor using twayblade, and brushless motor passes through its bottom
Screw hole is mounted on fixing bracket, and electron speed regulator, electronic speed regulation are equipped with by magic stick in support bracket fastened side
Device is for driving brshless DC motor to operate.Three screw holes of its mounting bracket side and wing components (as shown in Figure 6)
On holder mounting base 601 above screw hole it is corresponding.
Symmetrical wing components are illustrated in figure 6, component includes swept back wing main body 602, and electric machine support mounting base 601 is used
In the steering engine 603 and 609 of driving control surface deflection, steering engine mounting groove 604, the connection guide 608 of steering engine and rudder face, trailing edge flap rudder
Face 607, aileron rudder face 605, undercarriage 606 form.Steering engine is inlaid in steering engine mounting groove, and steering engine cursor passes through guide rod 608
It is connect with wing flap and aileron rudder face, to realize the rotation by controlling steering engine come the deflection of primary control surface.Undercarriage 606 carries
Spring shock absorption transposition can effectively reduce unmanned plane landing process of contacting to earth and be injured caused by wing and fuselage.Wing-body
Side has mounting hole corresponding with frame assembly position, the two to be attached by carbon bar.In addition the selection of symmetrical airfoil makes
This unmanned plane has axially symmetric structure truly, make its do not have to distinguish during flat fly up and down, so as to
Enough realize special maneuver.
Finally, it should be noted that：Above invention embodiment is only used to illustrate the technical scheme of the present invention rather than right
It is limited.It is all within the spirit and principle of the present invention program made by all any modification, equivalent and improvement etc., should all include
In the protection domain of the present invention program.
Claims (5)
1. a kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone, which is characterized in that including frame assembly, head
Cover, hood component, power spin paddle component, symmetrical wing components；Unmanned plane is to switch to level flight condition by floating state straight
Fuselage realization of verting was connected, keeps posture steady by the static thrust of power spin paddle output in hovering and VTOL stage
It is fixed, in the flat winged stage maneuvers such as rolling yaw are realized by trailing edge flap and aileron.
2. unmanned plane according to claim 1, which is characterized in that wing components are relative to the gas that fuselage is in cruciform symmetry structure
Dynamic layout, no canard and empennage mechanism, it is in cruciform symmetry layout structure that power spin paddle, which is mounted on wing equally,.
3. wing components according to claim 2, which is characterized in that the distribution form at symmetrical airfoil angle of sweep is used, and
The trailing edge flap close to fuselage side and the aileron at wing tip are provided on wing；The wing components also include embedded wing
Interior steering engine is used to drive the deflection of trailing edge flap and aileron rudder face, and power spin paddle group is equipped in the middle section position of wing
Part mounting base.
4. power spin paddle component according to claim 3, which is characterized in that power spin paddle component is mounted in wing
Fragment position, and it is located at the leading edge of wing, opposite same as fuselage in cruciform symmetry layout, unmanned plane is in VTOL and hangs
Stopping the stage provides stable static thrust, in flat winged stage verting due to fuselage, power spin paddle component provide unmanned plane to
The power of preceding flight.
5. head-shield, hood component according to claim 1, which is characterized in that before head-shield and hood are separately mounted to fuselage
Both ends afterwards；Include head-shield and air speed flowmeter sensor in hood assembly, air speed flowmeter sensor is mounted on the center of head-shield；Hood
It include near-earth sensor mounting hole in component.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810462467.6A CN108639328A (en) | 2018-05-15 | 2018-05-15 | A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810462467.6A CN108639328A (en) | 2018-05-15 | 2018-05-15 | A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108639328A true CN108639328A (en) | 2018-10-12 |
Family
ID=63755735
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810462467.6A Pending CN108639328A (en) | 2018-05-15 | 2018-05-15 | A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108639328A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109269363A (en) * | 2018-11-16 | 2019-01-25 | 湖南省军合科技有限公司 | A kind of Flying-wing individual soldier hand-thrown type scout missile |
| CN109573006A (en) * | 2019-01-30 | 2019-04-05 | 深圳市道通智能航空技术有限公司 | A kind of tilting rotor wing unmanned aerial vehicle and its wing components |
| CN110466754A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
| CN110775262A (en) * | 2019-10-22 | 2020-02-11 | 上海交通大学 | Tailstock type sea-air cross-domain aircraft device based on four-rotor driving mode |
| CN111439370A (en) * | 2020-04-21 | 2020-07-24 | 中国商用飞机有限责任公司 | High lift system and flap control method |
| WO2020190223A1 (en) * | 2019-03-21 | 2020-09-24 | Acikel Guerkan | Vtol tilting fuselage winged frame multirotor aircraft |
| CN111846226A (en) * | 2020-07-28 | 2020-10-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and control method thereof |
| CN112407270A (en) * | 2020-12-01 | 2021-02-26 | 中航金城无人系统有限公司 | Tailstock type vertical take-off and landing aircraft without control surface control |
| CN112799427A (en) * | 2020-12-28 | 2021-05-14 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned aerial vehicle control method |
| US11827348B2 (en) | 2019-03-21 | 2023-11-28 | Gurkan ACIKEL | VTOL tilting fuselage winged frame multirotor aircraft |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| CN106184738A (en) * | 2016-06-17 | 2016-12-07 | 北京航空航天大学 | A kind of dismountable tailstock formula VUAV |
| CN106240814A (en) * | 2016-08-10 | 2016-12-21 | 西北工业大学 | A kind of power-controlled tail sitting posture mixed layout vertically taking off and landing flyer |
| CN107406150A (en) * | 2015-02-05 | 2017-11-28 | 埃柔波提克斯有限公司 | Landing and charging system for unmanned plane |
-
2018
- 2018-05-15 CN CN201810462467.6A patent/CN108639328A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20050178879A1 (en) * | 2004-01-15 | 2005-08-18 | Youbin Mao | VTOL tailsitter flying wing |
| CN107406150A (en) * | 2015-02-05 | 2017-11-28 | 埃柔波提克斯有限公司 | Landing and charging system for unmanned plane |
| CN106184738A (en) * | 2016-06-17 | 2016-12-07 | 北京航空航天大学 | A kind of dismountable tailstock formula VUAV |
| CN106240814A (en) * | 2016-08-10 | 2016-12-21 | 西北工业大学 | A kind of power-controlled tail sitting posture mixed layout vertically taking off and landing flyer |
Non-Patent Citations (1)
| Title |
|---|
| 唐伟: "微小型电动垂直起降无人机总体设计方法及特殊参数影响", 《航空学报》 * |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109269363A (en) * | 2018-11-16 | 2019-01-25 | 湖南省军合科技有限公司 | A kind of Flying-wing individual soldier hand-thrown type scout missile |
| CN109573006A (en) * | 2019-01-30 | 2019-04-05 | 深圳市道通智能航空技术有限公司 | A kind of tilting rotor wing unmanned aerial vehicle and its wing components |
| CN109573006B (en) * | 2019-01-30 | 2024-04-12 | 深圳市道通智能航空技术股份有限公司 | Tilt rotor unmanned aerial vehicle and wing subassembly thereof |
| WO2020190223A1 (en) * | 2019-03-21 | 2020-09-24 | Acikel Guerkan | Vtol tilting fuselage winged frame multirotor aircraft |
| US11827348B2 (en) | 2019-03-21 | 2023-11-28 | Gurkan ACIKEL | VTOL tilting fuselage winged frame multirotor aircraft |
| CN110466754A (en) * | 2019-09-09 | 2019-11-19 | 西安交通大学 | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
| CN110775262A (en) * | 2019-10-22 | 2020-02-11 | 上海交通大学 | Tailstock type sea-air cross-domain aircraft device based on four-rotor driving mode |
| CN110775262B (en) * | 2019-10-22 | 2022-11-18 | 上海交通大学 | Tailstock type sea-air cross-domain aircraft device based on four-rotor driving mode |
| CN111439370B (en) * | 2020-04-21 | 2021-06-15 | 中国商用飞机有限责任公司 | High lift system and flap control method |
| CN111439370A (en) * | 2020-04-21 | 2020-07-24 | 中国商用飞机有限责任公司 | High lift system and flap control method |
| CN111846226A (en) * | 2020-07-28 | 2020-10-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and control method thereof |
| CN112407270A (en) * | 2020-12-01 | 2021-02-26 | 中航金城无人系统有限公司 | Tailstock type vertical take-off and landing aircraft without control surface control |
| CN112799427A (en) * | 2020-12-28 | 2021-05-14 | 尚良仲毅(沈阳)高新科技有限公司 | Unmanned aerial vehicle control method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108639328A (en) | A kind of New Tail A seating axial symmetry multiple propeller vertical take-off and landing drone | |
| KR102594866B1 (en) | electric tiltrotor aircraft | |
| US11634222B2 (en) | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system | |
| RU180474U1 (en) | Vertical takeoff and landing airplane | |
| US5419514A (en) | VTOL aircraft control method | |
| EP3604122B1 (en) | Aircraft with super high aspect ratio based on self-unfolding folding wing technology | |
| CN104085532B (en) | A kind of control method of tilting rotor transport plane | |
| CN106882371A (en) | A kind of hybrid tilting rotor wing unmanned aerial vehicle | |
| US20140312177A1 (en) | Coaxial rotor/wing aircraft | |
| CN104743112B (en) | Novel tilt wing aircraft | |
| CN111315655B (en) | Assembly of three composite wings for an air, water, land or space vehicle | |
| CN109849604A (en) | Folding rotor triphibian | |
| US10343774B2 (en) | Quad rotor aircraft with fixed wing and variable tail surfaces | |
| CN202728574U (en) | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function | |
| CN106143895B (en) | Thrust type tilt rotor aircraft | |
| CN107089328A (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft and its flight control method | |
| CN106218887A (en) | A kind of vertically taking off and landing flyer of distributed-power device layout | |
| CN105775117A (en) | Helicopter taking off and landing vertically and flying horizontally and application thereof | |
| CN103963959A (en) | Hovering type folding wing lifting body aircraft based on variable centroid technology | |
| CN109795682A (en) | A kind of efficient tail sitting posture VTOL Fixed Wing AirVehicle and its control method | |
| CN111196346A (en) | Distributed electric propulsion tilt rotor unmanned aerial vehicle | |
| CN205738073U (en) | A kind of helicopter of VTOL horizontal flight | |
| CN103754360B (en) | One kind flying disc type gyroplane | |
| CN109533319A (en) | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing | |
| CN110466754A (en) | A kind of tailstock formula tilting rotor vertical take-off and landing drone |
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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20181012 |
|
| WD01 | Invention patent application deemed withdrawn after publication |