CN105947192A - Tilting double-duct unmanned aerial vehicle - Google Patents
Tilting double-duct unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105947192A CN105947192A CN201610382189.4A CN201610382189A CN105947192A CN 105947192 A CN105947192 A CN 105947192A CN 201610382189 A CN201610382189 A CN 201610382189A CN 105947192 A CN105947192 A CN 105947192A
- Authority
- CN
- China
- Prior art keywords
- duct
- wing
- unmanned aerial
- aerial vehicle
- central wing
- 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
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 10
- 230000003187 abdominal effect Effects 0.000 claims description 3
- 238000005728 strengthening Methods 0.000 claims description 3
- 238000011176 pooling Methods 0.000 claims description 2
- 210000001015 abdomen Anatomy 0.000 abstract 1
- 238000006243 chemical reaction Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000005096 rolling process Methods 0.000 description 3
- 238000005183 dynamical system Methods 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 230000005611 electricity Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- 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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The invention discloses a tilting double-duct unmanned aerial vehicle and belongs to the technical field of unmanned aerial vehicles. The tilting double-duct unmanned aerial vehicle comprises a central wing, flight control equipment, avionics equipment, electrical equipment and a duct tilting control mechanism, wherein the flight control equipment, the avionics equipment, the electrical equipment and the duct tilting control mechanism are arranged inside the central wing, and the avionics equipment, the electrical equipment and the duct tilting control mechanism are connected with the flight control equipment. Short arms, ducts and outer wings are distributed on the two sides of the central wing from inside to outside; the ducts and the outer wings are connected into a whole; the ducts are connected with the central wing through the short arms; the ducts and the outer wings can tilt around the short arms; motors and propellers are arranged inside the ducts, and control surfaces are arranged on the back portions of the ducts; a suspension-mounting connector is arranged at the belly portion of the central wing and used for mounting and fixing a suspension-mounting module; and an undercarriage is installed below the central wing. The unmanned aerial vehicle is small in requirement for taking off and landing sites, high in flight efficiency and flexible to use, and has the vertical taking-off and landing capacity, hovering capacity and rapid cruising capacity.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, be specifically related to one and vert double duct unmanned aerial vehicle.
Background technology
In recent years, China's unmanned air vehicle technique quickly grows, and unmanned plane is widely used in military and civilian neck
Territory.In order to expand the range of application of unmanned plane, the use making unmanned plane is more convenient, and people have carried out many
Plant new ideas unmanned plane project study.Wherein, tilting duct unmanned aerial vehicle has VTOL, aerial simultaneously
Hovering and quick cruising ability, it has also become the focus in current unmanned plane research and development field.
Tradition tilting duct unmanned aerial vehicle typically uses multiple duct (general more than three), and by part duct
It is arranged in aircraft body.This unmanned plane power decentralized, efficiency are low, dynamical system and control system multiple
Miscellaneous；Owing to aircraft body domestic demand installs duct, thus internal stowage space is less, uses difficulty.
Summary of the invention
The object of the invention: provide one to vert double duct unmanned aerial vehicle, unmanned plane landing site demand is little for this, fly
Line efficiency is high, it is flexible to use, and loading space is big.
Technical scheme: one is verted double duct unmanned aerial vehicle, including: in central wing and central wing
The flight control unit in portion, Aerial Electronic Equipment, electrical equipment, duct vert operating mechanism；Aerial Electronic Equipment, electricity
Gas equipment, the duct operating mechanism that verts is connected with flight control unit respectively.
Central wing both sides are distributed galianconism, duct, outer wing, duct and outer wing from inside to outside and link into an integrated entity,
And be connected with central wing by galianconism, duct and outer wing can vert around galianconism, duct be internally provided with motor with
Propeller, rear portion is provided with rudder face；Central wing abdominal part is provided with carry joint, is used for mounting and fixing carry
Module, is provided with undercarriage below central wing.
Preferably, described duct is internally provided with structural strengthening parts.
Preferably, described carry module is detachable.
Preferably, described undercarriage is the skid landing gear with pooling feature.
Preferably, described central wing rear edge part is provided with central wing trailing edge rudder face.
Preferably, described outer wing rear edge part is provided with outer wing trailing edge rudder face.
Technical solution of the present invention advantage: providing a kind of double duct unmanned aerial vehicle, duct is symmetrically distributed in central wing two
Side, saves main body installing space, and loading space is big.This unmanned plane landing site demand is little, flight efficiency height,
Use flexibly, there is VTOL, hovering and quick cruising ability.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of double duct unmanned aerial vehicle one preferred embodiment that verts of the present invention.
Fig. 2 is the taking off of a kind of double duct unmanned aerial vehicle that verts of the present invention, duty of landing configuration picture.
Fig. 3 is to fly before a kind of double duct unmanned aerial vehicle that verts of the present invention and change, slow down and conversion work state
Configuration picture.
Fig. 4 be a kind of double duct unmanned aerial vehicle that verts of the present invention fixed-wing before fly duty configuration picture.
Wherein, 1-structural strengthening parts, 2-duct, 3-propeller, 4-motor, 5-rudder face, 6-flies control
Control equipment, 7-central wing, 8-central wing trailing edge rudder face, 9-Aerial Electronic Equipment, 10-galianconism, 11-outer wing trailing edge
Rudder face, 12-outer wing, 13-electrical equipment, 14-carry module, 15-carry joint, 16-duct verts behaviour
Vertical structure, 17-skid landing gear.
Detailed description of the invention
Clearer, below in conjunction with the present invention for the purpose making the present invention implement, technical scheme and advantage
Accompanying drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the present invention.Attached
In figure, the most same or similar label represents same or similar element or has same or like
The element of function.Described embodiment is a part of embodiment of the present invention rather than whole enforcement
Example.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to be used for explaining the present invention, and
It is not considered as limiting the invention.Based on the embodiment in the present invention, those of ordinary skill in the art
The every other embodiment obtained under not making creative work premise, broadly falls into present invention protection
Scope.Below in conjunction with the accompanying drawings embodiments of the invention are described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " horizontal stroke
To ", "front", "rear", "left", "right", " vertically ", " level ", " top ",
Orientation or the position relationship of the instruction such as " end " " interior ", " outward " are based on orientation shown in the drawings or position
Put relation, be for only for ease of and describe the present invention and simplify description rather than instruction or the dress of hint indication
Put or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that
Limiting the scope of the invention.
Below in conjunction with the accompanying drawings embodiments of the invention are described in detail, refer to Fig. 1；
One is verted double duct unmanned aerial vehicle, including: the flight control unit within central wing 7 and central wing
6, Aerial Electronic Equipment 9, electrical equipment 13, duct vert operating mechanism 16；During central wing 7 afterbody is provided with
Centre wing trailing edge rudder face 8；Central wing 7 both sides are distributed galianconism 10, duct 2, outer wing 12 from inside to outside, contain
Road 2 and outer wing 2 link into an integrated entity, and are connected with central wing 7 by galianconism 10, and duct 2 is with outer
The wing 12 can vert around galianconism 10, and outer wing 12 trailing edge is provided with outer wing trailing edge rudder face 11；Before duct 2 inner chamber
Portion is provided with structural reinforcement member 1, motor 4 and propeller 3 and is installed on rear side of structural reinforcement member 1, propeller 3
Being connected with rotor, duct rear portion is provided with rudder face 5；Central wing 7 abdominal part is provided with carry joint 15,
Carry module 14 mounts and is fixed on carry joint 15, below central wing 7 and outside carry module 14
Side is provided with skid landing gear 17.
Aerial Electronic Equipment 9 within central wing, electrical equipment 13, duct vert operating mechanism 16 respectively with fly
Row control equipment 6 is connected.The duct operating mechanism 16 that verts can handle duct 2 and outer wing 12 around galianconism 10
Vert.Electrical equipment 13 provides electric energy for motor 4, and exports control signal to motor 4, and motor 4 carries
Dynamic propeller 3 rotates.Aerial Electronic Equipment 9 provides the unmanned seat in the plane needed for flight control for flight control unit 6
Put, attitude and state of flight signal.Flight control unit 6 controls unmanned according to the control instruction received
Machine flies.
The duct layout of this novel unmanned plane, has power concentration, flight efficiency height, dynamical system and control
System practicality advantage flexibly；Owing to duct is symmetrically distributed in central wing both sides, save main body installing space,
Loading space is bigger.This unmanned plane landing site demand is little, uses flexibly, has VTOL, overhead suspension
Stop and quick cruising ability.
Vert five kinds of typical duty configurations of unmanned plane of the present invention are described as follows:
1, unmanned plane takes off: as in figure 2 it is shown, unmanned plane is in landing configuration, duct vertically upward, two
Propeller in individual duct rotates in opposite directions, it is provided that upwards thrust, and unmanned plane takes off.In this state
Under, by two duct thrust asymmetric control aircraft rollings, controlled by the rudder face at two duct rear portions
Aircraft pitch and driftage.When needing, unmanned plane can be made aloft to hover.
2, fly before unmanned plane and change: as it is shown on figure 3, by duct vert operating mechanism control duct with
Outer wing tilts forward certain angle together about galianconism, keeps central wing to be in horizontal attitude during verting.
Now, unmanned plane is in conversion configurations, and duct produces upwards thrust and forward pulling force simultaneously, unmanned plane to
Preacceleration, aerofoil produces lift.In this condition, rolled by left and right duct thrust asymmetric control aircraft
Turn and driftage, control aircraft pitch and driftage by duct rear portion rudder face.
3, unmanned plane quickly cruises flying configuration before fixed-wing: as shown in Figure 4, when unmanned plane speed reaches
During certain value, aerofoil lift and gravitational equilibrium, control duct and outer wing one by the duct operating mechanism that verts
With verting, until duct level.Now, unmanned plane flies configuration before being in fixed-wing, and duct flies before providing
Pulling force, unmanned plane quickly cruises.In this condition, inclined by left and right duct pulling force asymmetric control aircraft
Boat, controls aircraft pitch by central wing trailing edge rudder face, controls aircraft rolling by outer wing trailing edge rudder face.
4, unmanned plane slows down and changes: as it is shown on figure 3, before unmanned plane landing, verted manipulation by duct
Mechanism controls duct and outer wing upwards vert together about galianconism certain angle, keep central wing during verting
It is in horizontal attitude.Now, unmanned plane is in conversion configurations, and duct produces upwards thrust and forward simultaneously
Pulling force, unmanned plane speed reduces.In this condition, rolled by left and right duct thrust asymmetric control aircraft
Turn and driftage, control aircraft pitch and driftage by duct rear portion rudder face.
5, unmanned plane landing: as in figure 2 it is shown, when unmanned plane is close to landing place, verted by duct
Operating mechanism controls duct and verts together about galianconism with outer wing, until duct is vertically upward.Now, unmanned
Machine is in landing configuration, and duct provides upwards thrust.In this condition, by the thrust of two ducts not
Symmetrical control aircraft rolling, controls aircraft pitch and driftage by the rudder face at two duct rear portions.Arrive fall
After above pick-up point, being gradually reduced duct thrust, unmanned plane slowly lands and lands.
Last it is noted that above example is only in order to illustrate technical scheme, rather than right
It limits.Although the present invention being described in detail with reference to previous embodiment, the common skill of this area
Art personnel it is understood that the technical scheme described in foregoing embodiments still can be modified by it,
Or wherein portion of techniques feature is carried out equivalent；And these amendments or replacement, do not make corresponding
The essence of technical scheme departs from the spirit and scope of various embodiments of the present invention technical scheme.
Claims (6)
1. double duct unmanned aerial vehicle that verts, it is characterised in that including: central wing (7) and central wing
Internal flight control unit (6), Aerial Electronic Equipment (9), electrical equipment (13), duct vert manipulation machine
Structure (16)；Aerial Electronic Equipment (9), electrical equipment (13), duct vert operating mechanism (16) respectively with fly
Row control equipment (6) is connected；
Central wing (7) both sides are distributed galianconism (10), duct (2), outer wing (12) from inside to outside, contain
Road (2) and outer wing (12) link into an integrated entity, and are connected with central wing (7) by galianconism (10), and
And duct (2) and outer wing (12) vert around galianconism (10), duct (2) is internally provided with motor (4)
With propeller (3), rear portion is provided with rudder face (5)；Central wing (7) abdominal part is provided with carry joint (15),
Carry joint (15) is used for mounting and fixing carry module (14), and central wing (7) lower section is provided with rises and falls
Frame (17).
One the most according to claim 1 is verted double duct unmanned aerial vehicle, it is characterised in that: described duct
(2) structural strengthening parts (1) it are internally provided with.
One the most according to claim 1 is verted double duct unmanned aerial vehicle, it is characterised in that: described carry
Module (14) is detachable casing.
One the most according to claim 1 is verted double duct unmanned aerial vehicle, it is characterised in that rise and fall described in:
Frame (17) is the skid landing gear with pooling feature.
One the most according to claim 1 is verted double duct unmanned aerial vehicle, it is characterised in that: described central authorities
The wing (7) rear edge part is provided with central wing trailing edge rudder face (8).
One the most according to claim 1 is verted double duct unmanned aerial vehicle, it is characterised in that: described outer wing
(12) rear edge part is provided with outer wing trailing edge rudder face (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610382189.4A CN105947192A (en) | 2016-06-01 | 2016-06-01 | Tilting double-duct unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610382189.4A CN105947192A (en) | 2016-06-01 | 2016-06-01 | Tilting double-duct unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105947192A true CN105947192A (en) | 2016-09-21 |
Family
ID=56908473
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610382189.4A Pending CN105947192A (en) | 2016-06-01 | 2016-06-01 | Tilting double-duct unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105947192A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106927031A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
| CN107021208A (en) * | 2017-04-21 | 2017-08-08 | 陆艳辉 | The tail sitting posture VUAV and control method of a kind of utilization duct |
| CN107697281A (en) * | 2017-09-20 | 2018-02-16 | 大连民族大学 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
| CN108791868A (en) * | 2018-07-31 | 2018-11-13 | 刘浩然 | A kind of new transport unmanned plane of safety and stability |
| WO2018209911A1 (en) * | 2017-05-16 | 2018-11-22 | 华南理工大学 | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system |
| CN110254703A (en) * | 2019-06-28 | 2019-09-20 | 福州大学 | A tilting dual-rotor automatic hovering T-type unmanned aerial vehicle system |
| CN110281719A (en) * | 2019-06-28 | 2019-09-27 | 长城汽车股份有限公司 | Flight vehicle and its mode conversion method |
| CN113911334A (en) * | 2021-11-12 | 2022-01-11 | 北京航空航天大学 | Pneumatic layout of tilting duct type aircraft |
| CN114148516A (en) * | 2021-12-06 | 2022-03-08 | 浙江大学 | Distributed tilting duct vertical take-off and landing aircraft and control method thereof |
| CN114148513A (en) * | 2021-12-13 | 2022-03-08 | 浙江云途飞行器技术有限公司 | A UAV take-off and landing platform and a UAV take-off and landing system |
| CN114313251A (en) * | 2022-03-03 | 2022-04-12 | 天津斑斓航空科技有限公司 | Combined type aircraft active tilting structure and aircraft |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106927031B (en) * | 2017-03-27 | 2018-12-21 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
| CN106927031A (en) * | 2017-03-27 | 2017-07-07 | 上海珞鹏航空科技有限公司成都研发分公司 | A kind of double duct unmanned aerial vehicles of the horizontal cloth collaboration manipulation of bi-motor |
| CN107021208A (en) * | 2017-04-21 | 2017-08-08 | 陆艳辉 | The tail sitting posture VUAV and control method of a kind of utilization duct |
| US11634222B2 (en) | 2017-05-16 | 2023-04-25 | South China University Of Technology | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system |
| WO2018209911A1 (en) * | 2017-05-16 | 2018-11-22 | 华南理工大学 | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system |
| CN107697281A (en) * | 2017-09-20 | 2018-02-16 | 大连民族大学 | A kind of culvert vertical take-off and landing unmanned aerial vehicle |
| CN108791868A (en) * | 2018-07-31 | 2018-11-13 | 刘浩然 | A kind of new transport unmanned plane of safety and stability |
| CN110254703A (en) * | 2019-06-28 | 2019-09-20 | 福州大学 | A tilting dual-rotor automatic hovering T-type unmanned aerial vehicle system |
| CN110281719A (en) * | 2019-06-28 | 2019-09-27 | 长城汽车股份有限公司 | Flight vehicle and its mode conversion method |
| CN110254703B (en) * | 2019-06-28 | 2023-09-12 | 福州大学 | Tilting double-rotor wing automatic hovering T-shaped unmanned aerial vehicle system |
| CN113911334A (en) * | 2021-11-12 | 2022-01-11 | 北京航空航天大学 | Pneumatic layout of tilting duct type aircraft |
| CN113911334B (en) * | 2021-11-12 | 2024-05-03 | 北京航空航天大学 | Pneumatic layout of tilting duct type aircraft |
| CN114148516A (en) * | 2021-12-06 | 2022-03-08 | 浙江大学 | Distributed tilting duct vertical take-off and landing aircraft and control method thereof |
| CN114148513A (en) * | 2021-12-13 | 2022-03-08 | 浙江云途飞行器技术有限公司 | A UAV take-off and landing platform and a UAV take-off and landing system |
| CN114148513B (en) * | 2021-12-13 | 2024-05-31 | 浙江云途飞行器技术有限公司 | A UAV take-off and landing platform and a UAV take-off and landing system |
| CN114313251A (en) * | 2022-03-03 | 2022-04-12 | 天津斑斓航空科技有限公司 | Combined type aircraft active tilting structure and aircraft |
| CN114313251B (en) * | 2022-03-03 | 2022-06-21 | 天津斑斓航空科技有限公司 | Combined type aircraft active tilting structure and aircraft |
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| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160921 |