CN109305356A - A kind of tilting type vertical take-off and landing drone - Google Patents
A kind of tilting type vertical take-off and landing drone Download PDFInfo
- Publication number
- CN109305356A CN109305356A CN201710752962.6A CN201710752962A CN109305356A CN 109305356 A CN109305356 A CN 109305356A CN 201710752962 A CN201710752962 A CN 201710752962A CN 109305356 A CN109305356 A CN 109305356A
- Authority
- CN
- China
- Prior art keywords
- wing
- fuselage
- engine
- landing
- storehouse
- 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
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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
- 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
- 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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
- B64C27/50—Blades foldable to facilitate stowage of aircraft
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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
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
Abstract
The present invention relates to a kind of unmanned planes, in particular to a kind of tilting type vertical take-off and landing drone, including task storehouse and fuselage, the task storehouse and fuselage integrally connected, flight control unit storehouse is arranged close to the position in task storehouse in the fuselage, fuselage is located at the left and right side setting wing in flight control unit storehouse, wing described in two is symmetrical arranged, and wing is equipped with aileron, the tail portion of the fuselage is equipped with empennage, installation direction rudder on empennage, rudder described in two are symmetrical arranged, and the wing is equipped with fixed-wing close to the position of fuselage.The present invention makes unmanned plane not need to take off, land by any extraneous assist, make unmanned plane in the sky when save kwh loss, reducing engine cannot vert brought resistance, it is folded back by using the paddle engine that vert is folded in the rear screw shaft that verts, resistance brought by conventional non-collapsible propeller can be greatly reduced.
Description
Technical field
The present invention relates to a kind of unmanned planes, are specifically related to a kind of tilting type vertical take-off and landing drone.
Background technique
Existing unmanned plane takeoff and landing is inconvenient, and general using taking off and sliding race landing, (this mode is necessary
It needs certain length and width and flatter ground is as the sliding runway run, and be generally difficult to find such ideal in outfield
Place)；Or fall (whenever this mode all must be with bulky if needing using the parachuting of catapult-launching gear takeoff and landing
Launching cradle, generally conventional unmanned aerial vehicle ejecting frame weight thus at least need the 2-4 talent that can lift dynamic between 30-100KG,
And if launching cradle on mountain, is transported with regard to very inconvenient in flying field)；Or use rocket assist mode takeoff and landing
Parachuting falls that (this mode is also to need a bulky rocket assist steelframe, generally at least needs 2-4 people to carry, and boosting
Rocket is expendable consumed product and higher cost), and existing VTOL fixed-wing unmanned plane be all conventional fixed-wing nobody
On the basis of machine, 4 fixed genemotors are installed additional on wing or foot piece, then its working method is 4 installations
Engine is only responsible for the control taken off and landed, and this 4 engines are not involved in control in aircraft cruising flight, and
This 4 engines are typically all to do pneumatic rectification processing straight up but also not, thus give unmanned plane cruise bring ratio
Biggish air drag, to reduce the cruise time of unmanned plane.
Summary of the invention
The technical problem to be solved by the present invention is to overcome prior art unmanned plane takeoff and landing need by external force, nobody
The defect that the cruise time of machine is short, air drag is big provides a kind of tilting type vertical take-off and landing drone.
In order to solve the above technical problems, the present invention is the following technical schemes are provided: a kind of tilting type vertical take-off and landing drone, packet
Include task storehouse and fuselage, the task storehouse and fuselage integrally connected, position setting flight control of the fuselage close to task storehouse
Equipment compartment, fuselage are located at the left and right side setting wing in flight control unit storehouse, and wing described in two is symmetrical arranged, and machine
The wing is equipped with aileron, and the tail portion of the fuselage is equipped with empennage, installation direction rudder on empennage, and rudder described in two is symmetrically set
It sets, the wing is equipped with fixed-wing close to the position of fuselage, and the both ends of fixed-wing described in left side are equipped with VTOL engine,
First is fixedly mounted outside the shaft of VTOL engine and folds propeller, the first folding propeller is vertical with wing
It is arranged, Horizontal Take-off and Landing engine, fixed peace outside the shaft of Horizontal Take-off and Landing engine are installed in the both ends of fixed-wing described in right side
The second folding propeller is filled, the second folding propeller is to be arranged in parallel with wing, the VTOL engine and level
Landing engine is electrically connected the intracorporal automatic pilot of machine.
It further, include Oil Fuel Tank and battery compartment in the flight control unit storehouse.
Further, the empennage is set as " V " type tail.
Further, the fixed-wing and wing are in a cross-shaped mode arranged in a crossed manner.
Compared with the prior art, the invention has the beneficial effects that: a kind of tilting type vertical take-off and landing drone, structure are closed
Reason, easy to use, the engine that can be verted using 4, unmanned plane can use this 4 hairs when taking off vertically with vertical landing
Then motivation can use the engine of wing front or behind 2 in cruising flight, which reduces 2 engines
Waste, and 4 engines of unmanned plane and its rotating mechanism all have passed through pneumatic rectification processing and 4 engines and turning
It moves to horizontal position and propeller after folding, can greatly reduce resistance brought by 2 engines not arrived, by meter
It calculates these resistances and is substantially negligible and disregard, unmanned plane does not need to take off, land by any extraneous assist, and makes unmanned plane
Save kwh loss when in the sky, reducing engine cannot vert brought resistance, make the hair that verts by using paddle is folded
Motivation is folded back in the rear screw shaft that verts, and can be greatly reduced resistance brought by conventional non-collapsible propeller, be avoided and adopt
With the difficult problem of the landings such as catapult-launching gear, rocket assist and takeoff, realize unmanned plane take off vertically with vertical landing with
And engine can vert in the sky, while avoid VTOL Fixed Wing AirVehicle engine cannot vert, VTOL
The problem of engine does not work when cruising and increases aircraft air drag.
Detailed description of the invention
Fig. 1 is a kind of tilting type vertical take-off and landing drone overlooking structure diagram of the present invention；
Fig. 2 is a kind of tilting type vertical take-off and landing drone VTOL engine structure schematic diagram of the present invention.
Figure label are as follows: 1- task storehouse；2- fuselage；3- flight control unit storehouse；4- wing；5- aileron；6- empennage；The side 7-
To rudder；8- fixed-wing；9- VTOL engine；10- first folds propeller；11- second folds propeller.
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.
Referring to figs. 1 to known to Fig. 2: a kind of tilting type vertical take-off and landing drone, including task storehouse 1 and fuselage 2, the task
Flight control unit storehouse 3 is arranged close to the position in task storehouse 1 in storehouse 1 and 2 integrally connected of fuselage, the fuselage 2, and fuselage 2, which is located at, to fly
Wing 4 is arranged in the left and right side of row control equipment compartment 3, and wing 4 described in two is symmetrical arranged, and wing 4 is equipped with aileron
5, the tail portion of the fuselage 2 is equipped with empennage 6, and installation direction rudder 7 on empennage 6, rudder 7 described in two is symmetrical arranged, described
Wing 4 is equipped with fixed-wing 8 close to the position of fuselage 2, and the both ends of fixed-wing 8 described in left side are equipped with VTOL engine 9, hang down
First is fixedly mounted outside the shaft of straight landing engine 9 and folds propeller 10, the first folding propeller 10 is with wing 4
It is vertically arranged, Horizontal Take-off and Landing engine is installed at the both ends of fixed-wing 8 described in right side, and the shaft outside of Horizontal Take-off and Landing engine is solid
Dingan County fills the second folding propeller 11, and the second folding propeller 11 is to be arranged in parallel with wing 4, and the VTOL is started
Machine 9 and Horizontal Take-off and Landing engine are electrically connected the intracorporal automatic pilot of machine.
It include Oil Fuel Tank and battery compartment in the flight control unit storehouse 3, convenient for unmanned plane operating flight；The empennage 6
It is set as " V " type tail, has the function of tailplane and vertical tail；The fixed-wing 8 and wing 4 be in a cross-shaped mode to intersect and sets
It sets, folds propeller 10 and second convenient for first and fold the installation of propeller 11.
The principle of the present invention and advantage: it is by being located at beside engine that the type unmanned plane, which takes off vertically with vertical landing,
Servo mechanism controls the rotation of engine, so that automatic pilot be cooperated to be taken off vertically to unmanned plane and vertical landing
Control, unmanned plane are controlled servo mechanism by automatic pilot and arrive engine rotation when to be taken off vertically
The floor projection direction perpendicular to aircraft wing can be essentially in the position of balance airplane, the position, at this time by certainly
Dynamic pilot is precisely controlled unmanned plane VTOL engine 9 and the rotational angle and velocity of rotation of Horizontal Take-off and Landing engine come
The balance for controlling unmanned plane, finally makes unmanned plane reach the state that can vertically hover, then controls nothing by automatic pilot
Man-machine to take off vertically to the safe altitude of setting, after unmanned plane reaches safe altitude, automatic pilot controls unmanned plane wing
2, front engine starts slowly to rotate down until horizontality forward, while controlling the engine of wing back 2 and starting slowly
Slowly it is rotated down backward until horizontality, at the same time during this rotation, is started by automatic pilot control
Unmanned plane water when the speed that the speed and aircraft of machine rotation are accelerated forwardly makes engine soon turn to horizontal position
Flat speed accelerates to cruising speed from 0, and the engine of wing back 2 of automatic pilot control at this time is begun to shut off, then spiral
Paddle can be folded back due to the resistance of wind until the close position with fuselage axis horizontal, and 2, wing front engine
Its velocity of rotation is controlled to reach unmanned plane cruising speed by automatic pilot, it is winged to start progress level cruise for unmanned plane at this time
Row, it can start slowly to land back to the height of the setting of takeoff point after unmanned plane cruising flight task knows landing
To ground and engine is automatically closed, and when unmanned plane is when close to takeoff point, automatic pilot controls 4 before and after wing
A engine, which starts slowly to be rotated up, to be known to turn to and can balance the shape body position that unmanned plane vertically hovers, at the same time,
The horizontal velocity of unmanned plane can slowly be reduced to 0 from cruising speed, thereby realize entire fixed-wing unmanned plane and take off vertically
With the process of vertical landing, type UAV flight's visible image capturing head can be applied to patrol on the sea detection etc., offshore applications one
As all implement on naval vessel, and the platform space on naval vessel is extremely limited, and only the type unmanned plane could make on such space
With；Type UAV flight's thermal infrared camera can be applied to forest fire protection or the search that field personnel is missing, this application scenarios
The unmanned machine operation for being not suitable for the mode of baling out down, since field is due to complex conditions such as the gully mountain range woods, so that drop
Fall umbrella landing modes and increase the risk that great aircraft is lost, and the type unmanned plane due to can vertical and landing takeoff,
The scene can be used very advantageously in.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (4)
1. a kind of tilting type vertical take-off and landing drone, including task storehouse (1) and fuselage (2), it is characterised in that: the task storehouse
(1) and flight control unit storehouse (3) are arranged close to the position of task storehouse (1) in fuselage (2) integrally connected, the fuselage (2), fuselage
(2) wing (4) are arranged in the left and right side positioned at flight control unit storehouse (3), and wing (4) described in two is symmetrical arranged, and
Wing (4) is equipped with aileron (5), and the tail portion of the fuselage (2) is equipped with empennage (6), installation direction rudder (7) on empennage (6), and two
The rudder (7) is symmetrical arranged, and the wing (4) is equipped with fixed-wing (8) close to the position of fuselage (2), described in left side
The both ends of fixed-wing (8) are equipped with VTOL engine (9), and first is fixedly mounted outside the shaft of VTOL engine (9)
It folds propeller (10), first folding propeller (10) is to be vertically arranged with wing (4), fixed-wing described in right side (8)
Both ends Horizontal Take-off and Landing engine is installed, be fixedly mounted second outside the shaft of Horizontal Take-off and Landing engine and fold propeller (11),
Described second folds propeller (11) with wing (4) to be arranged in parallel, and the VTOL engine (9) is started with Horizontal Take-off and Landing
Machine is electrically connected the intracorporal automatic pilot of machine.
2. a kind of tilting type vertical take-off and landing drone according to claim 1, which is characterized in that the flight control unit
It include Oil Fuel Tank and battery compartment in storehouse (3).
3. a kind of tilting type vertical take-off and landing drone according to claim 1, which is characterized in that the empennage (6) is set as
" V " type tail.
4. a kind of tilting type vertical take-off and landing drone according to claim 1, which is characterized in that the fixed-wing (8) with
Wing (4) is in a cross-shaped mode arranged in a crossed manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710752962.6A CN109305356A (en) | 2017-08-29 | 2017-08-29 | A kind of tilting type vertical take-off and landing drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710752962.6A CN109305356A (en) | 2017-08-29 | 2017-08-29 | A kind of tilting type vertical take-off and landing drone |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109305356A true CN109305356A (en) | 2019-02-05 |
Family
ID=65207404
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710752962.6A Pending CN109305356A (en) | 2017-08-29 | 2017-08-29 | A kind of tilting type vertical take-off and landing drone |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109305356A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111152919A (en) * | 2020-01-08 | 2020-05-15 | 北京建筑大学 | Control method of unmanned aerial vehicle capable of taking off and landing vertically |
| CN113232854A (en) * | 2021-05-17 | 2021-08-10 | 南京航空航天大学 | Distributed unmanned aerial vehicle platform applicable to ballistic launching and launching method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030094537A1 (en) * | 2000-07-28 | 2003-05-22 | Austen-Brown John Frederick | Personal hoverplane with four tiltmotors |
| CN202728574U (en) * | 2011-10-17 | 2013-02-13 | 田瑜 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106143895A (en) * | 2016-07-13 | 2016-11-23 | 中国人民解放军国防科学技术大学 | Thrust type tilt rotor aircraft |
| CN106184736A (en) * | 2016-08-29 | 2016-12-07 | 天津中翔腾航科技股份有限公司 | The compound aircraft that a kind of fixed-wing forms with many rotors |
| WO2017077144A1 (en) * | 2015-11-04 | 2017-05-11 | Fuvex Sistems, S.L. | Aerodyne with vertical-takeoff-and-landing ability |
-
2017
- 2017-08-29 CN CN201710752962.6A patent/CN109305356A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030094537A1 (en) * | 2000-07-28 | 2003-05-22 | Austen-Brown John Frederick | Personal hoverplane with four tiltmotors |
| CN202728574U (en) * | 2011-10-17 | 2013-02-13 | 田瑜 | Composite aircraft with fixed wing and electric multiple propellers combined and with helicopter function |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| WO2017077144A1 (en) * | 2015-11-04 | 2017-05-11 | Fuvex Sistems, S.L. | Aerodyne with vertical-takeoff-and-landing ability |
| CN106143895A (en) * | 2016-07-13 | 2016-11-23 | 中国人民解放军国防科学技术大学 | Thrust type tilt rotor aircraft |
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106184736A (en) * | 2016-08-29 | 2016-12-07 | 天津中翔腾航科技股份有限公司 | The compound aircraft that a kind of fixed-wing forms with many rotors |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111152919A (en) * | 2020-01-08 | 2020-05-15 | 北京建筑大学 | Control method of unmanned aerial vehicle capable of taking off and landing vertically |
| CN111152919B (en) * | 2020-01-08 | 2021-06-15 | 北京建筑大学 | Control method of unmanned aerial vehicle capable of taking off and landing vertically |
| CN113232854A (en) * | 2021-05-17 | 2021-08-10 | 南京航空航天大学 | Distributed unmanned aerial vehicle platform applicable to ballistic launching and launching method |
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| PB01 | Publication | ||
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190205 |
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