CN108033013A - A kind of VTOL fixed-wing unmanned plane - Google Patents
A kind of VTOL fixed-wing unmanned plane Download PDFInfo
- Publication number
- CN108033013A CN108033013A CN201711339579.4A CN201711339579A CN108033013A CN 108033013 A CN108033013 A CN 108033013A CN 201711339579 A CN201711339579 A CN 201711339579A CN 108033013 A CN108033013 A CN 108033013A
- Authority
- CN
- China
- Prior art keywords
- rotor
- wing
- unmanned plane
- rotary mechanism
- inclining rotary
- 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
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
-
- 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
- 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
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The present invention relates to a kind of VTOL fixed-wing unmanned plane, fixed-wing with large area, 4 can tilting rotor and 4 rotor inclining rotary mechanisms, during VTOL, inclining rotary mechanism makes 4 rotors produce upward lift, and unmanned plane is lifted before and after wing, when flat winged, inclining rotary mechanism makes rotor produce consistent forward tractive force, and wing is set to produce lift, the lift of wing is consistent when the peace of making a concerted effort of fuselage both sides rotor lift flies during VTOL, so relatively simple light mechanical structure can be used, be conducive to reduction machine weight, increase loading capacity.The present invention is also suitable for all-wing aircraft unmanned plane, canard unmanned plane, more wing unmanned planes.
Description
Technical field：
The invention belongs to vehicle technology field, and in particular to a kind of tilting rotor VTOL fixed-wing unmanned plane, especially
It is the unmanned plane for logistics transportation.
Background technology：
Patent 201610644615.7 discloses a kind of three paddle tilting rotor VTOL fixed-wing unmanned planes, the invention
Two tilting rotors are provided with the leading edge of a wing, one tilting rotor, when VTOL, the two of the leading edge of a wing are set in tail
A tilting rotor is gone to vertically upward, produces main upward lift, the tilting rotor generation part of tail, which ramps up power, makes machine
Body balances, and by verting certain angle around fuselage axis to control revolution of the fuselage around vertical axis.When flat fly, the leading edge of a wing
Two tilting rotors go to horizontal forward, produce forward pulling force and speed, wing is produced lift.
In this way, the invention have both can with VTOL, also can as common fixed-wing unmanned plane high-speed flight or cunning
The advantages of row landing, but the invention also has a disadvantage that：
1st, during VTOL two preceding rotor-bornes machine weigh more than 2/3 load, which is applied by an arm of force
In the leading edge of a wing, considerable additional torque can be produced to wing, to prevent from producing destruction to wing, it is necessary to strengthen wing and fuselage
The intensity of dependency structure, therefore fuselage weight is necessarily increased, reduce lifting capacity.
2nd, rotor can produce aerodynamic drag after putting down when flying, and influence the speed of a ship or plane, increasing energy consumption.
3rd, three rotor VTOL, its controllability, stability, wind resistance be not most preferable.
The content of the invention：
It is an object of the invention to propose a kind of tilting rotor VTOL fixed-wing unmanned plane of new construction, the unmanned plane
Fly flat with VTOL two states, machine stress state is more reasonable, and mechanical structure is simpler, lighter, so as to ensure
More multi-load can be loaded, faster, VTOL is more stable for flat flight speed, can be in the accurate land in narrow plot.
In order to achieve the above object, a kind of tilting rotor VTOL fixed-wing unmanned plane of the present invention includes port wing, the right side
Wing, fuselage, left front rotor, it is right before rotor, left back rotor, it is right after rotor, left front motor, right front motor, left back motor, it is right after
Motor.
The leading edge of port wing has a left front inclining rotary mechanism, trailing edge to have a left back inclining rotary mechanism, passes through left connecting elements
Port wing is connected, the leading edge of starboard wing has inclining rotary mechanism before a right side, and trailing edge has inclining rotary mechanism behind a right side, passes through right connection structure
Part connects starboard wing.
Left front motor, right front motor, left back motor, it is right after motor is separately mounted to left front inclining rotary mechanism, the right side is leaned forward favourable turn
Behind structure, left back inclining rotary mechanism, the right side on inclining rotary mechanism.The left front inclining rotary mechanism of the left and right leading edge of a wing, it is right before inclining rotary mechanism can make institute
Left front motor, the axis of right front motor of dress are turn 90 degrees from inclining upwards to ground parastate, and the left back of left and right trailing edge inclines
Rotation mechanism, it is right after inclining rotary mechanism can make to be filled left back motor, it is right after the axis of motor vert downwards to ground parastate
90 degree, left front rotor, it is right before rotor, left back rotor, it is right after rotor rotation direction and installation direction all match somebody with somebody forward by thrust during flat fly
Put.
The rotor is changed to variable-pitch propeller and pitch-changing mechanism.
The left front rotor, it is right before rotor be changed to variable-pitch propeller and add pitch-changing mechanism, the left back rotor, it is right after rotor change
For foldable formula propeller.
The left back rotor, it is right after rotor be changed to variable-pitch propeller and add pitch-changing mechanism, the left front rotor, it is right before rotor change
For foldable formula propeller.
The form of the aircraft include the fixed-wing unmanned plane with rear portion empennage, canard unmanned plane, all-wing aircraft, multiple wing nobody
Machine.
Compared with the prior art, the present invention has the beneficial effect that：
During VTOL, former and later two rotors lift wing as shoulder pole, its lift make a concerted effort and wing is when putting down winged
Centre of lift be sufficiently close to, need not be that VTOL increases extra mechanical structure substantially, can be before proof strength
Put reduces the weight of fuselage as far as possible, improves lifting capacity.And in VTOL and hovering, quadrotor rotating speed is by flying control
The UAV Attitude signal and ground light that computer is fed back according to the Big Dipper or GPS location signal and axle sensor are controlled
System can realize the accurate land in relatively narrower plot, it can be achieved that the stabilization of position and posture in wind.
Brief description of the drawings：
Attached drawing 1 puts down the side view of winged state for VTOL fixed-wing unmanned plane of the present invention.
Attached drawing 2 puts down the top view of winged state for VTOL fixed-wing unmanned plane of the present invention.
Attached drawing 3 is the side view of VTOL fixed-wing unmanned plane VTOL state of the present invention.
Attached drawing 4 hovers to the top view of flat winged transition state 1 for VTOL fixed-wing unmanned plane of the present invention.
Attached drawing 5 hovers to the top view of flat winged transition state 2 for VTOL fixed-wing unmanned plane of the present invention.
Attached drawing 6 puts down the side view of winged state for flying wing type VTOL fixed-wing unmanned plane of the present invention.
Attached drawing 7 puts down the top view of winged state for flying wing type VTOL fixed-wing unmanned plane of the present invention.
Attached drawing 8 puts down the side view of winged state for the more wing type VTOL fixed-wing unmanned planes of the present invention.
Attached drawing 9 is the side view of the more wing type VTOL fixed-wing unmanned plane VTOL states of the present invention.
Figure label：Revolved before 1 port wing, 2 starboard wings, 3 fuselages, 4 left front rotors, 5 right sides behind rotor, 6 left back rotors, 7 right sides
Inclining rotary mechanism, 14 before motor, 12 left front inclining rotary mechanisms, 13 right sides behind the wing, 8 left front motors, 9 right front motors, 10 left back motors, 11 right sides
Inclining rotary mechanism, 18 left connecting elements, 19 right connecting elements, 20 variable-pitch propellers, 21 displacement machines behind left back inclining rotary mechanism, 15 right sides
Structure, 22 foldable formula propellers.
Embodiment：
With reference to embodiment and with reference to attached drawing, the invention will be further described.
Join Fig. 1-Fig. 2, a kind of tilting rotor VTOL fixed-wing unmanned plane of the invention includes port wing 1, starboard wing
2nd, fuselage 3, left front rotor 4, it is right before rotor 5, left back rotor 6, it is right after rotor 7, left front motor 8, right front motor 9, left back motor
10th, motor 11 behind the right side, the leading edge of port wing have a left front inclining rotary mechanism 12, trailing edge to have a left back inclining rotary mechanism 14, pass through
Left connecting elements 18 connects port wing 1, and the leading edge of starboard wing has inclining rotary mechanism 13 before a right side, and trailing edge has a right hypsokinesis favourable turn
Structure 15, starboard wing 2 is connected by right connecting elements 19,
Motor 11 is separately mounted to left front inclining rotary mechanism 12, the right side behind left front motor 8, right front motor 9, left back motor 10, the right side
Behind preceding inclining rotary mechanism 13, left back inclining rotary mechanism 14, the right side on inclining rotary mechanism 15.The left front inclining rotary mechanism 12 of the left and right leading edge of a wing, the right side
Left front motor 8 that preceding inclining rotary mechanism 13 can make to be filled, the axis of right front motor 9 are turn 90 degrees from inclining upwards to ground parastate,
The left back inclining rotary mechanism 14 of left and right trailing edge, it is right after inclining rotary mechanism 15 can make to be filled left back motor 10, it is right after motor 11
Axis is turn 90 degrees from dipping down to ground parastate, left front rotor 4, it is right before rotor 5, left back rotor 6, it is right after rotor 7 rotation
To and installation direction all configured forward by thrust during flat fly.Front and rear inclining rotary mechanism and wing except being made mechanics by left and right connecting elements
Beyond connection in structure, rectification is also acted as, reduces the effect of air drag.
Turn 90 degrees when the axis of the right front motor 9 of left front motor 8 inclines upwards, left back motor 10, it is right after motor 11 axis to
Have a down dip when turning 90 degrees, two preceding rotors produce upward pulling force, and rotor produces upward thrust after two, when the conjunction of four rotors
When power is more than machine weight, it is achieved that and takes off.When the axis of four motors is synchronously tilted to parallel to ground, rotor produces horizontal
Pulling force, and wing to front haulage, is produced by left connecting elements 18, right connecting elements 19 by lift.The present invention is hovered from vertical
Fly or all very steady from the flat process vertically hovered flown to flat.Join Fig. 3, Fig. 4, Fig. 5, since vertical hovering, with four
Progressively increasing of a rotor to horizontal direction inclination angle, quadrotor vertical stress component are gradually reduced, and horizontal component is gradually increased, and horizontal
Speed accordingly increases, and airfoil lift is also gradually increased, and coordinates the adjustment of rotor rotating speed, finally reaches wing-borne whole machine weight,
Rotor only produces the pure flat winged state of horizontal pull.
Fig. 6, Fig. 7 show the flying wing type unmanned plane using this patent, and two preceding rotors use variable-pitch propeller slurry and displacement instead
Mechanism, to improve level speed.Because being adapted to the rotor of VTOL, when putting down winged for high speed, efficiency is than relatively low, so such as
Pitch is become larger when flat fly, is conducive to improve level speed.
When unmanned plane is flat winged at a high speed, required horizontal drag force only has the part of VTOL lift, so Fig. 6, Fig. 7
Two motors of shown flying wing type unmanned plane trailing edge when flat fly can be with no power, but is to reduce air drag, the two motors
On rotor should be changed to foldable formula propeller.
In addition to the fixed-wing unmanned plane with rear portion empennage, the present invention is also adapted to canard unmanned plane, flying wing type unmanned plane,
More wing unmanned planes.
Flying wing type unmanned plane shown in Fig. 6, Fig. 7 has the wing of larger area, and flat winged lifting capacity is stronger, and reduces machine
The weight of tail, empennage, is more suitable for the purposes of shipping load-carrying.
More wing unmanned planes shown in Fig. 8 Fig. 9 use the two-shipper wing, and wing length can reduce, suitable for the landing field of relatively narrower
Ground.
Claims (5)
1. a kind of VTOL fixed-wing unmanned plane includes port wing (1), starboard wing (2), fuselage (3), left front rotor (4), the right side
Preceding rotor (5), left back rotor (6), it is right after rotor (7), left front motor (8), right front motor (9), left back motor (10), it is right after electricity
Machine (11), it is characterised in that：The leading edge of port wing has left front inclining rotary mechanism (12), a trailing edge to have a left back inclining rotary mechanism
(14), port wing (1) is connected by left connecting elements (18), the leading edge of starboard wing has inclining rotary mechanism (13) before a right side, trailing edge
There is inclining rotary mechanism (15) behind a right side, pass through right connecting elements (19) and connect starboard wing (2), left front motor (8), right front motor
(9), left back motor (10), it is right after motor (11) be separately mounted to left front inclining rotary mechanism (12), it is right before inclining rotary mechanism (13), left back
Behind inclining rotary mechanism (14), the right side on inclining rotary mechanism (15), inclining rotary mechanism (13) can make a filled left side before left front inclining rotary mechanism (12), the right side
Front motor (8), the axis of right front motor (9) are turn 90 degrees from inclining upwards to ground parastate, behind left back inclining rotary mechanism (14), the right side
Left back motor (10) that inclining rotary mechanism (15) can make to be filled, it is right after the axis of motor (11) vert downwards to ground parastate
90 degree, left front rotor (4), it is right before rotor (5), left back rotor (6), it is right after rotor (7) rotation direction and installation direction all fly by flat
When thrust configure forward.
2. VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：The rotor is changed to displacement spiral shell
Revolve paddle (20) and pitch-changing mechanism (21).
3. tilting rotor VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：The left front rotor
(4), rotor (5) is changed to variable-pitch propeller (20) plus pitch-changing mechanism (21) before the right side, and rotor (7) changes behind the left back rotor (6), the right side
For foldable formula propeller (22).
4. tilting rotor VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：The left back rotor
(6), rotor (7) is changed to variable-pitch propeller (20) plus pitch-changing mechanism (21) behind the right side, and rotor (5) changes before the left front rotor (4), the right side
For foldable formula propeller (22).
5. VTOL fixed-wing unmanned plane according to claim 1, it is characterised in that：The form of the unmanned plane includes
All-wing aircraft, the fixed-wing unmanned plane with rear portion empennage, canard unmanned plane, multiple wing unmanned plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711339579.4A CN108033013A (en) | 2017-12-14 | 2017-12-14 | A kind of VTOL fixed-wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711339579.4A CN108033013A (en) | 2017-12-14 | 2017-12-14 | A kind of VTOL fixed-wing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108033013A true CN108033013A (en) | 2018-05-15 |
Family
ID=62103349
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711339579.4A Pending CN108033013A (en) | 2017-12-14 | 2017-12-14 | A kind of VTOL fixed-wing unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108033013A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131867A (en) * | 2018-07-18 | 2019-01-04 | 深圳筋斗云智能科技有限公司 | Aircraft |
| CN110116806A (en) * | 2019-04-28 | 2019-08-13 | 南京航空航天大学 | A kind of device docked for fixed-wing unmanned plane with rotor flat pad |
| CN110341951A (en) * | 2019-07-22 | 2019-10-18 | 中北大学 | A kind of unmanned vehicle of folding wing and tilting rotor |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738496A (en) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
| CN204507252U (en) * | 2015-02-10 | 2015-07-29 | 上海美利达电子科技有限公司 | A kind of collapsible four axle multi-rotor aerocrafts |
| CN204688415U (en) * | 2015-05-22 | 2015-10-07 | 上海俏动智能化科技有限公司 | A kind of collapsible screw propeller for unmanned plane |
| CN106516147A (en) * | 2016-12-01 | 2017-03-22 | 南京航空航天大学 | Mobile launch type autogyro and control method thereof |
| CN107284656A (en) * | 2017-07-12 | 2017-10-24 | 重庆国飞通用航空设备制造有限公司 | Coaxial double-oar rotor mechanism in the same direction and its aircraft |
| CN107310715A (en) * | 2017-07-05 | 2017-11-03 | 上海未来伙伴机器人有限公司 | A kind of propeller of variable pitch and flying robot |
| CN107352024A (en) * | 2017-07-12 | 2017-11-17 | 重庆国飞通用航空设备制造有限公司 | The reverse rotor mechanism of coaxial double-oar and its aircraft |
-
2017
- 2017-12-14 CN CN201711339579.4A patent/CN108033013A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103738496A (en) * | 2013-12-24 | 2014-04-23 | 西安交通大学 | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof |
| CN204507252U (en) * | 2015-02-10 | 2015-07-29 | 上海美利达电子科技有限公司 | A kind of collapsible four axle multi-rotor aerocrafts |
| CN204688415U (en) * | 2015-05-22 | 2015-10-07 | 上海俏动智能化科技有限公司 | A kind of collapsible screw propeller for unmanned plane |
| CN106516147A (en) * | 2016-12-01 | 2017-03-22 | 南京航空航天大学 | Mobile launch type autogyro and control method thereof |
| CN107310715A (en) * | 2017-07-05 | 2017-11-03 | 上海未来伙伴机器人有限公司 | A kind of propeller of variable pitch and flying robot |
| CN107284656A (en) * | 2017-07-12 | 2017-10-24 | 重庆国飞通用航空设备制造有限公司 | Coaxial double-oar rotor mechanism in the same direction and its aircraft |
| CN107352024A (en) * | 2017-07-12 | 2017-11-17 | 重庆国飞通用航空设备制造有限公司 | The reverse rotor mechanism of coaxial double-oar and its aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109131867A (en) * | 2018-07-18 | 2019-01-04 | 深圳筋斗云智能科技有限公司 | Aircraft |
| CN109131867B (en) * | 2018-07-18 | 2023-10-27 | 深圳筋斗云智能科技有限公司 | Aircraft with a plurality of aircraft body |
| CN110116806A (en) * | 2019-04-28 | 2019-08-13 | 南京航空航天大学 | A kind of device docked for fixed-wing unmanned plane with rotor flat pad |
| CN110116806B (en) * | 2019-04-28 | 2022-05-03 | 南京航空航天大学 | Device for butt joint of fixed-wing unmanned aerial vehicle and rotor wing launching platform |
| CN110341951A (en) * | 2019-07-22 | 2019-10-18 | 中北大学 | A kind of unmanned vehicle of folding wing and tilting rotor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP6949869B2 (en) | Tail sitter aircraft rotor assembly | |
| CN106828915B (en) | Control method of high-speed aircraft with tilting propeller capable of vertically taking off and landing | |
| CN101875399B (en) | Tilt rotor aircraft adopting parallel coaxial dual rotors | |
| CN110267876A (en) | More rotor lift body aircrafts with tilting rotor | |
| CN108860582A (en) | More rotor lifting body aircraft with tail portion propeller | |
| CN106741820A (en) | A kind of VTOL fixed-wing unmanned vehicle | |
| CN106043696A (en) | Flying system for unmanned aerial vehicle | |
| CN107571994B (en) | Aircraft | |
| CN106218887A (en) | A kind of vertically taking off and landing flyer of distributed-power device layout | |
| CN102001446B (en) | Structure of vertical take-off and landing rotor aircraft | |
| CN103158856B (en) | Light airscrew flying wing aircraft capable of taking off and landing in short distance | |
| CN206984354U (en) | A kind of aircraft | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN105460215A (en) | Fixed-wing air vehicle achieving vertical or short-distance take-off and landing | |
| CN108033013A (en) | A kind of VTOL fixed-wing unmanned plane | |
| CN107352029A (en) | A kind of electronic multiaxis tilting rotor wing unmanned aerial vehicle system | |
| CN112896499A (en) | Vertical take-off and landing aircraft with combined layout of tilting duct and fixed propeller | |
| CN108177777A (en) | A kind of aircraft based on tip vortex lift-rising | |
| CN205469821U (en) | Perpendicular or short take off and landing fixed wing aircraft | |
| CN110116802A (en) | A kind of big loading small-sized unmanned aircraft of high universalizable | |
| CN218617171U (en) | Multi-rotor aircraft | |
| CN209176908U (en) | A kind of rotor fixed-wing unmanned plane of composite drive | |
| US11919633B2 (en) | Convertiplane | |
| US20220388647A1 (en) | Winged tiltrotor aircraft | |
| CN211281472U (en) | Duct tail sitting posture VTOL unmanned aerial vehicle |
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: 20180515 |
|
| WD01 | Invention patent application deemed withdrawn after publication |