CN110422313A - A kind of aircraft with folded wing - Google Patents
A kind of aircraft with folded wing Download PDFInfo
- Publication number
- CN110422313A CN110422313A CN201910814692.6A CN201910814692A CN110422313A CN 110422313 A CN110422313 A CN 110422313A CN 201910814692 A CN201910814692 A CN 201910814692A CN 110422313 A CN110422313 A CN 110422313A
- Authority
- CN
- China
- Prior art keywords
- main
- machine body
- wing
- aircraft
- lever
- 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
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000004308 accommodation Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
Classifications
-
- 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
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
Abstract
The invention discloses a kind of aircraft with folded wing, including main machine body, and the tail portion of the main machine body is provided with aileron, and is connected with propeller；The two sides of the main machine body are connected separately with wing, the wing has the first hinge joint and the second hinge joint, the wing is hinged by the first hinge joint and main machine body, and the second hinge joint of the wing and the end of main lever are hinged, and the head end and master slider of the main lever are hinged；The master slider is slided along the length direction of main machine body, and drives wing around the first hinged spot wobble by main lever.A kind of aircraft with folded wing of the present invention, main body two sides wing is swingable, can reduce area occupied when aircraft leaves unused.
Description
Technical field
The present invention relates to a kind of aircraft more particularly to a kind of aircraft with folded wing.
Background technique
Aircraft be it is a kind of can endoatmosphere carry out controllable flight aircraft.Any aircraft, which must all generate, to be greater than
The lift of own wt could fly.The type of aircraft is varied, and common mainly has balloon, dirigible, aircraft, gliding
Machine, gyroplane, helicopter etc..The lift of aircraft is according to bernoulli principle: flow velocity is bigger, and pressure is smaller；Flow velocity is smaller, pressure
Qiang Yue great.The shape that the wing of aircraft is made into can just make the flow velocity below its wing lower than top flow velocity, to produce machine
The pressure difference of wing upper and lower, to obtain lift.Therefore, aircraft two sides wing is to provide the main component of lift.But have
When the aircraft of similar aircraft wing shape is parked in bottom surface or storage, need to occupy more space.
Summary of the invention
Goal of the invention: in order to overcome the deficiencies in the prior art, the present invention provides a kind of winged with folded wing
Row device, to reduce aircraft the space occupied when parking.
Technical solution: to achieve the above object, a kind of aircraft with folded wing of the invention, including main machine body,
The tail portion of the main machine body is provided with aileron, and is connected with propeller；The two sides of the main machine body are connected separately with wing, described
Wing has the first hinge joint and the second hinge joint, and the wing is hinged by the first hinge joint and main machine body, the wing
The end of second hinge joint and main lever is hinged, and the head end and master slider of the main lever are hinged；The master slider is along main machine body
Length direction sliding, and by main lever drive wing around the first hinged spot wobble.
Further, further include auxiliary lever, the end of the auxiliary lever be articulated with main lever head end and main lever end it
Between, the head end of the auxiliary lever and secondary sliding block are hinged, and the pair sliding block is slided along the glide direction of master slider.
It further, further include master cylinder, the master cylinder fixing end is connected on the girder being fixed in main machine body, institute
The telescopic end for stating master cylinder is connect with master slider.
Further, main sliding slot is provided on the girder, the master slider is slidably connected in main sliding slot.
It further, further include auxiliary oil cylinder, the auxiliary oil cylinder fixing end is connected on the girder being fixed in main machine body, institute
The telescopic end for stating auxiliary oil cylinder is connect with secondary sliding block.
Further, secondary sliding slot is provided on the girder, the pair sliding block is slidably connected in secondary sliding slot.
Further, the end of the auxiliary lever is arranged at intervals with several secondary connecting plates, the secondary connection along the vertical direction
Plate is provided with secondary connecting hole；The main company of several protrusions is arranged at intervals between the main lever head end and end along the vertical direction
Fishplate bar, the main connecting plate are provided with main connecting hole；Several main connecting plates and several secondary connecting plates are successively overlapped mutually, institute
It states main connecting hole and secondary connecting hole is coaxially opposite.
Further, the slave body of arc, the head end of the slave body and master are provided with above the main machine body front
Fuselage is integrally formed, and the tail end of the slave body extends back, and opposite up and down with main machine body.
Beneficial effects of the present invention are as described below: the wing of a kind of aircraft with folded wing, two sides can be shunk:
The telescopic end of master cylinder extends, while the telescopic end of auxiliary oil cylinder reduces, and main lever drives wing to rotate around the first hinge joint, makes machine
The tail end of the wing completes the storage of wing close to aileron, shortens the occupied area of parked aircraft；Master cylinder shortens, while secondary oil
Cylinder elongation, main lever drive wing to extend the normal use for not influencing aircraft to two sides rotation.
Detailed description of the invention
Accompanying drawing 1 is the structural representation of the present invention；
Attached drawing 2 is the knot that main lever of the present invention, auxiliary lever, master slider, secondary sliding block, master cylinder are connected with auxiliary oil cylinder
Structure schematic diagram；
Attached drawing 3 is the schematic diagram that main lever of the present invention is connect with auxiliary lever.
Specific embodiment
The present invention will be further explained with reference to the accompanying drawing.
A kind of aircraft with folded wing as described in attached drawing 1 to 3, including main machine body 1, the tail of the main machine body 1
Portion is provided with aileron 2, and is connected with propeller 18；The quantity of the aileron 2 has 3 to be connected to the two of 1 tail portion of main machine body
Side and top, three distributions triangular in shape of aileron 2, the propeller 18 are three wing propellers of axis horizontal setting.The master
The two sides of fuselage 1 are connected separately with wing 3, and the head end and main machine body 1 of the wing 3 are hinged, and the tail end of the wing 3 is put backward
Dynamic close aileron 2, completes the storage of wing, to reduce occupied area when parking of aircraft.It should be provided on the wing 3
Landing plate 17.The bottom of the main machine body 1 is provided with crane 19.
Specifically, there are two different hinge joints for one end setting of the wing 3, are the first hinge joint 4 and second respectively
Hinge joint 5.First hinge joint 4 is hinged with main machine body 1, and the end of second hinge joint 5 and main lever 6 is hinged, described
The head end and master slider 7 of main lever 6 are hinged；The master slider 7 is slided along the length direction of main machine body 1, and passes through 6 band of main lever
The motivation wing 3 is swung around the first hinge joint 4.The master slider 7 is connect with the telescopic end of master cylinder 10, the fixation of the master cylinder 10
End is fixedly connected on the girder of main machine body 1.In order to effectively control the motion profile of master slider 7, the shaking of main lever 6 is reduced,
Length direction on girder 1 along main machine body is provided with main sliding slot, slides master slider 7 along main sliding slot.In the head of main lever 6
It is also articulated with auxiliary lever 8 between end and tail end, the other end of the auxiliary lever 8 is hingedly and on secondary sliding block 9.The pair sliding block 9 is same
Sample is slided along the length direction of main machine body 1, and the sliding trace of the sliding trace of master slider and secondary sliding block 9 is same straight line.
The pair sliding block 9 is connected to the telescopic end of auxiliary oil cylinder 11, and the fixing end of the auxiliary oil cylinder 11 is connected on girder.Similarly, it is
The sliding trace for guaranteeing secondary sliding block 9, reduces the shaking of auxiliary lever, secondary sliding slot is again provided on girder, make secondary 9 edge of sliding block
Secondary sliding slot sliding.
The end of the auxiliary lever 8 is arranged at intervals with several secondary connecting plates 12 along the vertical direction, and the pair connecting plate 12 is set
It is equipped with secondary connecting hole 13；The main company of several protrusions is arranged at intervals between 6 head end of main lever and end along the vertical direction
Fishplate bar 14, the main connecting plate 14 are provided with main connecting hole 15；Several main connecting plates 14 and several secondary connecting plates 12 are successively
It is overlapped mutually, the main connecting hole 15 is coaxial opposite with secondary connecting hole 13.
The slave body 16 of arc, the head end and main machine body 1 of the slave body 16 are provided with above 1 front of main machine body
Integrally formed, the tail end of the slave body 16 extends back, and opposite with about 1 main machine body.
The specific accommodation method of wing of the present invention are as follows: when aircraft needs to store, master cylinder elongation, auxiliary oil cylinder
Shorten, rotates main lever along with master slider hinge joint, while wing being driven to rotate at the first hinge joint, make the tail of wing
It holds close to aileron, until completing storage；When aircraft needs take off, master cylinder shorten, auxiliary oil cylinder growth, make main lever along with
The rotation of master slider hinge joint, while wing being driven to rotate around the first hinge joint, make the tail end of wing far from aileron, until completing to stretch
Exhibition.
The above is only a preferred embodiment of the present invention, it should be pointed out that: for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications are also answered
It is considered as protection scope of the present invention.
Claims (8)
1. a kind of aircraft with folded wing, it is characterised in that: including main machine body (1), the tail portion of the main machine body (1) is set
Aileron (2) are equipped with, and are connected with propeller (18)；The two sides of the main machine body (1) are connected separately with wing (3), the wing
(3) there is the first hinge joint (4) and the second hinge joint (5), the wing (3) is cut with scissors by the first hinge joint (4) and main machine body (1)
It connects, the second hinge joint (5) of the wing (3) and the end of main lever (6) are hinged, the head end of the main lever (6) and main cunning
Block (7) is hinged；The master slider (7) along main machine body (1) length direction slide, and by main lever (6) drive wing (3) around
First hinge joint (4) is swung.
2. a kind of aircraft with folded wing according to claim 1, it is characterised in that: it further include auxiliary lever (8),
The end of the auxiliary lever (8) is articulated between main lever (6) head end and main lever (6) end, the head end of the auxiliary lever (8)
Hingedly with secondary sliding block (9), the secondary sliding block (9) is slided along the glide direction of master slider (7).
3. a kind of aircraft with folded wing according to claim 1, it is characterised in that: further include master cylinder
(10), master cylinder (10) fixing end is connected on the girder being fixed on main machine body (1), and the master cylinder (10) is stretched
End is connect with master slider (7).
4. a kind of aircraft with folded wing according to claim 3, it is characterised in that: be provided on the girder
Main sliding slot, the master slider (7) are slidably connected in main sliding slot.
5. a kind of aircraft with folded wing according to claim 2, it is characterised in that: further include auxiliary oil cylinder
(11), auxiliary oil cylinder (11) fixing end is connected on the girder being fixed on main machine body (1), and the auxiliary oil cylinder (11) is stretched
End is connect with secondary sliding block (9).
6. a kind of aircraft with folded wing according to claim 5, it is characterised in that: be provided on the girder
Secondary sliding slot, the pair sliding block (9) are slidably connected in secondary sliding slot.
7. a kind of aircraft with folded wing according to claim 2, it is characterised in that: the auxiliary lever (8)
End is arranged at intervals with several secondary connecting plates (12) along the vertical direction, and the pair connecting plate (12) is provided with secondary connecting hole (13)；
The main lever (6) is arranged at intervals with the main connecting plate (14) of several protrusions along the vertical direction between head end and end, described
Main connecting plate (14) is provided with main connecting hole (15)；Several main connecting plates (14) and several secondary connecting plates (12) are successively mutual
Superposition, the main connecting hole (15) are coaxial opposite with secondary connecting hole (13).
8. a kind of aircraft with folded wing according to claim 1, it is characterised in that: before the main machine body (1)
The slave body (16) of arc is provided with above portion, the head end and main machine body (1) of the slave body (16) are integrally formed, the pair
The tail end of fuselage (16) extends back, and opposite up and down with main machine body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910814692.6A CN110422313A (en) | 2019-08-30 | 2019-08-30 | A kind of aircraft with folded wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910814692.6A CN110422313A (en) | 2019-08-30 | 2019-08-30 | A kind of aircraft with folded wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110422313A true CN110422313A (en) | 2019-11-08 |
Family
ID=68418320
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910814692.6A Pending CN110422313A (en) | 2019-08-30 | 2019-08-30 | A kind of aircraft with folded wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110422313A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111169620A (en) * | 2020-01-14 | 2020-05-19 | 浙江大学 | Telescopic wing mechanism with slotted flap and continuously variable wingspan |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7185847B1 (en) * | 2004-05-13 | 2007-03-06 | Raytheon Company | Winged vehicle with variable-sweep cantilevered wing mounted on a translating wing-support body |
| US20100078526A1 (en) * | 2006-07-03 | 2010-04-01 | Instituto Nacional De Technica Aeroespacial "Esteban Terradas" | Aircraft with a convertible flight system |
| CN101767647A (en) * | 2010-03-02 | 2010-07-07 | 北京航空航天大学 | Self-locking 90-degree full-wing variable sweepback transmission mechanism |
| CN103661919A (en) * | 2013-12-23 | 2014-03-26 | 北京理工大学 | Wing folding mechanism based on flex-wing aircraft |
| CN104176237A (en) * | 2014-07-25 | 2014-12-03 | 哈尔滨工业大学深圳研究生院 | Deformable wing device and airplane applying same |
| CN105923158A (en) * | 2016-04-23 | 2016-09-07 | 董昕武 | Folding wing unmanned plane for municipal landscaping |
| CN106114835A (en) * | 2016-06-29 | 2016-11-16 | 南京航空航天大学 | A kind of compound un-manned aerial helicopter |
| CN108190003A (en) * | 2017-12-28 | 2018-06-22 | 陕西中科博亿电子科技有限公司 | A kind of unmanned plane with buffer gear |
| WO2019125198A1 (en) * | 2017-12-19 | 2019-06-27 | Валерий Туркубеевич ПЧЕНТЛЕШЕВ | Aircraft |
-
2019
- 2019-08-30 CN CN201910814692.6A patent/CN110422313A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7185847B1 (en) * | 2004-05-13 | 2007-03-06 | Raytheon Company | Winged vehicle with variable-sweep cantilevered wing mounted on a translating wing-support body |
| US20100078526A1 (en) * | 2006-07-03 | 2010-04-01 | Instituto Nacional De Technica Aeroespacial "Esteban Terradas" | Aircraft with a convertible flight system |
| CN101767647A (en) * | 2010-03-02 | 2010-07-07 | 北京航空航天大学 | Self-locking 90-degree full-wing variable sweepback transmission mechanism |
| CN103661919A (en) * | 2013-12-23 | 2014-03-26 | 北京理工大学 | Wing folding mechanism based on flex-wing aircraft |
| CN104176237A (en) * | 2014-07-25 | 2014-12-03 | 哈尔滨工业大学深圳研究生院 | Deformable wing device and airplane applying same |
| CN105923158A (en) * | 2016-04-23 | 2016-09-07 | 董昕武 | Folding wing unmanned plane for municipal landscaping |
| CN106114835A (en) * | 2016-06-29 | 2016-11-16 | 南京航空航天大学 | A kind of compound un-manned aerial helicopter |
| WO2019125198A1 (en) * | 2017-12-19 | 2019-06-27 | Валерий Туркубеевич ПЧЕНТЛЕШЕВ | Aircraft |
| CN108190003A (en) * | 2017-12-28 | 2018-06-22 | 陕西中科博亿电子科技有限公司 | A kind of unmanned plane with buffer gear |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111169620A (en) * | 2020-01-14 | 2020-05-19 | 浙江大学 | Telescopic wing mechanism with slotted flap and continuously variable wingspan |
| CN111169620B (en) * | 2020-01-14 | 2020-11-24 | 浙江大学 | Telescopic wing mechanism with slotted flap and continuously variable wingspan |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10696376B2 (en) | Foldable wing and rotocraft and glider using the same | |
| US7946527B2 (en) | Aircraft with fixed, swinging and folding wings | |
| US8651431B1 (en) | Aircraft with movable winglets and method of control | |
| CN106428525B (en) | A kind of variable sweep angle ejection tandem arrangement rotor flying robot | |
| US6899298B2 (en) | Variable area wing aircraft and method | |
| US7131611B2 (en) | Device and method of control of fixed and variable geometry rhomboid wings | |
| US11820503B2 (en) | Aircraft having a folding system | |
| CN106364672A (en) | Ornithopter with elastic wings | |
| CN105059537A (en) | UAV (unmanned aerial vehicle) | |
| CN104443353B (en) | A kind of variable wing plane | |
| CN110422313A (en) | A kind of aircraft with folded wing | |
| US1890012A (en) | Airplane | |
| US1723962A (en) | Folding wing | |
| CN105460202B (en) | A kind of variable geometry unmanned plane | |
| US2961188A (en) | Lift-propulsion device for aircraft | |
| US2349858A (en) | Adjustable airfoil | |
| US3025027A (en) | Vertical airfoil | |
| CN110550203A (en) | Supersonic aircraft | |
| CN210479005U (en) | Aircraft with retractable wings | |
| US2570534A (en) | Aerodynamic trim means | |
| US3811642A (en) | Collapsible propeller for man-powered glider aircraft | |
| DE2421627A1 (en) | Aircraft folding airscrew operating mechanism - has linkage to fold glider auxiliary blades into streamlined recess | |
| CN107284658A (en) | A kind of compound vertical/STOL aircraft | |
| RU128182U1 (en) | SECURITY PLAN (OPTIONS) | |
| DE202011005401U1 (en) | Wing skeleton for ornithopter |
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 |