CN112455650A - Double-wing flying device - Google Patents
Double-wing flying device Download PDFInfo
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- CN112455650A CN112455650A CN202011346831.6A CN202011346831A CN112455650A CN 112455650 A CN112455650 A CN 112455650A CN 202011346831 A CN202011346831 A CN 202011346831A CN 112455650 A CN112455650 A CN 112455650A
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- wing
- translational
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- sliding sleeve
- driving shaft
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- 230000005540 biological transmission Effects 0.000 claims abstract description 4
- 230000007246 mechanism Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention relates to the technical field of aircrafts, in particular to a double-wing flying device; the device comprises translational wings, a driving device and a carrier, wherein the carrier is provided with a bracket, the bracket is provided with two translational wings capable of rotating on the bracket, and the two translational wings are arranged in a pair at intervals from top to bottom; the driving device is fixedly arranged on the carrier and is respectively in transmission connection with the two translational wings so as to enable the two translational wings to respectively reciprocate up and down along the support; the structure of the invention is reasonable, the driving device drives the two translational wings on the bracket to reciprocate up and down, and when the translational wings ascend, air generates pressure difference between the front curved surface and the rear smooth surface of the spoiler wing surface so as to drive the translational wings to rotate in a single direction; when the translational wing descends, a vertical upward acting force is generated between the fanning wing surface and air; the translational wing converts the up-and-down reciprocating motion of the driving device into self rotary motion, and then generates lift force through the rotary motion to enable the carrier to obtain the lift force to achieve the flying purpose.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a double-wing flying device.
Background
The lift device of an aircraft is an aerodynamic-based mechanism, and can be divided into a fixed wing and a rotor wing according to the structure, and the fixed wing aircraft generally has a fuselage and symmetrically arranged fixed wings, and is powered by a propeller to obtain larger flight speed and maneuverability. The flying principle of the airplane is that relative speed exists between the fixed wing and air, and the air and all surfaces of the fixed wing interact to generate lift force so as to enable the airplane to obtain flying capability. Fixed wing aircraft have the disadvantages of being unable to hover in the air, requiring taxiing takeoff or landing on a runway and support for airport facility construction. A rotary-wing aircraft such as helicopter features that it can take off without runway and hover in sky, and its power system is composed of engine and rotary wings. The defects of the method are that the cruising speed is low, the load capacity is not high, the efficiency is low, but the dependence on ground facilities is little.
The autorotation gyroplane is an aircraft combining two modes of a fixed wing and a rotor wing, and the main structure of the autorotation gyroplane comprises the rotor wing, a wheel type undercarriage and a propeller, wherein the propeller drives the autorotation gyroplane to slide on a runway, air and rotor blades interact in the sliding process, the air can push the rotor blades to rotate, the rotor blades rotate and generate acting force in the relative sliding direction, and when the rotating speed of the rotor blades is high enough, the acting force makes the aircraft lift off to realize flight. Its advantages are low requirement to take-off runway, long running distance, and limited application range.
Accordingly, the prior art is yet to be improved and developed.
Disclosure of Invention
The invention aims to provide a double-wing flying device which is reasonable in structure, capable of realizing multi-layer layout, good in safety and capable of vertically lifting and hovering, aiming at the defects and shortcomings of the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention relates to a double-wing flying device which comprises translational wings, a driving device and a carrier, wherein the carrier is provided with a bracket, the bracket is provided with two translational wings capable of rotating on the bracket, and the two translational wings are arranged in a pairing manner at intervals from top to bottom; the driving device is fixedly arranged on the carrier and is respectively in transmission connection with the two translational wings, so that the two translational wings respectively reciprocate up and down along the support.
According to the above solution, the driving means comprises a first driving shaft and a second driving shaft, which are respectively mounted on the support through sliding bearings; and the rotating center of the translational wings is provided with a rotating bearing, one translational wing is arranged at the upper end of the first driving shaft through the rotating bearing, the rotating bearing on the other translational wing is arranged on the first driving shaft through a sliding bearing, and the upper end of the second driving shaft is fixedly connected with the sliding bearing.
According to the scheme, the driving device further comprises a first sliding sleeve and a second sliding sleeve, the first sliding sleeve is sleeved on the support, a sliding bearing is arranged between the first sliding sleeve and the second sliding sleeve, the second sliding sleeve is sleeved on the first sliding sleeve, and a sliding bearing is arranged between the first sliding sleeve and the second sliding sleeve; the rotating bearing of one of the translation wings is fixedly connected with the upper end of the first sliding sleeve, and the first driving shaft is fixedly connected with the lower end of the first sliding sleeve; and the rotating bearing of the other translational wing is fixedly connected with the upper end of the second sliding sleeve, and the second driving shaft is fixedly connected with the lower end of the second sliding sleeve.
According to the scheme, the driving device is provided with two output shafts, and the two output shafts are respectively and rotatably connected to the first driving shaft and the second driving shaft.
According to the scheme, the translational wing comprises two wings and a rotary bearing, the two wings are oppositely arranged on two sides of the rotary bearing, and the wing roots of the two wings are respectively and fixedly connected with the rotary bearing; the upper side plane of the wing is a turbulent wing surface, and the lower side plane of the wing is a fanning wing surface; the vortex wing surface is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the vortex wing surface is upwards raised relative to a rotating plane of the translational wing, and the vortex wing surface and the fan-moving wing surface are in an asymmetric structure in the longitudinal projection plane.
According to the scheme, the front side edges of the turbulence wing surface and the fanning wing surface are mutually closed to form a front wing edge, and the rear side edges of the turbulence wing surface and the fanning wing surface are mutually closed to form a rear wing tail; and the span longitude line H where the maximum arch height point of the front curved surface of the spoiler airfoil is positioned is close to the front wing edge.
The invention has the beneficial effects that: the structure of the invention is reasonable, the driving device drives the two translational wings on the bracket to reciprocate up and down, and when the translational wings ascend, air generates pressure difference between the front curved surface and the rear smooth surface of the spoiler wing surface so as to drive the translational wings to rotate in a single direction; when the translational wing descends, a vertical upward acting force is generated between the fanning wing surface and air; the translational wing converts the up-and-down reciprocating motion of the driving device into self rotary motion, and then generates lift force through the rotary motion to enable the carrier to obtain the lift force to achieve the flying purpose.
Drawings
FIG. 1 is a schematic structural view of example 1 of the present invention;
FIG. 2 is a schematic structural view of embodiment 2 of the present invention;
FIG. 3 is a schematic view of a translational wing mounting structure according to embodiment 1 of the present invention;
fig. 4 is a structural diagram of a translational wing section of the invention.
In the figure:
1. a translational wing; 2. a drive device; 3. a carrier; 10. a wing; 11. a spoiler airfoil; 12. a fanning airfoil; 13. a leading fin edge; 14. the rear wing tail; 15. a rotating bearing; 21. a first drive shaft; 22. a second drive shaft; 23. a sliding bearing; 24. a first sliding sleeve; 25. a second sliding sleeve; 26. an output shaft; 31. and (4) a bracket.
Detailed Description
The technical solution of the present invention is described below with reference to the accompanying drawings and examples.
Example 1
As shown in fig. 1, 3 and 4, the double-wing flying device of the invention comprises a translational wing 1, a driving device 2 and a carrier 3, wherein the carrier 3 is provided with a bracket 31, the bracket 31 is provided with two translational wings 1 capable of rotating thereon, and the two translational wings 1 are arranged in a pair at intervals from top to bottom; the driving device 2 is fixedly arranged on the carrier 3, and the driving device 2 is respectively connected with the two translational wings 1 in a transmission manner, so that the two translational wings 1 respectively reciprocate up and down along the bracket 31. The carrier 3 is a main body of the flying device and used for carrying people and objects, the driving device 2 drives the two translational wings 1 to reciprocate up and down, the translational wings 1 generate rotation action under the action of air in an ascending stroke, and the two translational wings 1 rotate to generate lift force, so that the purpose of flying the carrier 3 is achieved.
The translational wing 1 comprises two wings 10 and a rotary bearing 15, the two wings 10 are oppositely arranged on two sides of the rotary bearing 15, and the wing roots of the two wings 10 are respectively fixedly connected with the rotary bearing 15; the upper side plane of the wing 10 is a turbulent wing surface 11, and the lower side plane of the wing 10 is a fanning wing surface 12; the spoiler airfoil 11 is formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the spoiler airfoil 11 protrudes upwards relative to the rotating plane of the translational wing 1, and the spoiler airfoil 11 and the fanning airfoil 12 are in an asymmetric structure in the longitudinal projection plane. The driving mechanism 2 drives the translational wing 1 to reciprocate up and down, when the translational wing 1 ascends, the turbulent wing surfaces 11 of the wings 10 interact with air above, the air generates pressure difference between the front side curved surface and the rear smooth surface of the turbulent wing surfaces 11, the pressure difference pushes the wings 10 to move forward, and the two wings 10 act in the same direction, so that the translational wing 1 rotates unidirectionally by taking the rotating bearing 15 as the center; when the translational wing 1 descends, the fanning wing surface 12 of the wing 10 interacts with the air below, the rotational motion of the translational wing 1 is combined with the downward motion to enable the fanning wing surface 12 to form a vector attack angle C, and the vector attack angle C enables the fanning wing surface 12 and the air to generate a vertical upward acting force; the translational wing 1 converts the up-and-down reciprocating motion of the driving mechanism 2 into self rotary motion, and then generates lift force through the rotary motion to enable the flying device to obtain the lift force to achieve the flying purpose.
The front side edges of the spoiler airfoil 11 and the fanning airfoil 12 are mutually closed to form a front wing edge 13, and the rear side edges of the spoiler airfoil 11 and the fanning airfoil 12 are mutually closed to form a rear wing tail 14; the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil 11 is located is close to the front wing edge 13. The front wing edge 13 is a curved surface so as to respectively continue the front side edges of the spoiler wing surface 11 and the fanning wing surface 12, the existence of the front wing edge 13 can improve the structural strength of the wing type translational wing 1, the front wing edge 13 is positioned at the front side of the rotational direction of the translational wing 1, and the curved front wing edge 13 can reduce the air resistance received by the translational wing 1 during rotation and improve the power conversion efficiency of the driving mechanism. As shown in fig. 2, the X direction in the figure is the chord length direction of the airfoil structure, and the Z direction in the figure is the spanwise direction of the airfoil structure. The contour line of the cross section of the turbulent wing surface 11 along the X direction is in a curve shape relative to the rotating plane of the translational wing 1, the highest point of the contour line forms a span warp H along the Z direction, and the span warp H is positioned on the front curved surface of the turbulent wing surface 11 and is close to the front wing edge 13, so that the turbulent wing surface 11 is in a front-back asymmetric structure. When the translational wing 1 is lifted, the spoiler wing surface 11 interacts with air above, pressure difference is generated between the front side and the rear side of the span longitude line H of the spoiler wing surface 11 by the air, the wing wings 10 are pushed to move forwards by the pressure difference, and the two wing wings 10 act in the same direction, so that the translational wing 1 rotates in a single direction by taking the rotating bearing 15 as the center.
The driving device 2 comprises a first driving shaft 21 and a second driving shaft 22, and the first driving shaft 21 and the second driving shaft 22 are respectively installed on a bracket 31 through sliding bearings 23; the rotating bearings 15 are arranged on the rotating centers of the translational wings 1, one translational wing 1 is installed at the upper end of the first driving shaft 21 through the rotating bearing 15, the rotating bearing 15 on the other translational wing 1 is installed on the first driving shaft 21 through the sliding bearing 23, and the upper end of the second driving shaft 22 is fixedly connected with the sliding bearing 23. The driving device 2 outputs power to drive the first driving shaft 21 and the second driving shaft 22 to reciprocate up and down on the support 31, the first driving shaft 21 drives one of the translational wings 1 to rotate thereon through the rotating bearing 15 to generate lift force, the second driving shaft 22 drives the other translational wing 1 to move up and down along the support 31 through the sliding bearing 23, so that the translational wings rotate around the support 31 through the rotating bearing 15 to generate lift force, and the two translational wings 1 jointly output lift power to enable the carrier 3 to obtain flight capability. The flight mode of the translational wing 1 is similar to that of a helicopter without sliding, taking off and landing, so that the translational wing has the capability of suspending and staying empty. Because the two translational wings 1 are respectively arranged on the bracket 31 through the rotating bearing 15, when the driving device 2 loses power, the two translational wings 1 can still continue to rotate, the attack angle C of the fanning wing surface 12 is adjusted to be less than or equal to 0 degree, the translational wings 1 can continue to rotate under the action of the dropping inertia force, the actual vector attack angle of the fanning wing surface 12 is more than or equal to 0 degree to maintain a certain lift force, and the lift force can delay the descending speed of the carrier 1 so as to ensure the carrier to land safely, thereby effectively improving the safety of the flying device.
The driving device 2 is provided with two output shafts 26, and the two output shafts 26 are respectively and rotatably connected to the first driving shaft 21 and the second driving shaft 22. The driving device 2 comprises a motor, a fuel engine and the like, the driving device 2 outputs continuous power to drive the two output shafts 26 to do work, and the two output shafts 26 can drive the first driving shaft 21 and the second driving shaft 22 in a time-sharing manner so as to drive the two translational wings 1. The translational wing 1 rotates by adopting the up-and-down reciprocating motion to generate lift force, and the spoiler wing surface 11 and the fanning wing surface 12 of the wing 10 do work in the up-and-down stroke respectively, so that a lift force output gap exists in the operation of the single translational wing 1, the reciprocating motion of the single translational wing 1 can generate larger vibration to influence the stability of the flying device, and the structures of the two translational wings 1 which move up and down oppositely can well offset the vibration and make up the lift force output gap, thereby improving the flying stability.
Example 2
As shown in fig. 2, the only difference between this embodiment and embodiment 1 is that the driving device 2 further includes a first sliding sleeve 24 and a second sliding sleeve 25, the first sliding sleeve 24 is sleeved on the bracket 31 and the sliding bearing 23 is arranged between the two, the second sliding sleeve 25 is sleeved on the first sliding sleeve 24 and the sliding bearing 23 is arranged between the two; the rotating bearing 15 of one of the translational wings 1 is fixedly connected with the upper end of a first sliding sleeve 24, and the first driving shaft 21 is fixedly connected with the lower end of the first sliding sleeve 24; the rotating bearing 15 of the other translational wing 1 is fixedly connected with the upper end of the second sliding sleeve 25, and the second driving shaft 22 is fixedly connected with the lower end of the second sliding sleeve 25. The support 31 is used as a central support mechanism, the first sliding sleeve 24 and the second sliding sleeve 25 are sequentially sleeved and arranged concentrically with the support 31, and further, time-sharing up-and-down reciprocating motion is realized under the driving of the driving device 2, and the two translational wings 1 are driven to relatively open and close so as to realize the flying purpose.
The above description is only a preferred embodiment of the present invention, and all equivalent changes or modifications of the structure, characteristics and principles described in the present invention are included in the scope of the present invention.
Claims (6)
1. A double-wing flying device comprises a translational wing (1), a driving device (2) and a carrier (3), and is characterized in that: a support (31) is arranged on the carrier (3), two translational wings (1) capable of rotating on the support (31) are arranged on the support (31), and the two translational wings (1) are arranged in a paired manner at intervals up and down; the driving device (2) is fixedly arranged on the carrier (3), and the driving device (2) is respectively in transmission connection with the two translational wings (1) so as to enable the two translational wings (1) to respectively reciprocate up and down along the support (31).
2. The twin wing flying device of claim 1, wherein: the driving device (2) comprises a first driving shaft (21) and a second driving shaft (22), and the first driving shaft (21) and the second driving shaft (22) are respectively installed on a bracket (31) through sliding bearings (23); the rotary wing is characterized in that a rotary bearing (15) is arranged on the rotary center of the translational wing (1), one translational wing (1) is installed at the upper end of the first driving shaft (21) through the rotary bearing (15), the rotary bearing (15) on the other translational wing (1) is installed on the first driving shaft (21) through a sliding bearing (23), and the upper end of the second driving shaft (22) is fixedly connected with the sliding bearing (23).
3. The twin wing flying device of claim 2, wherein: the driving device (2) further comprises a first sliding sleeve (24) and a second sliding sleeve (25), the first sliding sleeve (24) is sleeved on the support (31), a sliding bearing (23) is arranged between the first sliding sleeve and the second sliding sleeve, the second sliding sleeve (25) is sleeved on the first sliding sleeve (24), and the sliding bearing (23) is arranged between the first sliding sleeve and the second sliding sleeve; the rotating bearing (15) of one of the translation wings (1) is fixedly connected with the upper end of the first sliding sleeve (24), and the first driving shaft (21) is fixedly connected with the lower end of the first sliding sleeve (24); and the rotating bearing (15) of the other translation wing (1) is fixedly connected with the upper end of a second sliding sleeve (25), and a second driving shaft (22) is fixedly connected with the lower end of the second sliding sleeve (25).
4. The twin wing flying device of claim 2 or 3, wherein: two output shafts (26) are arranged on the driving device (2), and the two output shafts (26) are respectively and rotatably connected to the first driving shaft (21) and the second driving shaft (22).
5. The twin wing aircraft device of any one of claims 1 to 3 wherein: the translational wing (1) comprises two wing fins (10) and a rotary bearing (15), the two wing fins (10) are oppositely arranged on two sides of the rotary bearing (15), and the wing roots of the two wing fins (10) are respectively fixedly connected with the rotary bearing (15); the upper side plane of the wing (10) is a turbulent wing surface (11), and the lower side plane of the wing (10) is a fanning wing surface (12); the vortex wing surfaces (11) are formed by connecting a front curved surface and a rear smooth surface, the front curved surface of the vortex wing surfaces (11) is upwards raised relative to a rotating plane of the translational wing (1), and the vortex wing surfaces (11) and the fanning wing surfaces (12) are in an asymmetric structure in the longitudinal projection plane.
6. The twin wing flying device of claim 1, wherein: the front side edges of the turbulent flow wing surfaces (11) and the fanning wing surfaces (12) are mutually closed to form front wing edges (13), and the rear side edges of the turbulent flow wing surfaces (11) and the fanning wing surfaces (12) are mutually closed to form rear wing tails (14); the span meridian H where the maximum arch height point of the front curved surface of the spoiler airfoil (11) is located is close to the front wing edge (13).
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346831.6A CN112455650A (en) | 2020-11-26 | 2020-11-26 | Double-wing flying device |
| PCT/CN2020/133750 WO2022110271A1 (en) | 2020-11-26 | 2020-12-04 | Double-wing flying device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011346831.6A CN112455650A (en) | 2020-11-26 | 2020-11-26 | Double-wing flying device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112455650A true CN112455650A (en) | 2021-03-09 |
Family
ID=74809500
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011346831.6A Withdrawn CN112455650A (en) | 2020-11-26 | 2020-11-26 | Double-wing flying device |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN112455650A (en) |
| WO (1) | WO2022110271A1 (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101492093A (en) * | 2009-03-12 | 2009-07-29 | 北京理工大学 | Flapping rotor wing design method and microminiature flapping rotor wing designed according to the method |
| CN108995804A (en) * | 2018-08-01 | 2018-12-14 | 北京理工大学 | The bionic Aircraft for flutterring rotor and the conversion of flapping flight mode is realized based on the deformation wing |
| CN110104175A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | A kind of coaxial reversed pair is flutterred rotor mechanism |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB378641A (en) * | 1930-08-21 | 1932-08-18 | Graf Joseph De Korwin | Improvements in or relating to flying machines |
| GB404257A (en) * | 1932-04-04 | 1934-01-11 | Ernst Wilhelm Gretscher | Helicopter |
| US8784057B2 (en) * | 2011-02-28 | 2014-07-22 | The Boeing Company | Disc rotor retraction system |
| US9172287B2 (en) * | 2013-03-14 | 2015-10-27 | Nucleus Scientific, Inc. | Actuator configuration for a rotary drive |
| WO2013076712A2 (en) * | 2013-03-19 | 2013-05-30 | Wasfi Alshdaifat | Top-wing aerobotic glass cleaner |
| JP5811384B1 (en) * | 2014-05-31 | 2015-11-11 | 榮一 渡邊 | Air levitation device and its air navigation |
| CN110001949A (en) * | 2019-03-13 | 2019-07-12 | 陈铭 | A kind of compound rotation unmanned helicopter of close coupled type |
| CN111232194B (en) * | 2020-03-23 | 2024-07-02 | 北京海空行科技有限公司 | Rotor lifting mechanism for coaxial double rotors and flying device |
-
2020
- 2020-11-26 CN CN202011346831.6A patent/CN112455650A/en not_active Withdrawn
- 2020-12-04 WO PCT/CN2020/133750 patent/WO2022110271A1/en active Application Filing
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101492093A (en) * | 2009-03-12 | 2009-07-29 | 北京理工大学 | Flapping rotor wing design method and microminiature flapping rotor wing designed according to the method |
| CN108995804A (en) * | 2018-08-01 | 2018-12-14 | 北京理工大学 | The bionic Aircraft for flutterring rotor and the conversion of flapping flight mode is realized based on the deformation wing |
| CN110104175A (en) * | 2019-04-24 | 2019-08-09 | 北京航空航天大学 | A kind of coaxial reversed pair is flutterred rotor mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2022110271A1 (en) | 2022-06-02 |
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Application publication date: 20210309 |