CN109353498A - The wing of flapping wing aircraft - Google Patents
The wing of flapping wing aircraft Download PDFInfo
- Publication number
- CN109353498A CN109353498A CN201811471242.3A CN201811471242A CN109353498A CN 109353498 A CN109353498 A CN 109353498A CN 201811471242 A CN201811471242 A CN 201811471242A CN 109353498 A CN109353498 A CN 109353498A
- Authority
- CN
- China
- Prior art keywords
- wing
- axis
- spar
- skeleton
- close
- 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
- 239000002131 composite material Substances 0.000 claims description 15
- 239000000835 fiber Substances 0.000 claims description 11
- 239000004744 fabric Substances 0.000 claims description 5
- 239000012779 reinforcing material Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims 2
- ZCCUUQDIBDJBTK-UHFFFAOYSA-N psoralen Chemical compound C1=C2OC(=O)C=CC2=CC2=C1OC=C2 ZCCUUQDIBDJBTK-UHFFFAOYSA-N 0.000 claims 2
- 239000002023 wood Substances 0.000 claims 2
- VXGRJERITKFWPL-UHFFFAOYSA-N 4',5'-Dihydropsoralen Natural products C1=C2OC(=O)C=CC2=CC2=C1OCC2 VXGRJERITKFWPL-UHFFFAOYSA-N 0.000 claims 1
- 241001416181 Axis axis Species 0.000 claims 1
- 241000596926 Sparaxis Species 0.000 abstract description 11
- 238000004519 manufacturing process Methods 0.000 abstract description 8
- 241000238631 Hexapoda Species 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 210000000988 bone and bone Anatomy 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000009940 knitting Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The present invention provides a kind of wings of flapping wing aircraft, including skeleton, liner, film, filament.There are spar, aperture, quarter butt, rib on the skeleton.The aperture is located at skeleton close to the part of airfoil root, and quarter butt, rib are connected on spar, and quarter butt axis, rib axis are vertical with spar axis.The component of dynamic wing-beat is provided on flapping wing aircraft, which drives wing to flap around the axis vertical with spar axis, there is the through-hole for the fitting machine wing on the component.The suture of filament is respectively used in part of the film close to wing ending, the part close to airfoil root, filament some close to rib, some is close to spar.Wing manufacturing process provided by the invention is simple, and manufacture difficulty is small, and the film of wing is wrapped securely on the skeleton of wing, and the film of wing and the skeleton of wing are not readily separated, and the service life of wing is long.
Description
Technical field
The present invention relates to aircraft field, the wing of specifically a kind of flapping wing aircraft.
Background technique
Insect, birds, the bat that can be flown in nature all use flapping flight, with high maneuverability and low energy consumption
Feature.Flapping wing aircraft is the aircraft for being different from Fixed Wing AirVehicle, rotor craft, it is using insect, birds, bat
The aircraft of flying method, military, civilian aspect is widely used.Flight, such as moral are realized there are many flapping wing aircraft
" SmartBird " flapping wing aircraft of Fei Situo company of state.
The wing of flapping wing aircraft has the following problems in the prior art:
1, the manufacturing process of wing is complicated, and the manufacture difficulty of wing is big.
2, the film of wing is not secured enough in conjunction with the skeleton of wing, and the service life of wing falls short of.
Summary of the invention
The present invention in order to solve problems in the prior art, provides a kind of wing of flapping wing aircraft, the manufacture work of wing
Skill is simple, and the manufacture difficulty of wing is small, and the film of wing is wrapped securely on the skeleton of wing, the film of wing and the bone of wing
Frame is not readily separated, and the service life of wing is long.
The present invention includes skeleton, liner, film, filament.There are spar, aperture, quarter butt, rib on the skeleton, it is described
Aperture be located at skeleton close to the part of airfoil root, the quarter butt, rib are connected on spar, quarter butt axis, rib axis
Line is vertical with spar axis.
The component of dynamic wing-beat is provided on flapping wing aircraft, which drives wing around vertical with spar axis
Axis flap, have the through-hole for the fitting machine wing on the component.It is first that skeleton is close when wing is installed on toward flapping wing aircraft
Partially passing through for airfoil root is used to install the through-hole of wing on the component for driving wing-beat, then pin is inserted into aperture, prevents
Only wing falls off from flapping wing aircraft.
Entire skeleton is carved by one piece of composite board, and the reinforcing material in the composite board is high intensity
Fibre knitting cloth, high strength fibre woven cloth are one or more layers.By one piece of this composite board put in the horizontal plane, from
Composite board is observed in surface, and in composite board there are two the trends of fibre bundle, the two trends are hung down mutually
Directly, the trend of fibre bundle and the axis of spar are parallel or vertical.
Liner is fixed on the skeleton, liner at least one side is plane, which is attached on skeleton；Liner is at least
Having one side is arc surface, and the center of circle of " circular arc " is on spar axis in the arc surface.After wing is mounted on flapping wing aircraft, lining
Pad the gap between the through-hole for filling up skeleton and for installing wing, spar axis and the through-bore axis weight for installing wing
It closes, entire wing can surround spar axis oscillating.
It drives and is fixed with protrusion on the component of wing-beat, after wing is mounted on flapping wing aircraft, protrusion passes through limitation
Quarter butt limits the range that entire wing surrounds spar axis oscillating around the range of spar axis oscillating, when wing surrounds and the wing
When the vertical axis of beam axis is flapped, entire wing can be put under the action of air force and inertia force around spar axis
It is dynamic.
It is surrounded by film on the skeleton, film is sutured with filament, wraps film on skeleton securely, need using 2
Bar filament:
(1) film is sutured close to the part of wing ending with a filament, filament some close to rib, there are also one for filament
Divide close to spar；
(2) film is sutured close to the part of airfoil root with a filament, filament some close to rib, there are also one for filament
Divide close to spar.
The beneficial effects of the invention are that:
1, the manufacturing process of wing is simple, and the manufacture difficulty of wing is small.
2, the film of wing is wrapped securely on the skeleton of wing, and the film of wing and the skeleton of wing are not readily separated, machine
The service life of the wing is long.
Detailed description of the invention
Fig. 1 is the main view of wing of the present invention.
Fig. 2 is the shaft side figure of skeleton of the present invention.
Fig. 3 is the axonometric drawing that the present invention pads.
Fig. 4 is the shaft side figure of skeleton of the present invention, liner.
Fig. 5 is the expanded view of film of the present invention, and dotted line sutures film along figure.
Specific embodiment
The present invention will be further explained below with reference to the attached drawings.
A kind of specific embodiment of the invention is as shown in Figure 1.The present invention includes skeleton 1, liner 2, film 3, filament 4.
There are spar 5, aperture 6, quarter butt 7, rib 8 on the skeleton 1, the aperture 6 is located at skeleton 1 close to the portion of airfoil root
Point, the quarter butt 7, rib 8 are connected on spar 5, and 7 axis of quarter butt, 8 axis of rib are vertical with 5 axis of spar.
There is the component for driving wing-beat on flapping wing aircraft, which drives wing around vertical with 5 axis of spar
Axis is flapped, and has the through-hole for the fitting machine wing on the component.It is first that skeleton 1 is close when wing is installed on toward flapping wing aircraft
Airfoil root is partially passed through for installing the through-hole of wing on the component for driving wing-beat, then pin is inserted into aperture 6, is prevented
Only wing falls off from flapping wing aircraft.
Skeleton 1 is as shown in Figure 2.Entire skeleton 1 is carved by one piece of composite board, in the composite board
Reinforcing material is high strength fibre woven cloth, and high strength fibre woven cloth can be one layer, be also possible to multilayer.It is this by one piece
Composite board is put in the horizontal plane, the composite board from surface, and fibre bundle walks in composite board
There are two only, the two move towards orthogonal, and the trend of fibre bundle is parallel or vertical with the axis of spar 5.
Liner 2 is fixed on the skeleton 1.Liner 2 is as shown in Figure 3.At least one side of liner 2 is plane, the plane
It is attached on skeleton 1；At least one side of liner 2 is arc surface, and the center of circle of " circular arc " is on 5 axis of spar in the arc surface.Skeleton
1, liner 2 is as shown in Figure 4.After wing is mounted on flapping wing aircraft, pad for filling up skeleton 1 and for installing the logical of wing
Gap between hole, 5 axis of spar are overlapped with the through-bore axis for installing wing, and entire wing can be put around 5 axis of spar
It is dynamic.
It drives and is fixed with protrusion on the component of wing-beat, after wing is mounted on flapping wing aircraft, protrusion passes through limitation
Quarter butt 7 limits the range that entire wing surrounds 5 axis oscillating of spar around the range of 5 axis oscillating of spar.When wing surrounds
When the axis vertical with 5 axis of spar is flapped, entire wing can surround 5 axis of spar under the action of air force and inertia force
String pendulum is dynamic.
Film 3 is surrounded by the skeleton 1.Film 3 is as shown in Figure 5.Film 3 is sutured with filament 4, makes film 3 securely
Packet needs on skeleton 1 using 2 filaments 4:
(1) film 3 is sutured close to the part of wing ending with a filament 4, filament 4 some close to rib 8, filament 4 is also
Some is close to spar 5；
(2) film 3 is sutured close to the part of airfoil root with a filament 4, filament 4 some close to rib 8, filament 4 is also
Some is close to spar 5.
There are many concrete application approach of the present invention, the above is only a preferred embodiment of the present invention, it is noted that for
For those skilled in the art, without departing from the principle of the present invention, it can also make several improvements, this
A little improve also should be regarded as protection scope of the present invention.
Claims (5)
1. a kind of wing of flapping wing aircraft, it is characterised in that: including skeleton (1), liner (2), film (3), filament (4)；Institute
There are spar (5), aperture (6), quarter butt (7), rib (8) on the skeleton (1) stated, the aperture (6) is located at skeleton (1) close to machine
The part in wing root portion, the quarter butt (7), rib (8) are connected on spar (5), quarter butt (5) axis, rib (8) axis and the wing
Beam (5) axis is vertical；
The component of dynamic wing-beat is provided on flapping wing aircraft, which drives wing around vertical with spar (5) axis
Axis flap, have the through-hole for the fitting machine wing on the component；When installing wing on toward flapping wing aircraft, first by skeleton (1)
It close to partially passing through for airfoil root is used to that the through-hole of wing be installed on the component for driving wing-beat, then pin is inserted into aperture
(6).
2. the wing of flapping wing aircraft according to claim 1, it is characterised in that: entire skeleton (1) is by one piece of composite wood
Flitch material is carved, and the reinforcing material in the composite board is high strength fibre woven cloth；By one piece of this composite wood
Flitch material is put in the horizontal plane, the composite board from surface, and the trend of fibre bundle only has in composite board
Two, the two move towards orthogonal, and the trend and the axis of spar (5) of fibre bundle are parallel or vertical.
3. the wing of flapping wing aircraft according to claim 1, it is characterised in that: be fixed with lining on the skeleton (1)
It pads (2), liner (2) at least one side is plane, which is attached on skeleton (1)；Padding (2) at least one side is arc surface,
The center of circle of " circular arc " is on spar (5) axis in the arc surface, and after wing is mounted on flapping wing aircraft, liner (2) is for filling out
Gap between Psoralen frame (1) and through-hole for installing wing, spar (5) axis and the through-bore axis weight for installing wing
It closes.
4. the wing of flapping wing aircraft according to claim 1, it is characterised in that: drive fixed on the component of wing-beat
After having protrusion, wing to be mounted on flapping wing aircraft, protrusion surrounds the range of spar (5) axis oscillating by limitation quarter butt (7)
The range that entire wing surrounds spar (5) axis oscillating is limited, when wing is flapped around the axis vertical with spar (5) axis
When, entire wing surrounds spar (5) axis oscillating under the action of air force and inertia force.
5. the wing of flapping wing aircraft according to claim 1, it is characterised in that: be surrounded by film on the skeleton (1)
(3), filament (4) suture is respectively used in part of the film (3) close to wing ending, the part close to airfoil root, and filament (4) has
A part is close to rib (8), some is close to spar (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811471242.3A CN109353498A (en) | 2018-12-04 | 2018-12-04 | The wing of flapping wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811471242.3A CN109353498A (en) | 2018-12-04 | 2018-12-04 | The wing of flapping wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109353498A true CN109353498A (en) | 2019-02-19 |
Family
ID=65331040
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811471242.3A Pending CN109353498A (en) | 2018-12-04 | 2018-12-04 | The wing of flapping wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109353498A (en) |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB116914A (en) * | 1917-06-19 | 1918-06-19 | James Dennis Roots | A Flying Machine. |
| GB442667A (en) * | 1934-05-28 | 1936-01-29 | Karl Haenle | Ornithopter |
| JPH05178293A (en) * | 1991-12-27 | 1993-07-20 | Komota Masayuki | Flapping airplane |
| JPH0733092A (en) * | 1993-07-16 | 1995-02-03 | Tamakingumi:Kk | Flapping flying device and flying thrust generating device |
| RU2063367C1 (en) * | 1993-06-10 | 1996-07-10 | Алексей Алексеевич Леонтьев | Flapping wing aeroplane |
| US6206324B1 (en) * | 1999-08-30 | 2001-03-27 | Michael J. C. Smith | Wing-drive mechanism, vehicle employing same, and method for controlling the wing-drive mechanism and vehicle employing same |
| US6659397B1 (en) * | 2002-10-18 | 2003-12-09 | Richard Charron | Control system for ornithopter |
| CN2928681Y (en) * | 2006-06-15 | 2007-08-01 | 武川 | Wing surface jet vortex flapping wing aircraft |
| RU2375253C1 (en) * | 2008-06-10 | 2009-12-10 | Юрий Семенович Дёмин | Flight vehicle with flapping wings ("dragonfly") |
| WO2012112816A1 (en) * | 2011-02-16 | 2012-08-23 | Aerovironment, Inc. | Air vehicle flight mechanism and control method for non-sinusoidal wing flapping |
| CN106005405A (en) * | 2016-07-18 | 2016-10-12 | 上海交通大学 | High-frequency flapping-wing bionic insect aircraft with controllable passive torsion |
| CN107161340A (en) * | 2017-05-27 | 2017-09-15 | 南京航空航天大学 | Bionic flapping-wing flying vehicle and its flight control method |
| CN107416202A (en) * | 2017-07-05 | 2017-12-01 | 北京航空航天大学 | Micro flapping wing air vehicle |
| CN209833998U (en) * | 2018-12-04 | 2019-12-24 | 南京航空航天大学 | Wing of flapping wing aircraft |
-
2018
- 2018-12-04 CN CN201811471242.3A patent/CN109353498A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB116914A (en) * | 1917-06-19 | 1918-06-19 | James Dennis Roots | A Flying Machine. |
| GB442667A (en) * | 1934-05-28 | 1936-01-29 | Karl Haenle | Ornithopter |
| JPH05178293A (en) * | 1991-12-27 | 1993-07-20 | Komota Masayuki | Flapping airplane |
| RU2063367C1 (en) * | 1993-06-10 | 1996-07-10 | Алексей Алексеевич Леонтьев | Flapping wing aeroplane |
| JPH0733092A (en) * | 1993-07-16 | 1995-02-03 | Tamakingumi:Kk | Flapping flying device and flying thrust generating device |
| US6206324B1 (en) * | 1999-08-30 | 2001-03-27 | Michael J. C. Smith | Wing-drive mechanism, vehicle employing same, and method for controlling the wing-drive mechanism and vehicle employing same |
| US6659397B1 (en) * | 2002-10-18 | 2003-12-09 | Richard Charron | Control system for ornithopter |
| CN2928681Y (en) * | 2006-06-15 | 2007-08-01 | 武川 | Wing surface jet vortex flapping wing aircraft |
| RU2375253C1 (en) * | 2008-06-10 | 2009-12-10 | Юрий Семенович Дёмин | Flight vehicle with flapping wings ("dragonfly") |
| WO2012112816A1 (en) * | 2011-02-16 | 2012-08-23 | Aerovironment, Inc. | Air vehicle flight mechanism and control method for non-sinusoidal wing flapping |
| CN106005405A (en) * | 2016-07-18 | 2016-10-12 | 上海交通大学 | High-frequency flapping-wing bionic insect aircraft with controllable passive torsion |
| CN107161340A (en) * | 2017-05-27 | 2017-09-15 | 南京航空航天大学 | Bionic flapping-wing flying vehicle and its flight control method |
| CN107416202A (en) * | 2017-07-05 | 2017-12-01 | 北京航空航天大学 | Micro flapping wing air vehicle |
| CN209833998U (en) * | 2018-12-04 | 2019-12-24 | 南京航空航天大学 | Wing of flapping wing aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104340356B (en) | Aircraft body joint side | |
| CN106043691B (en) | The bionical wing of fluttering that wingtip cracks | |
| CN105905274B (en) | The airframe structure of eight rotor wing unmanned aerial vehicles | |
| CN104443375B (en) | Rotor blade and the structural system for being connected in rotor blade in rotor head | |
| KR101499190B1 (en) | Separable blade attachment for a bearingless rotor of a helicopter | |
| ES2799935T3 (en) | Aircraft aerodynamic profile with a dotted trailing edge and manufacturing procedure for the same | |
| CN109353498A (en) | The wing of flapping wing aircraft | |
| JPH05178293A (en) | Flapping airplane | |
| CN109353497A (en) | Can VTOL flapping wing aircraft wing | |
| US9708058B2 (en) | Device for folding a blade, a blade, and an aircraft | |
| CN109823532A (en) | A kind of mechanism that achievable wing is passively folded and reversed | |
| CN110143282A (en) | A kind of aircraft using high aspect ratio twin fuselage Flying-wing | |
| CN209833998U (en) | Wing of flapping wing aircraft | |
| CN103569359B (en) | Transmission helicopter in multi-feature-membrane spiral arm control boomerang wing trunk arm | |
| CN107089323A (en) | A kind of aircraft rotor driver and aircraft | |
| CN109383755A (en) | It is a kind of can the aircraft leading edge structure hit of anti-bird | |
| CN107364576A (en) | One kind vibration rotor aircraft | |
| CN106564588A (en) | Unmanned helicopter blade and unmanned helicopter | |
| CN207523915U (en) | A kind of strong light-duty sport plane wing of anti-load-carrying ability | |
| CN206511106U (en) | A kind of VTOL composite wing Vertical Dynamic device for quickly disassembling | |
| US2067228A (en) | Rotary sustaining wings for aircraft | |
| CN104859856A (en) | Scheme for improving flapping intensity of flapping-wing aircrafts | |
| US10273013B1 (en) | Preferred break points and paths in airframes for ballistic parachute systems | |
| CN209258371U (en) | The cantilever connection structure of the dynamic unmanned plane of oil | |
| CN207809755U (en) | Stratospheric airship aerodynamic arrangement structure with auxiliary stabilization |
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 |