CN111392038A - Flapping wing aircraft wing capable of being folded and stored quickly - Google Patents
Flapping wing aircraft wing capable of being folded and stored quickly Download PDFInfo
- Publication number
- CN111392038A CN111392038A CN202010218973.8A CN202010218973A CN111392038A CN 111392038 A CN111392038 A CN 111392038A CN 202010218973 A CN202010218973 A CN 202010218973A CN 111392038 A CN111392038 A CN 111392038A
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- China
- Prior art keywords
- front edge
- carbon tube
- wing
- edge carbon
- tube
- 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
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 69
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 69
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 33
- 239000002390 adhesive tape Substances 0.000 claims abstract description 12
- 238000000034 method Methods 0.000 claims description 5
- 238000005728 strengthening Methods 0.000 claims 11
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 235000001968 nicotinic acid Nutrition 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
Abstract
The invention discloses a flapping wing aircraft wing capable of being folded and stored quickly, which comprises a root front edge carbon tube, a tip front edge carbon tube, a sliding quick-release tube, a wing film, a main reinforcing rib, an auxiliary reinforcing rib, a non-elastic line and a transparent adhesive tape. The root front edge carbon tube and the tip front edge carbon tube can be connected through a sliding quick release tube, the wing film is pasted to the two front edge rods through a transparent adhesive tape, the pasting part avoids the movement range of the sliding sleeve, the main reinforcing rib and the auxiliary reinforcing rib are respectively arranged in the middle and outside of the wing film, the two reinforcing ribs are pasted to the wing film through the transparent adhesive tape, a non-elastic line penetrates through the two front edge carbon tubes, one end of the non-elastic line is stably fixed inside the root front edge carbon tube, the other end of the non-elastic line is stably fixed inside the tip front edge carbon tube, and when the sliding quick release tube completely moves to the root front edge carbon tube, the wing can. The wing folding device can realize the rapid folding and storage of the wings of the flapping wing aircraft, and has the characteristics of simple structure, low manufacturing difficulty and convenient carrying.
Description
Technical Field
The invention relates to the technical field of mechanical design and flapping wing aircrafts, in particular to a flapping wing aircraft wing capable of being folded and stored quickly.
Background
Compared with the conventional aircraft, the flapping wing aircraft has the outstanding characteristics of bionics, good concealment, light weight, low cost, strong flexibility and the like, so that the flapping wing aircraft has attractive application prospect in both military fields and civil fields. The main driving force of the flapping wing air vehicle is derived from the reciprocating flapping of the wings, on the premise of the same flapping frequency, the larger the surface area of the wings is, the higher the flapping efficiency is, and the overlarge surface area of the wings causes the inconvenience of carrying the wings out and the easy damage of the wings. Therefore, how to properly arrange the folding and unfolding mechanism of the flapping wing, the flapping wing aircraft can be unfolded quickly before taking off and can be folded and stored quickly after finishing flying, and the folding and unfolding mechanism is the key for improving the practicability and flexibility of the flapping wing aircraft.
Disclosure of Invention
The invention provides a flapping wing aircraft wing capable of being folded and stored quickly, which solves the problems that the flapping wing aircraft wing is difficult to carry and is easy to damage due to overlarge size.
The invention comprises a root front edge carbon tube, a tip front edge carbon tube, a sliding quick-release tube, a wing film, a reinforcing rib and a non-elastic line, wherein the root front edge carbon tube, the tip front edge carbon tube and the sliding quick-release tube are all hollow tubes; the wing film is adhered to the root front edge carbon tube and the tip front edge carbon tube, and reinforcing ribs are fixed on the wing film; and the non-elastic line penetrates through the root front edge carbon tube and the tip front edge carbon tube, one end of the non-elastic line is stably fixed inside the root front edge carbon tube, the other end of the non-elastic line is stably fixed inside the tip front edge carbon tube, and when the sliding quick-release tube completely moves to the root front edge carbon tube, the wing can rotate around the middle shaft to be folded for 180 degrees to complete folding and storage.
The length of the thin-wall section of the carbon tube at the front edge of the root part is slightly larger than that of the sliding quick-release tube, so that the sliding quick-release tube can slide along the carbon tube at the front edge of the root part without obstruction.
The improvement is further that the connecting end of the front edge carbon tube at the tip part and the sliding quick-release tube is polished into a conical shape, and the length of the conical shape is half of that of the sliding quick-release tube, so that the sliding quick-release tube is ensured to have enough locking friction force in a locking state.
The wing film is further improved, the wing film is adhered to the root front edge carbon tube and the tip front edge carbon tube through the transparent adhesive tape, the transparent adhesive tape completely wraps the root front edge carbon tube and the tip front edge carbon tube, the wing film adopts a double-sided adhering mode, and the adhering process avoids the movement range of the sliding quick-release tube.
The improved structure comprises a plurality of reinforcing ribs, wherein the reinforcing ribs comprise main reinforcing ribs and additional reinforcing ribs, the main reinforcing ribs and the additional reinforcing ribs are arranged on the same side of the wing film, the plane position is located on one side of the folding axis of the wing film, the extension lines of the main reinforcing ribs and the additional reinforcing ribs are converged and matched with one point, the axis of each main reinforcing rib is at an angle of 85 degrees with the tip front edge carbon pipe shaft clamp, the axis of each auxiliary reinforcing rib is at an angle of 35 degrees with the tip front edge carbon pipe shaft clamp, and the main reinforcing ribs and the additional reinforcing ribs are fixed on the wing film through.
The invention has the beneficial effects that:
1. the problem of the quick folding of flapping wing accomodate is solved.
2. The whole flapping wing has small manufacturing difficulty and simple and reliable mechanism.
3. By utilizing the principle of friction self-locking and centrifugal force locking, the flapping wings are not easy to separate in the flapping process, and the whole service life is long.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a folding isometric view of the wing of the present invention;
FIG. 3 is a partial schematic view of the sliding quick release tube of the present invention in a fully locked state;
FIG. 4 is a partial schematic view of the slide quick release tube of the present invention in a fully open position;
fig. 5 is a top partial schematic view of the present invention in a semi-folded state.
In the drawings: 1. a root leading edge carbon tube; 2. a tip leading edge carbon tube; 3. sliding the quick-release pipe; 4. wing film 5, main reinforcing rib; 6. a secondary reinforcing rib; 7. no elastic line; 8. transparent adhesive tape.
Detailed Description
The invention will be further explained with reference to the drawings.
The invention provides a flapping wing aircraft wing capable of being folded and stored quickly, which comprises a root front edge carbon tube 1, a tip front edge carbon tube 2, a sliding quick-release tube 3, a wing film 4, a main reinforcing rib 5, an auxiliary reinforcing rib 6, a non-elastic line 7 and a transparent adhesive tape 8, as shown in figure 1. The root front edge carbon tube 1 is a hollow tube, one end of the root front edge carbon tube can be inserted into a flapping mechanism of the ornithopter, the outer diameter of the other end of the root front edge carbon tube is evenly thinned, and the length of the thinned part is slightly larger than that of the sliding quick-release tube 3, so that the sliding quick-release tube can slide along the root front edge carbon tube 1 without hindrance. The tip leading edge carbon tube 2 is also a hollow tube, one end of the tip leading edge carbon tube is polished to be conical, the length of the conical shape is half of that of the sliding quick-release tube 3, so that the sliding quick-release tube 3 has enough locking friction force in a locking state, and in the flapping process of the wing, the sliding quick-release tube 3 can generate an outward centrifugal force along the axis of the tip leading edge carbon tube 2, so that the wing is further ensured to be in the locking state in the flapping state. The fully locked state and the fully opened state of the sliding quick release pipe are respectively shown in fig. 3 and 4.
The wing film 4 is adhered to the root front edge carbon tube 1 and the tip front edge carbon tube 2 through the transparent adhesive tape 8, the transparent adhesive tape 8 completely wraps the root front edge carbon tube 1 and the tip front edge carbon tube 2, the wing film 4 adopts a double-sided adhering mode, and the adhering process avoids the movement range of the sliding quick-release tube 3. The main reinforcing ribs 5 and the additional reinforcing ribs 6 are arranged on the same side of the wing film 4, the plane position is located on one side of the folding axis of the wing film 4, the extension lines of the main reinforcing ribs 5 and the additional reinforcing ribs 6 are converged at one point, the angle between the axis of the main reinforcing ribs 5 and the tip front edge carbon tube 2 axis clamp is 85 degrees, the angle between the axis of the auxiliary reinforcing ribs 6 and the tip front edge carbon tube 2 axis clamp is 35 degrees, and the main reinforcing ribs 5 and the additional reinforcing ribs 6 are fixed on the wing film 4 through the transparent adhesive tape 8 in a sticking mode. The non-elastic line 7 penetrates through the root front edge carbon tube 1 and the tip front edge carbon tube 2, one end of the non-elastic line is stably fixed inside the root front edge carbon tube 1, the other end of the non-elastic line is stably fixed inside the tip front edge carbon tube 2, when the sliding quick-release tube 3 completely moves to the root front edge carbon tube 1, the wing can rotate around the middle shaft and is folded by 180 degrees, folding and storage are completed, and the folding state is as shown in fig. 2 and 5.
While the invention has been described in terms of its preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention.
Claims (5)
1. The utility model provides a flapping wing aircraft wing that can fold fast and accomodate which characterized in that: the flapping-wing aircraft wing comprises a root front edge carbon tube, a tip front edge carbon tube, a sliding quick-release tube, a wing film, a reinforcing rib and a non-elastic line, wherein the root front edge carbon tube, the tip front edge carbon tube and the sliding quick-release tube are all hollow tubes; the wing film is adhered to the root front edge carbon tube and the tip front edge carbon tube, and reinforcing ribs are fixed on the wing film; and the non-elastic line penetrates through the root front edge carbon tube and the tip front edge carbon tube, one end of the non-elastic line is stably fixed inside the root front edge carbon tube, the other end of the non-elastic line is stably fixed inside the tip front edge carbon tube, and when the sliding quick-release tube completely moves to the root front edge carbon tube, the wing can rotate around the middle shaft to be folded for 180 degrees to complete folding and storage.
2. A rapidly collapsible storage flapping wing aircraft wing according to claim 1 wherein: the length of the thin-wall section of the carbon tube at the front edge of the root part is slightly larger than that of the sliding quick-release tube.
3. A rapidly collapsible storage flapping wing aircraft wing according to claim 1 wherein: the connecting end of the tip front edge carbon tube and the sliding quick-release tube is polished into a cone shape, and the length of the cone shape is half of that of the sliding quick-release tube.
4. A rapidly collapsible storage flapping wing aircraft wing according to claim 1 wherein: the wing film is adhered to the root front edge carbon tube and the tip front edge carbon tube through the transparent adhesive tape, the transparent adhesive tape completely wraps the root front edge carbon tube and the tip front edge carbon tube, the wing film adopts a double-sided adhering mode, and the moving range of the sliding quick-release tube is avoided in the adhering process.
5. A rapidly collapsible storage flapping wing aircraft wing according to claim 1 wherein: the strengthening rib include main strengthening rib and additional strengthening rib, main strengthening rib and additional strengthening rib arrange in the same one side of wing film, the plane position is located one side of wing film folding axis, the extension line of main strengthening rib and additional strengthening rib is converged and a little, main strengthening rib axis and tip front edge carbon tube axle fastener 85 degrees angles, vice strengthening rib axis and tip front edge carbon tube axle fastener 35 degrees angles, main strengthening rib and additional strengthening rib are fixed in on the wing film through scotch tape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010218973.8A CN111392038A (en) | 2020-03-25 | 2020-03-25 | Flapping wing aircraft wing capable of being folded and stored quickly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010218973.8A CN111392038A (en) | 2020-03-25 | 2020-03-25 | Flapping wing aircraft wing capable of being folded and stored quickly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111392038A true CN111392038A (en) | 2020-07-10 |
Family
ID=71427565
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010218973.8A Pending CN111392038A (en) | 2020-03-25 | 2020-03-25 | Flapping wing aircraft wing capable of being folded and stored quickly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111392038A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113173247A (en) * | 2021-05-07 | 2021-07-27 | 北京航空航天大学 | Bionic folding unmanned aerial vehicle using flexible airfoil |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB756673A (en) * | 1953-08-05 | 1956-09-05 | Ronald Clemens | An improved structure of aerofoil shape for use in aircraft |
| RU2288139C2 (en) * | 2004-07-22 | 2006-11-27 | Анатолий Петрович Низяев | Construction of flapping-wing aircraft at low moment of return motion |
| CN201308184Y (en) * | 2008-12-05 | 2009-09-16 | 李明贤 | Length-adjustable folded crutch |
| CN201842258U (en) * | 2010-09-16 | 2011-05-25 | 孙为红 | Folding rotor wing of rotorcraft |
| CN102381476A (en) * | 2011-08-11 | 2012-03-21 | 西北工业大学 | Miniature semi-active folding flapping wing |
| CN203512032U (en) * | 2013-10-30 | 2014-04-02 | 吉林大学 | Bionic folding wing of micro air vehicle |
| CN204593144U (en) * | 2015-05-06 | 2015-08-26 | 李秋芬 | A kind of LED street lamp |
| CN204846246U (en) * | 2015-07-07 | 2015-12-09 | 东莞市创明电池技术有限公司 | Beta structure and have this beta structure's scooter |
| CN205574277U (en) * | 2016-05-05 | 2016-09-14 | 吉林大学 | A full -automatic collapsible flapping wing that is used for miniature aircraft of flapping wing type |
| CN106394897A (en) * | 2016-10-26 | 2017-02-15 | 吉林大学 | Foldable wind-resistant flapping wing of flapping-wing micro air vehicle |
| CN206968966U (en) * | 2017-06-02 | 2018-02-06 | 广州长天航空科技有限公司 | A kind of foldable undercarriage of multi-rotor unmanned aerial vehicle |
| CN108177759A (en) * | 2017-12-28 | 2018-06-19 | 王开富 | A kind of unmanned plane horn fold mechanism with locking function |
| CN208053632U (en) * | 2018-04-04 | 2018-11-06 | 吉林大学 | A kind of self-regulation deformation flexible wing mechanism for foldable flapping-wing MAV |
| CN110466755A (en) * | 2019-09-20 | 2019-11-19 | 西北工业大学 | It is applicable in the chord length self-adapting stretching formula flapping wing and flapping-wing aircraft of active twist flapping mechanism |
-
2020
- 2020-03-25 CN CN202010218973.8A patent/CN111392038A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB756673A (en) * | 1953-08-05 | 1956-09-05 | Ronald Clemens | An improved structure of aerofoil shape for use in aircraft |
| RU2288139C2 (en) * | 2004-07-22 | 2006-11-27 | Анатолий Петрович Низяев | Construction of flapping-wing aircraft at low moment of return motion |
| CN201308184Y (en) * | 2008-12-05 | 2009-09-16 | 李明贤 | Length-adjustable folded crutch |
| CN201842258U (en) * | 2010-09-16 | 2011-05-25 | 孙为红 | Folding rotor wing of rotorcraft |
| CN102381476A (en) * | 2011-08-11 | 2012-03-21 | 西北工业大学 | Miniature semi-active folding flapping wing |
| CN203512032U (en) * | 2013-10-30 | 2014-04-02 | 吉林大学 | Bionic folding wing of micro air vehicle |
| CN204593144U (en) * | 2015-05-06 | 2015-08-26 | 李秋芬 | A kind of LED street lamp |
| CN204846246U (en) * | 2015-07-07 | 2015-12-09 | 东莞市创明电池技术有限公司 | Beta structure and have this beta structure's scooter |
| CN205574277U (en) * | 2016-05-05 | 2016-09-14 | 吉林大学 | A full -automatic collapsible flapping wing that is used for miniature aircraft of flapping wing type |
| CN106394897A (en) * | 2016-10-26 | 2017-02-15 | 吉林大学 | Foldable wind-resistant flapping wing of flapping-wing micro air vehicle |
| CN206968966U (en) * | 2017-06-02 | 2018-02-06 | 广州长天航空科技有限公司 | A kind of foldable undercarriage of multi-rotor unmanned aerial vehicle |
| CN108177759A (en) * | 2017-12-28 | 2018-06-19 | 王开富 | A kind of unmanned plane horn fold mechanism with locking function |
| CN208053632U (en) * | 2018-04-04 | 2018-11-06 | 吉林大学 | A kind of self-regulation deformation flexible wing mechanism for foldable flapping-wing MAV |
| CN110466755A (en) * | 2019-09-20 | 2019-11-19 | 西北工业大学 | It is applicable in the chord length self-adapting stretching formula flapping wing and flapping-wing aircraft of active twist flapping mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113173247A (en) * | 2021-05-07 | 2021-07-27 | 北京航空航天大学 | Bionic folding unmanned aerial vehicle using flexible airfoil |
| CN113173247B (en) * | 2021-05-07 | 2022-12-09 | 北京航空航天大学 | Bionic folding unmanned aerial vehicle using flexible airfoil |
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