CN113998104A - Flapping wing aircraft wing capable of hovering and having bionic wing rib form and shape - Google Patents

Flapping wing aircraft wing capable of hovering and having bionic wing rib form and shape Download PDF

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Publication number
CN113998104A
CN113998104A CN202111476664.1A CN202111476664A CN113998104A CN 113998104 A CN113998104 A CN 113998104A CN 202111476664 A CN202111476664 A CN 202111476664A CN 113998104 A CN113998104 A CN 113998104A
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China
Prior art keywords
wing
rib
main beam
length
hovering
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Pending
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CN202111476664.1A
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Chinese (zh)
Inventor
杨晓君
稂鑫雨
宋笔锋
张明昊
刘恒
杨驰
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Shenzhen Institute of Northwestern Polytechnical University
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Shenzhen Institute of Northwestern Polytechnical University
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Priority to CN202111476664.1A priority Critical patent/CN113998104A/en
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    • 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
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/182—Stringers, longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/187—Ribs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels

Abstract

The invention provides a hovering flapping wing aircraft wing with bionic wing rib form and shape, which comprises a wing framework, wherein the wing framework comprises a main beam and wing ribs, and the number of the wing ribs is five, namely a first wing rib, a second wing rib, a third wing rib, a fourth wing rib and a fifth wing rib; the front edges of the first rib and the second rib are in point contact and are fixed on the main beam; the front edge points of the third rib, the fourth rib and the fifth rib are sequentially arranged on the main beam and are distributed in a dispersed manner along the spanwise direction; the wing ribs with the gradually increased curvature radius in the spanwise direction are arranged, spanwise rigidity and chordwise rigidity can be kept at the same time, the spanwise rigidity is increased by the wing ribs with the larger curvature radius at the wing tips, and overlarge bending deformation in the spanwise direction is avoided.

Description

Flapping wing aircraft wing capable of hovering and having bionic wing rib form and shape
Technical Field
The invention belongs to the technical field of miniature ornithopters, and particularly relates to a wing of an ornithopter capable of hovering and having a bionic wing rib form and a bionic wing rib shape.
Background
The flapping wing aircraft is a novel bionic aircraft which generates lift force and thrust force by means of wing flapping, has the characteristics of good concealment and high flight efficiency, is widely concerned at home and abroad, and has wide application prospect in the fields of military and civil use.
The wing is a main part for generating lift force and thrust force when the flapping wing aircraft flies, and the design of the wing with excellent performance is of great importance to the high-performance flapping wing aircraft. At present, most of common flapping-wing aircrafts are front-flying flapping-wing aircrafts, and the flapping-wing aircrafts capable of hovering are rare, because the wings capable of achieving stable hovering at present are low in aerodynamic efficiency and large in power consumption, so that the flapping-wing aircrafts cannot achieve stable hovering flight for a long time. More importantly, the wings of the conventional hovering flapping wing aircraft cannot realize effective deformation by utilizing a favorable structural form, so that the aerodynamic efficiency is poor and the lift force is low.
Disclosure of Invention
The invention aims to provide a hovering flapping wing aircraft wing with a bionic wing rib form and a bionic wing rib shape, and the hovering flapping wing aircraft wing overcomes the defects of poor aerodynamic efficiency and low lift force of the existing hovering flapping wing aircraft wing.
In order to achieve the purpose, the invention adopts the technical scheme that:
the invention provides a hovering flapping wing aircraft wing with bionic wing rib form and shape, which comprises a wing framework, wherein the wing framework comprises a main beam and wing ribs, and the number of the wing ribs is five, namely a first wing rib, a second wing rib, a third wing rib, a fourth wing rib and a fifth wing rib; the front edges of the first rib and the second rib are in point contact and are fixed on the main beam; the front edge points of the third rib, the fourth rib and the fifth rib are sequentially arranged on the main beam and are distributed in a spread mode.
Preferably, a skin is attached to the wing skeleton.
Preferably, the width of the main beam is 1 mm.
Preferably, the five ribs are each 0.5mm thick.
Preferably, the first rib is a straight-line segment structure and is perpendicular to the main beam.
Preferably, the first rib is located 17% to 20% from the spar end; the third wing rib is positioned 28% to 30% away from the end of the main beam; the fourth wing rib is positioned at a position 45% -50% away from the end part of the main beam; the fifth rib is located 58% to 60% from the spar end.
Preferably, the length of the first rib is 28% to 30% of the length of the main beam; the length of the second rib is 41 to 43 percent of the length of the main beam; the length of the third rib is 57 to 59 percent of the length of the main beam; the length of the fourth rib is 56% to 58% of the length of the main beam; the length of the fifth rib is 52% to 54% of the length of the main beam.
Preferably, the skin is of a circular arc-shaped structure at the wing tip between the end of the main beam and the end of the third rib, and the shape of the trailing edge of the end of the third rib and the end of the first rib is of a quadratic curve shape.
Preferably, the wing aspect ratio is four.
Preferably, the maximum chord length of the wing is at a position of 60% to 70% of the main beam.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a hovering flapping wing aircraft wing with a bionic wing rib form and a bionic wing rib shape, which can generate hovering lift force by utilizing the flexible deformation of the wing rib when the flapping wing aircraft wing hovers and flaps; when the flapping wings flap, the spanwise bending deformation and the chordwise torsion deformation are formed at the same time, but the overlarge spanwise bending deformation and chordwise torsion deformation are not beneficial to generating lift force. The wing ribs with the gradually increased curvature radius in the spanwise direction are arranged, spanwise rigidity and chordwise rigidity can be kept at the same time, the spanwise rigidity is increased by the wing ribs with the larger curvature radius at the wing tips, and overlarge bending deformation in the spanwise direction is avoided. Gradually approaching the trailing edge of the wing, the wing ribs are distributed in the chordwise direction, the chordwise rigidity is increased, and the lift loss caused by excessive deformation is avoided. Through the wing rib form for simultaneously maintaining the spanwise direction and the chordwise rigidity, the whole wing surface keeps a constant 45-degree torsion angle capable of obtaining the optimal lift force in the hovering flapping process, and simultaneously, a larger dimensionless area secondary moment is combined to generate the optimal hovering lift force.
Drawings
FIG. 1 is a schematic view of an embodiment;
FIG. 2 is a schematic view of an embodiment;
in the figure: 1. the first rib 2, the second rib 3, the third rib 4, the fourth rib 5, the fifth rib 6, the girder, 7 and the skin.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
The invention provides a wing of a hovering flapping wing aircraft with a bionic wing rib form and a bionic wing rib shape, which comprises a main beam 6, a wing rib and a skin 7, wherein a wing framework structure formed by the main beam and the wing rib is integrally cut by a carbon fiber plate with the thickness of 0.8mm to 1mm, and the width of the main beam is 1 mm.
The wing rib is provided with five, and the thickness of five wing ribs is 0.5 mm.
The front edge points of the five wing ribs are fixedly connected to the main beam, wherein the five wing ribs are a first wing rib 1, a second wing rib 2, a third wing rib 3, a fourth wing rib 4 and a fifth wing rib 5 respectively; the front edge points of the first rib 1 and the second rib 2 are in point contact, and the front edge points of the third rib 3, the fourth rib 4 and the fifth rib 5 are sequentially arranged on the main beam and are distributed in a spread mode.
The first rib 1 is a straight line segment and is perpendicular to the main beam 6. And constructing a plane coordinate system formed by the first rib 1 and the girder 6 to describe the shape of the subsequent rib, wherein the origin is positioned at the intersection of the first rib 1 and the girder 6, the x axis is along the girder and points to the wing tip in the positive direction, and the y axis is along the first rib 1 and points to the trailing edge of the wing in the positive direction.
The second wing rib 2 is a circular arc-shaped structure with the radius of 50mm, and the circle center is positioned at the position of (-21, -45) mm.
One end of the second wing rib 2 is contacted with one end of the first wing rib 1 and is fixedly connected to the main beam 6.
The third wing rib 3 is in the shape of a circular arc with the radius of 80mm, and the circle center is positioned at the position of (-10, -80) mm. .
One end of the third rib 3 is fixedly connected to the main beam 6.
The fourth rib 4 is in the shape of a circular arc with the radius of 90mm, and the circle center is located at the position of (15-90) mm. .
One end of the fourth rib 4 is in contact with and fixedly connected with the main beam 6.
The fifth rib 5 is in the shape of a circular arc with the radius of 110mm, and the center of the circle is located at the position of (35-108) mm. .
One end of the fifth rib 5 is in contact with and fixedly connected with the main beam 6.
The first rib 1 is located 17% to 20% of the distance between the main beam 6 and the end of the main beam;
the third rib 3 is positioned at the position 28 to 30 percent of the distance from the end part of the main beam 6;
the fourth rib 4 is positioned at a position 45 to 50 percent away from the end part of the main beam 6;
the fifth rib 5 is located 58% to 60% of the distance from the end of the spar 6.
The length of the first rib 1 is 28% to 30% of the length of the main beam 6.
The length of the second rib 2 is 41% to 43% of the length of the main beam 6.
The length of the third rib 3 is 57% to 59% of the length of the main beam 6.
The length of the fourth rib 4 is 56% to 58% of the length of the main beam 6.
The length of the fifth rib 5 is 52% to 54% of the length of the main beam 6.
The main beam 6 and the wing ribs form a wing structural framework, and a skin 7 is attached to the structural framework to form a complete wing.
The skin 7 is made of a flexible polyester film and is fixed at the contact part of the skin 7 and the main beam 6 and the wing ribs by bonding, the covered area of the skin 7 is the area formed by the wing ribs and the main beam 6, the skin 7 is in an arc shape at the wing tip and is connected with the end part of the main beam 6 and the end part of the third wing rib 3 in the arc shape, the end part of the third wing rib 3 and the end part of the first wing rib 1 are in a secondary curve shape, and the shape of the trailing edge is farthest from the main beam 6 at the end part of the third wing rib 3, so that the chord length of the wing has the maximum value at the position of 60-70% of the main beam; the wing aspect ratio is 4.
The maximum chord length is arranged at the position of 60 to 70 percent of the main beam, so that the dimensionless area second moment R of the wing2Is 0.6, R2Can be expressed as shown in formula (1), and research shows that R is smaller than R2，R2At 0.6, the wings can obtain larger lift when hovering and flapping:
Figure BDA0003393743690000041
in the formula, S is the wing area, R is the length of the main beam, R is the distance between the wing strip infinitesimal and the end part of the main beam, and c is the corresponding local chord length at R.
Through the embodiment, when the wings of the flapping wing aircraft flap in a hovering mode, the flexible deformation of the wing ribs is utilized to generate the hovering lift force. When the flapping wings flap, the spanwise bending deformation and the chordwise torsion deformation are formed at the same time, but the overlarge spanwise bending deformation and chordwise torsion deformation are not beneficial to generating lift force. The wing ribs with the gradually increased curvature radius in the spanwise direction are arranged, spanwise rigidity and chordwise rigidity can be kept at the same time, the spanwise rigidity is increased by the wing ribs with the larger curvature radius at the wing tips, and overlarge bending deformation in the spanwise direction is avoided. Gradually approaching the trailing edge of the wing, the wing ribs are distributed in the chordwise direction, the chordwise rigidity is increased, and the lift loss caused by excessive deformation is avoided. Through the wing rib form for simultaneously maintaining the spanwise direction and the chordwise rigidity, the whole wing surface keeps a constant 45-degree torsion angle capable of obtaining the optimal lift force in the hovering flapping process, and simultaneously, a larger dimensionless area secondary moment is combined to generate the optimal hovering lift force.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and improvements can be made without departing from the principle of the present invention, and such modifications and improvements should also be considered within the scope of the present invention.

Claims (9)

1. The hovering flapping wing aircraft wing with the bionic wing rib form and the bionic wing rib shape is characterized by comprising a wing framework, wherein the wing framework comprises a main beam (6) and wing ribs, and the number of the wing ribs is five, namely a first wing rib (1), a second wing rib (2), a third wing rib (3), a fourth wing rib (4) and a fifth wing rib (5); the front edges of the first rib (1) and the second rib (2) are in point contact and are fixed on the main beam; the front edge points of the third rib (3), the fourth rib (4) and the fifth rib (5) are sequentially arranged on the main beam and are distributed in a dispersed manner in the spanwise direction.
2. The wing of a hovering ornithopter according to claim 1, characterised in that the wing skeleton is fitted with a skin (7).
3. The wing of a hover ornithopter having a biomimetic rib formation and profile of claim 1 wherein the width of the main beam is 1 mm.
4. The wing of a hovering ornithopter according to claim 1, having a bionic rib form and profile, wherein the five ribs are each 0.5mm thick.
5. The wing of a hovering ornithopter according to claim 1, having a bionic rib form and profile, characterized in that the first rib (1) is a straight line segment structure and perpendicular to the main beam (6).
6. The wing of a hover ornithopter with bionic rib form and profile according to claim 1, characterized by the first rib (1) being located 17% to 20% from the end of the main beam; the third rib (3) is located 28% to 30% away from the end of the main beam; the fourth rib (4) is positioned at a position which is 45 to 50 percent away from the end part of the main beam; the fifth rib (5) is located 58% to 60% from the spar end.
7. The wing of the hovering ornithopter according to claim 1, having a bionic rib form and shape, wherein the length of the first rib (1) is 28% to 30% of the length of the main beam (6); the length of the second wing rib (2) is 41 to 43 percent of the length of the main beam (6); the length of the third rib (3) is 57 to 59 percent of the length of the main beam (6); the length of the fourth rib (4) is 56-58% of the length of the main beam (6); the length of the fifth rib (5) is 52 to 54 percent of the length of the main beam (6).
8. The wing of a hovering ornithopter with bionic rib form and profile according to claim 1, characterized in that the skin (7) is a circular arc shaped structure at the tip from between the end of the main beam (6) and the end of the third rib (3), and the shape of the trailing edge of the end of the third rib (3) and the end of the first rib (1) is a conic profile.
9. The wing of a hovering ornithopter according to claim 1, having a bionic rib form and profile, wherein the maximum chord length of the wing is located at 60% to 70% of the main beam.
CN202111476664.1A 2021-12-02 2021-12-02 Flapping wing aircraft wing capable of hovering and having bionic wing rib form and shape Pending CN113998104A (en)

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Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070138339A1 (en) * 2003-06-18 2007-06-21 Sinclair Peter L Motion assisting apparatus for flying objects
US20110278391A1 (en) * 2010-05-17 2011-11-17 Kotler Andrey Dragonfly unmanned aerial vehicle
US20140073216A1 (en) * 2010-07-05 2014-03-13 Edwin VAN RUYMBEKE Flying toy configured to move by wing flapping
KR20170040421A (en) * 2015-10-02 2017-04-13 건국대학교 산학협력단 Insect-like tailless flapping-wing micro air vehicle
CN107021223A (en) * 2017-05-17 2017-08-08 潘胜利 A kind of imitative birds multiple degrees of freedom flapping wing aircraft
CN110171567A (en) * 2019-05-14 2019-08-27 吉林大学 A kind of passive torsion swipe three-freedom miniature flapping wing aircraft
WO2019235972A1 (en) * 2018-06-07 2019-12-12 Malykh Alexander Iurevich Flying machine with flapping wings
KR102134474B1 (en) * 2019-04-11 2020-07-14 건국대학교 산학협력단 Insect-like tailless flying robot based on change of flapping-wing plane angle
US20200324892A1 (en) * 2017-12-20 2020-10-15 The Texas A&M University System Hover-Capable Flapping-Wing Aircraft
CN112278270A (en) * 2020-11-06 2021-01-29 南京航空航天大学 Two-degree-of-freedom flexible flapping wing aircraft based on dressing flexible hinge

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070138339A1 (en) * 2003-06-18 2007-06-21 Sinclair Peter L Motion assisting apparatus for flying objects
US20110278391A1 (en) * 2010-05-17 2011-11-17 Kotler Andrey Dragonfly unmanned aerial vehicle
US20140073216A1 (en) * 2010-07-05 2014-03-13 Edwin VAN RUYMBEKE Flying toy configured to move by wing flapping
KR20170040421A (en) * 2015-10-02 2017-04-13 건국대학교 산학협력단 Insect-like tailless flapping-wing micro air vehicle
CN107021223A (en) * 2017-05-17 2017-08-08 潘胜利 A kind of imitative birds multiple degrees of freedom flapping wing aircraft
US20200324892A1 (en) * 2017-12-20 2020-10-15 The Texas A&M University System Hover-Capable Flapping-Wing Aircraft
WO2019235972A1 (en) * 2018-06-07 2019-12-12 Malykh Alexander Iurevich Flying machine with flapping wings
KR102134474B1 (en) * 2019-04-11 2020-07-14 건국대학교 산학협력단 Insect-like tailless flying robot based on change of flapping-wing plane angle
CN110171567A (en) * 2019-05-14 2019-08-27 吉林大学 A kind of passive torsion swipe three-freedom miniature flapping wing aircraft
CN112278270A (en) * 2020-11-06 2021-01-29 南京航空航天大学 Two-degree-of-freedom flexible flapping wing aircraft based on dressing flexible hinge

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