CN112340016B - Wing rib structure, wing structure and flapping wing type aircraft - Google Patents

Abstract

The wing rib structure comprises a plurality of wing rib units, adjacent wing rib units are connected through wing section control units and wing rib outer edge connecting pieces, each wing rib unit comprises a plurality of wing rib edge pieces and wing connecting rod connecting pieces which are connected with each other, and the wing connecting rod connecting pieces in each wing rib unit are correspondingly connected with a wing connecting rod group of the aircraft. The wing rib structure has the characteristics of wide-range wing profile variability in chord length and curvature, the movement of the wing rib structure is driven by the movement of the wing connecting rod group, the wing structure has the capabilities of wing profile variability and wide-range pitch angle variability, wide-range swinging along the vertical direction of the plane of the main body of the aircraft and wide-range swinging along the longitudinal direction of the main body of the aircraft, the wing rib structure can be adjusted according to a complex flow field or environment, the movement speed and the movement efficiency are greatly improved, and high maneuvering action can be realized.

Description

Wing rib structure, wing structure and flapping wing type aircraft

Technical Field

The disclosure relates to the field of navigation devices, in particular to a wing rib structure, a wing structure and an ornithopter type aircraft.

Background

In the prior art, most aircrafts adopt a fixed wing structure or a relatively limited variable wing (morphing) structure, so that the adjustment cannot be carried out according to actual sailing or flying environments or complex flow fields, the sailing or flying efficiency is poor, the stability is poor, and high maneuvering action cannot be realized.

Disclosure of Invention

An object of the embodiment of the present disclosure is to provide an aircraft and a wing structure for the aircraft, so as to solve the problems in the prior art that adjustment cannot be performed for an actual navigation or flight environment or a complex flow field, the navigation or flight efficiency is poor, the stability is poor, and high maneuvering operation cannot be realized.

In order to solve the technical problem, the embodiment of the present disclosure adopts the following technical solutions: a rib structure for a vehicle comprises a plurality of rib units, wherein adjacent rib units are connected through an airfoil control unit and a rib outer edge connecting piece, each rib unit comprises a plurality of rib edge pieces and wing connecting rod connecting pieces which are connected with each other, and the wing connecting rod connecting pieces in each rib unit are correspondingly connected with a wing connecting rod group of the vehicle.

In some embodiments, the plurality of rib elements comprises a rib leading edge element and a rib trailing edge element, at least one rib mid-element being disposed between the rib leading edge element and the rib trailing edge element.

In some embodiments, the rib leading edge unit comprises a rib leading edge arc, a first rib edge, an eighth rib edge, and a wing leading edge link, wherein two ends of the rib leading edge arc are connected to one end of the first rib edge and the eighth rib edge by a first rotational bearing and a sixth rotational bearing, the other end of the first rib edge and the eighth rib edge are connected to the rib middle unit by a rib outer edge link, the first rotational bearing and the sixth rotational bearing are connected by a first rib unit support, and the first rib unit support passes through and is connected to the wing leading edge link.

In some embodiments, the rib trailing edge unit comprises a rib trailing edge wedge, a fourth rib edge piece, a fifth rib edge piece, and a wing trailing edge link connector, wherein two ends of the rib trailing edge wedge are connected to one end of the fourth rib edge piece and the fifth rib edge piece by a third rotational bearing and a fourth rotational bearing, the other end of the fourth rib edge piece and the fifth rib edge piece are connected to the rib center unit by a rib outer edge connector, the third rotational bearing and the fourth rotational bearing are connected by a third rib unit support, and the third rib unit support passes through and is connected to the wing trailing edge link connector.

In some embodiments, the rib center unit comprises a second rib edge piece, a third rib edge piece, a sixth rib edge piece, a seventh rib edge piece, and a wing center link connector, the first end of the second rib edge piece and the first end of the third rib edge piece are connected by a second pivot bearing, the first end of the sixth rib edge piece and the first end of the seventh rib edge piece are connected by a fifth pivot bearing, the second pivot bearing and the fifth pivot bearing are connected by a second rib unit support, the second rib unit support passes through and is connected with the wing center link connector.

In some embodiments, the rib edge members of adjacent rib units are connected by the rib rim connectors, the rib rim connectors comprising flexible connectors and sliding covers, the flexible connectors telescopically connecting adjacent rib edge members, one end of the sliding cover being fixedly connected to the end of one of the rib edge members, and the other end of the sliding cover being slidably connected to the end of the other adjacent rib edge member.

In some embodiments, the wing control unit includes a slip ring link, a slip ring, and a slide bar, one end of the slip ring link is connected to a side of the first wing link connector of the first wing rib unit, the other end of the slip ring link is connected to the slip ring, the slide bar is disposed at a side of the second wing link connector of the second wing rib unit adjacent to the first wing rib unit and extends toward a direction of the first wing link connector, and the slide ring is sleeved on the slide bar and can slide back and forth along the slide bar.

In some embodiments, a slide rod base is disposed on the top of the slide rod, two slide rod base hinged supports are disposed on the first side and the second side of the slide rod base, and each slide rod base hinged support is connected with a corresponding slide ring hinged support on the slide ring through a connecting rod group.

In some embodiments, the linkage comprises a front rod and a rear rod connected to each other on the first side or the second side of the slide bar base, a first end of the front rod being connected to the corresponding slide bar base hinge support, a second end of the front rod being connected to the corresponding rib edge member via one hinge support, a middle portion of the front rod being connected to a first end of the rear rod via another hinge support, and a second end of the rear rod being connected to the corresponding slide ring hinge support on the slide ring.

The embodiment of the present disclosure further provides a wing structure, which includes the rib structure described in any one of the above technical solutions.

The embodiment of the disclosure also provides an aircraft structure, which adopts the wing structure in the technical scheme.

The wing structure has the characteristics of a wing with a variable wing profile, a variable pitching angle, a large-range vertical swinging capacity along the plane of the main body of the aircraft and a large-range longitudinal swinging capacity along the main body of the aircraft, can be adjusted according to a complex flow field or environment, greatly improves the movement speed and the movement efficiency, and can realize high maneuvering action.

Drawings

FIG. 1 is a schematic structural view of an airfoil configuration having a three multi-linkage configuration in accordance with an embodiment of the present disclosure;

FIG. 2 is a cross-sectional view of a rib structure provided by an embodiment of the present disclosure;

FIG. 3 is a schematic perspective view of a rib structure provided in an embodiment of the present disclosure;

FIG. 4 is a schematic view of a rib structure attachment provided by an embodiment of the present disclosure;

FIG. 5 is a schematic structural view of an airfoil control unit in a rib structure according to an embodiment of the disclosure;

FIG. 6 is a schematic structural view of an airfoil control unit in a rib structure according to an embodiment of the disclosure;

FIG. 7 is a schematic structural view of an airfoil control unit in a rib structure according to an embodiment of the disclosure;

FIG. 8 is a schematic view of the connection of an airfoil control unit in a rib structure according to an embodiment of the disclosure;

FIG. 9 is a schematic view of the connection of an airfoil control unit in a rib structure according to an embodiment of the disclosure;

FIG. 10 is a schematic view of the connection of an airfoil control unit in a rib structure according to an embodiment of the disclosure;

FIG. 11 is a schematic view of a change in attitude of a rib structure according to an embodiment of the disclosure;

FIG. 12 is a schematic view of a change in attitude of a rib structure according to an embodiment of the disclosure;

FIG. 13 is a schematic view of a change in attitude of a rib structure according to an embodiment of the disclosure;

FIG. 14 is a schematic view of a change in attitude of a rib structure according to an embodiment of the disclosure;

FIG. 15 is a schematic view of a change in attitude of a rib structure according to an embodiment of the disclosure;

FIG. 16 is a schematic view of a change in attitude of a rib structure according to an embodiment of the disclosure;

FIG. 17 is a schematic view of a change in attitude of a rib structure according to an embodiment of the disclosure;

fig. 18 is a schematic view of a change in attitude of a rib structure according to an embodiment of the present disclosure.

Reference numerals:

100-wing leading edge link; 200-wing middle link; 300-wing trailing edge link; 400-rib outer frame; 110-wing leading edge link connection; 210-wing mid-link connection; 310-wing trailing edge link connection; 500-a first airfoil control unit; 600-a second wing control unit;

1-rib leading edge arc; 2-a first rib edge piece; 3-a first rib outer edge connector; 4-a second rib edge piece; 5-a third rib edge piece; 6-second rib outer edge connectors; 7-a fourth rib edge piece; 8-rib trailing edge wedges; 9-a fifth rib edge piece; 10-third rib outer edge connector; 11-a sixth rib edge piece; 12-a seventh rib edge piece; 13-a fourth rib outer edge connector; 14-an eighth rib edge piece; 15-a first rotating bearing; 16-a second rotational bearing; 17-a third rotational bearing; 18-a fourth rotational bearing; 19-a fifth rotational bearing; 20-a sixth rotational bearing; 21-a first rib element support; 22-a second rib cell support; 23-a third rib element support; 24-a first slip ring link; 25-a first slip ring; 26-a first slide bar; 27-a first straight bar; 28-a first U-shaped bar; 29-a first slide bar base; 30-a first slide bar base hinge support; 31-a second slide bar base hinged support; 32-a third slide bar base hinged support; 33-a fourth slide bar base hinge support; 34-a first set of levers; 35-a second set of levers; 36-a third lever set; 37-a fourth lever set; 38-first slip ring hinge support; 39-second slip ring hinge support; 40-a third slip ring hinge support; 41-fourth slip ring hinged support; 42-a first rod; 43-a second rod; 44-a first hinge support; 45-a second hinged support; 46-a third rod; 47-fourth bar; 48-third hinge support; 49-fourth hinge support; 50-a fifth bar; 51-sixth rod; 52-fifth hinge support; 53-sixth hinge support; 54-a seventh rod; 55-eighth bar; 56-seventh hinged support; 57-eighth hinge support.

Detailed Description

Various aspects and features of the disclosure are described herein with reference to the drawings.

It will be understood that various modifications may be made to the embodiments of the present application. Accordingly, the foregoing description should not be construed as limiting, but merely as exemplifications of embodiments. Other modifications within the scope and spirit of the present disclosure will occur to those skilled in the art.

The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate embodiments of the disclosure and, together with a general description of the disclosure given above, and the detailed description of the embodiments given below, serve to explain the principles of the disclosure.

These and other characteristics of the present disclosure will become apparent from the following description of preferred forms of embodiment, given as non-limiting examples, with reference to the attached drawings.

It should also be understood that, although the present disclosure has been described with reference to some specific examples, a person of skill in the art shall certainly be able to achieve many other equivalent forms of the disclosure, having the characteristics as set forth in the claims and hence all coming within the field of protection defined thereby.

The above and other aspects, features and advantages of the present disclosure will become more apparent in view of the following detailed description when taken in conjunction with the accompanying drawings.

Specific embodiments of the present disclosure are described hereinafter with reference to the accompanying drawings; however, it is to be understood that the disclosed embodiments are merely exemplary of the disclosure that may be embodied in various forms. Well-known and/or repeated functions and structures have not been described in detail so as not to obscure the present disclosure with unnecessary or unnecessary detail. Therefore, specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present disclosure in virtually any appropriately detailed structure.

The specification may use the phrases "in one embodiment," "in another embodiment," "in yet another embodiment," or "in other embodiments," which may each refer to one or more of the same or different embodiments in accordance with the disclosure.

Embodiments of the present disclosure provide a wing rib structure, a wing structure, and an ornithopter-type aircraft.

The wing structure here is composed of the rib structure, the wing structure is installed on the flapping wing type aircraft, the flapping wing type aircraft here can realize navigation or flight, gliding and other high maneuvering actions based on the swinging and other movements of the wing structure in the air or in the water, the structure of the flapping wing type aircraft here can be a bionic structure similar to a bionic bird, a bionic fish and the like, and can also be a structure of an airplane type double-wing aircraft and the like, and the specific structure of the aircraft is not limited in the disclosure.

The wing structure herein may also be referred to as "flapping wing" and may be arranged at any position on the body of the aircraft, for example, at the side of the body of the aircraft, at a single side, or at two symmetrical sides of the body of the aircraft, and the disclosure is not limited to the position of the wing structure.

The wing structure related to the embodiments of the present disclosure may connect the rib structures of the embodiments of the present disclosure through a multi-link structure to achieve the distortion of the wing structure. Different wing structure forms can be realized according to the number of the rib units and the wing profile control units adopted in each rib structure, so that different swing postures and swing degrees are realized.

In particular, the wing structure according to embodiments of the disclosure comprises at least one multi-link structure, which is arranged extending from the body of the aircraft in the direction of the wing tip, between which a rib structure according to embodiments of the disclosure is arranged. In the following embodiments of the present disclosure, the wing structure includes three multi-link-group structures as an example, but not as a limitation of the number. As shown in fig. 1, in the wing structure according to the embodiment of the present disclosure, three multi-link structures are sequentially arranged in a wing leading edge portion, a wing middle portion, and a wing trailing edge portion, which extend from a main body of the aircraft to a wing tip direction, and a wing leading edge multi-link structure a, a wing middle multi-link structure b, and a wing trailing edge multi-link structure c, which are sequentially arranged from a head to a tail of the main body of the aircraft and have sequentially reduced total lengths, are connected to a support frame d on the main body of the aircraft, and the multi-link structures a, b, and c are driven to rotate by motors at corresponding joints thereof, and the directions of the motors relative rotation are not limited. The rib structure, the wing structure and the aircraft are described in detail below with reference to specific embodiments:

a first aspect of the embodiments of the present disclosure provides a multi-dimensional deformable wing rib structure, each of the wing rib structures is sequentially sleeved on a wing leading edge multi-link structure, a wing middle multi-link structure, and a wing trailing edge multi-link structure to form the wing structure, as shown in fig. 2, the wing structure includes a wing leading edge link 100, a wing middle link 200, and a wing trailing edge link 300, which are sequentially arranged, where an extending direction of the wing leading edge link 100, the wing middle link 200, and the wing trailing edge link 300 is defined as a first direction, where the wing leading edge link 100, the wing middle link 200, and the wing trailing edge link 300 are respectively link portions on the leading edge multi-link structure, the middle multi-link structure, and the trailing edge multi-link structure. Each rib structure is sleeved on the wing leading edge connecting rod 100, the wing middle connecting rod 200 and the wing trailing edge connecting rod 300 along a second direction, and the second direction can be perpendicular to the first direction; the motion of the leading edge link 100, the middle link 200 and the trailing edge link 300 driven by a driving device (e.g. a motor) can drive the motion of the rib structure, so as to drive the overall motion of the wing structure.

Each rib structure related to the embodiment of the present disclosure includes a plurality of rib units, adjacent rib units are connected by the wing profile control unit and a rib outer edge connector, each rib unit includes a plurality of rib edge members and wing link connectors, the wing link connector in each rib unit is connected to the wing link group of the aircraft, different wing links of the aircraft can swing up and down, left and right, and the like relatively, that is, relative position changes occur, where the wing link group is the wing leading edge link 100, the wing middle link 200, or the wing trailing edge link 300; in each rib structure, the rib edge piece and the rib skirt connector form a rib outer frame 400 of the rib structure.

In the disclosed embodiment, the rib structure comprises a rib leading edge unit and a rib trailing edge unit, and in some embodiments, at least one rib middle unit may be disposed between the rib leading edge unit and the rib trailing edge unit, wherein the number of the rib middle units may be one or more, and the number of the rib middle units is set according to the overall length of the rib structure, the deformation requirement of the rib structure, and the like. In the disclosed embodiment, the number of rib center cells is one. The rib leading edge unit, the rib middle unit and the rib trailing edge unit are respectively connected with the wing leading edge link 100, the wing middle link 200 and the wing trailing edge link 300. Further, as shown in fig. 2, the rib leading edge unit and the rib middle unit are connected by a first wing profile control unit 500, and the rib middle unit and the rib trailing edge unit are connected by a second wing profile control unit 600.

Specifically, referring to fig. 3 in combination with fig. 2, fig. 3 shows a schematic structural diagram of the rib structure, the rib leading edge unit is located at the leading edge of the rib unit, and includes a rib leading edge arc 1, a first rib edge 2, an eighth rib edge 14, and a wing leading edge link connector 110, the first end of the first rib edge 2 and the first end of the eighth rib edge 14 are respectively connected with the first end and the second end of the rib leading edge arc 1 and are respectively located at the upper side and the lower side of the rib leading edge unit, which can realize passive deformation; the second end of the first rib edge 2 and the second end of the eighth rib edge 14 are connected to a first rotary bearing 15 and a sixth rotary bearing 20, respectively, the first rotary bearing 15 and the sixth rotary bearing 20 are connected by a first rib element support 21, the first rib element support 21 passes through and is connected to the leading edge link connection 110, wherein the first rotary bearing 15 and the sixth rotary bearing 20 are slidable on the first rib element support 21.

The rib central unit is located at the central position of the rib unit and comprises a second rib edge piece 4, a third rib edge piece 5, a sixth rib edge piece 11, a seventh rib edge piece 12 and a wing central link connector 210, wherein the second rib edge piece 4 and the third rib edge piece 5 are located at the upper side of the rib central unit, the sixth rib edge piece 11 and the seventh rib edge piece 12 are located at the lower side of the rib central unit, and the rib edge pieces can realize passive deformation; the first end of the second rib edge 4 and the first end of the third rib edge 5 are connected by a second rotary bearing 16, the sixth rib edge 11 and the seventh rib edge 12 are connected by a fifth rotary bearing 19, the second rotary bearing 16 and the fifth rotary bearing 19 are connected by a second rib unit support 22, and the second rib unit support 22 passes through and is connected with the wing middle link connector 210; wherein fig. 4 exemplarily shows that the first end of the second rib edge piece 4 is connected with the first end of the third rib edge piece 5 through the second rotational bearing 16, and this connection structure is applicable to other rotational bearings; the second and fifth rotational bearings 16, 19 are slidable on the second finunit support 22. In some embodiments, the second rib edge 4, the third rib edge 5, the sixth rib edge 11 and the seventh rib edge 12 may also be replaced by rigid links.

The wing rib trailing edge unit is located at the trailing edge position of the wing rib unit and comprises a wing rib trailing edge wedge 8, a fourth wing rib edge piece 7, a fifth wing rib edge piece 9 and a wing trailing edge connecting rod connector 310, wherein the first ends of the fourth wing rib edge piece 7 and the fifth wing rib edge piece 9 are respectively connected with the first end and the second end of the wing rib trailing edge wedge 8 and are respectively located at the upper side and the lower side of the wing rib trailing edge unit, and passive deformation can be realized; the second end of the fourth rib edge 7 and the second end of the fifth rib edge 9 are connected to a third rotary bearing 17 and a fourth rotary bearing 18, respectively, the third rotary bearing 17 and the fourth rotary bearing 18 are connected by a third rib unit support 23, the third rib unit support 23 passes through and is connected to the wing trailing edge link connector 310, wherein the third rotary bearing 17 and the fourth rotary bearing 18 can slide on the third rib unit support 23.

Further, the leading edge link connector 110, the middle link connector 210 and the trailing edge link connector 310 are respectively disposed on the leading edge link 100, the middle link 200 and the trailing edge link 300.

As described above, the wing rib units are connected with each other through the wing profile control unit, specifically, the wing leading edge link connector 110, the wing middle link connector 210 and the wing trailing edge link connector 310 are connected with each other through the wing profile control unit, specifically, the wing leading edge link connector 110 and the wing middle link connector 210 are connected with each other through the first wing profile control unit 500, and the wing middle link connector 210 and the wing trailing edge link connector 310 are connected with each other through the second wing profile control unit 600. Considering that the movement of the leading edge link 100, the middle link 200 and the trailing edge link 300 driven by a driving device (e.g. a motor) can drive the whole rib structure to move, the leading edge link connector 110, the middle link connector 210 and the trailing edge link connector 310 may be, for example, a rotor of the motor or a shaft sleeve, so that an active driving movement or a passive movement can be realized, and the specific selection is determined based on the requirements and positions of the aircraft, which is not limited herein.

Further, as described above, the rib edge members of different rib units are connected to each other by the rib outer edge connecting members, and in the embodiment of the present disclosure, the rib leading edge unit and the rib middle unit are connected to each other by the first rib outer edge connecting member 3 and the fourth rib outer edge connecting member 13 at upper and lower sides, and the rib middle unit and the rib trailing edge unit are connected to each other by the second rib outer edge connecting member 6 and the third rib outer edge connecting member 10 at upper and lower sides. Wherein, on one side of the rib structure, the first rib peripheral connection 3 comprises a first flexible connection 301 and a first sliding cover 302, which first flexible connection 301 and first sliding cover 302 are arranged between the end faces of the first rib edge piece 2 of the rib leading edge unit and the second rib edge piece 4 of the rib mid-unit; the second rib skirt connector 6 comprises a second flexible connector 601 and a second sliding cover 602, which flexible connector 601 and sliding cover 602 are arranged between the end faces of the third rib edge piece 5 and the fourth rib edge piece 7 of the rib central unit. On the other side of the rib structure, the third rib peripheral connection 10 comprises a third flexible connection 1001 and a third sliding cover 1002, which third flexible connection 1001 and third sliding cover 1002 are arranged between the end faces of the fifth rib edge piece 9 of the rib trailing edge unit and the sixth rib edge piece 11 of the rib mid-unit; the fourth rib skirt connector 13 comprises a fourth flexible connector 1301 and a fourth sliding flap 1302, the fourth flexible connector 1301 and the fourth sliding flap 1302 being arranged between the seventh rib edge piece 12 of the rib centre unit and the end face of the eighth rib edge piece 14 of the rib leading edge unit.

As mentioned above, the rib leading edge unit and the rib middle unit are connected by the first airfoil control unit 500, specifically, the wing leading edge link connector 110 and the wing middle link connector 210 are connected by the first airfoil control unit 500, as shown in fig. 5-7, wherein fig. 5 shows the three-dimensional structure of the first airfoil control unit 500 and the connection relationship between the first airfoil control unit 500 and the wing leading edge link connector 110 and the wing middle link connector 210, fig. 6 and 7 further show the structure of the first airfoil control unit 500 and the connection relationship between the first airfoil control unit 500 and the wing leading edge link connector 110 and the wing middle link connector 210 from two sides respectively,

the first airfoil control unit 500 includes a first slip ring connecting rod 24, a first slip ring 25 and a first sliding rod 26, specifically, one end of the first slip ring connecting rod 24 is connected to a side surface of the wing leading edge connecting rod connecting member 110 opposite to the wing middle connecting rod connecting member 210, the other end of the first slip ring connecting rod 24 is connected to the first slip ring 25, the first sliding rod 26 is disposed on the side surface of the wing middle connecting rod connecting member 210 opposite to the wing leading edge connecting rod connecting member 110, and the first slip ring 25 is sleeved on the first sliding rod 26 and can slide back and forth along the first sliding rod 26.

Specifically, the first slip ring link 24 includes a first straight rod 27 and a first U-shaped rod 28, one end of the first straight rod 27 is connected to a side surface of the wing leading edge link connector 110, as shown in fig. 8, the first straight rod 27 and the wing leading edge link connector 110 may be connected in a ball hinge manner, the other end of the first straight rod 27 is connected to a bottom edge of the first U-shaped rod 28, two long edges of the first U-shaped rod 28 are respectively connected to the first slip ring 25, and the first slide rod 26 passes through a middle portion of the first slip ring 25 and is located between the two long edges.

Further, a first slide bar base 29 is arranged on the top of the first slide bar 26, the first slide bar base 29 is limited in an annular area enclosed by the first U-shaped bar 28 and the first slide ring 25, a first slide bar base hinge support 30 and a second slide bar base hinge support 31 are arranged side by side on the upper side of the first slide bar base 29, and correspondingly, a third slide bar base hinge support 32 and a fourth slide bar base hinge support 33 are arranged side by side on the lower side of the first slide bar base 29, wherein the first slide bar base hinge support 30 is connected with one end of a first lever set 34, the other end of the first lever set 34 is connected with the first slide ring 25, the second slide bar base hinge support 31 is connected with one end of a second lever set 35, the other end of the second lever set 35 is connected with the first slide ring 25, and the third slide bar base hinge support 32 is connected with one end of a third lever set 36, the other end of the third lever set 36 is connected to the first slip ring 25, the fourth sliding rod base hinged support 33 is connected to one end of a fourth lever set 37, and the other end of the fourth lever set 37 is connected to the first slip ring 25. In this way, the first slide rod base 29 is rotatably connected to the first slide ring 25 by four linkages.

Further, a first slip ring hinge support 38 and a second slip ring hinge support 39 are disposed at an end portion of the first slip ring 25 on a first side, the other end of the first lever set 34 is rotatably connected to the first slip ring hinge support 38 of the first slip ring 25, the other end of the second lever set 35 is rotatably connected to the second slip ring hinge support 39 of the first slip ring 25, a third slip ring hinge support 40 and a fourth slip ring hinge support 41 are disposed at an end portion of the first slip ring 25 on a second side, the other end of the third lever set 36 is rotatably connected to the third slip ring hinge support 40 of the first slip ring 25, and the other end of the fourth lever set 37 is rotatably connected to the fourth slip ring hinge support 41 of the first slip ring 25.

Specifically, the first lever set 34 includes a first lever 42 and a second lever 43, a first end of the first lever 42 is rotatably connected to the first slide rod-based hinge support 30, a second end and a middle of the first lever 42 are respectively provided with a first hinge support 44 and a second hinge support 45, wherein the second end of the first lever 42 is connected to the first rib edge 2 through the first hinge support 44, the first end of the second lever 43 is connected to the first lever 42 through the second hinge support 45, and the second end of the second lever 43 is rotatably connected to the first slip ring hinge support 38.

The second lever set 35 includes a third rod 46 and a fourth rod 47, a first end of the third rod 46 is rotatably connected to the second slide bar base hinge support 31, a third hinge support 48 and a fourth hinge support 49 are respectively disposed at a second end and a middle portion of the third rod 46, wherein the second end of the third rod 46 is connected to the second rib edge 4 through the third hinge support 48, a first end of the fourth rod 47 is connected to the third rod 46 through the fourth hinge support 49, and a second end of the fourth rod 47 is rotatably connected to the second slip ring hinge support 39.

The third lever set 36 includes a fifth rod 50 and a sixth rod 51, a first end of the fifth rod 50 is rotatably connected to the third sliding rod base hinge support 32, a fifth hinge support 52 and a sixth hinge support 53 are respectively disposed at a second end and a middle portion of the fifth rod 50, wherein the second end of the fifth rod 50 is connected to the eighth rib edge 14 through the fifth hinge support 52, a first end of the sixth rod 51 is connected to the fifth rod 50 through the sixth hinge support 53, and a second end of the sixth rod 51 is rotatably connected to the third sliding ring hinge support 40.

The fourth lever set 37 includes a seventh lever 54 and an eighth lever 55, a first end of the seventh lever 54 is rotatably connected to the fourth sliding rod base hinge support 33, a seventh hinge support 56 and an eighth hinge support 57 are respectively disposed at a second end and a middle portion of the seventh lever 54, wherein the second end of the seventh lever 54 is connected to the seventh rib edge 12 through the seventh hinge support 56, a first end of the eighth lever 55 is connected to the seventh lever 54 through the eighth hinge support 57, and a second end of the eighth lever 55 is rotatably connected to the fourth slip ring hinge support 41.

In this way, each lever set can form a rotational connection with the rib edge member in the rib outer frame 400 through the hinge support, thereby realizing the linkage relationship between the wing profile control unit and the rib outer frame 400. The following is a detailed description of the motion control of the first profile control unit 500 located at the front of the rib:

in the actual movement of the rib structure, as long as the relative position change between the wing leading edge link 100 and the wing middle link 200 occurs, whether swinging in the horizontal plane, swinging in the vertical plane, or combined movement in the horizontal and vertical planes, the first sliding rod 26 is caused to perform relative movement with respect to the first sliding ring 25; further, due to the linkage relationship between the wing profile control unit and the outer frame of the wing rib, the relative motion between the first slide bar 26 and the first slide ring 25 is transmitted to the first rod 42, the second rod 43, the third rod 46, the fourth rod 47, the fifth rod 50, the sixth rod 51, the seventh rod 54 and the eighth rod 55 through the first slide bar base hinge support 30, the second slide bar base hinge support 31, the third slide bar base hinge support 32, the fourth slide bar base hinge support 33, the first slide bar hinge support 38, the second slide bar hinge support 39, the third slide bar hinge support 40 and the fourth slide bar hinge support 41 which are fixedly connected to the first slide bar 25 and the first slide bar 26, respectively, wherein the linkage relationship between the first rod 42 and the second rod 43 is generated through the second hinge support 45, the third rod 46 and the fourth rod 47 are in linkage relationship through a fourth hinge support 49, the fifth rod 50 and the sixth rod 51 are in linkage relationship through a sixth hinge support 53, and the seventh rod 54 and the eighth rod 55 are in linkage relationship through an eighth hinge support 57; furthermore, as a result of the transmission of the relative movement of the first slide ring 25 and the first slide bar 26 to the first pivot bearing 44, the third pivot bearing 48, the fifth pivot bearing 52 and the seventh pivot bearing 56, the transmission of the relative movement of the first slide ring 25 and the first slide bar 26 to the first rib edge 2, the second rib edge 4, the seventh rib edge 12 and the eighth rib edge 14, which can be deformed passively, enables the first rib edge 2, the second rib edge 4, the seventh rib edge 12 and the eighth rib edge 14, which can be deformed passively, to follow the relative movement of the first slide ring 25 and the first slide bar 26.

Further, with the movement of the first rib edge 2, the second rib edge 4, the seventh rib edge 12 and the eighth rib edge 14, the first sealing flexible connector 301 and the fourth sealing flexible connector 1301, which form a flexible connection between the adjacent rib edges, will also generate a telescopic movement, wherein one end of the first sliding cover plate 302 is fixedly connected with the first rib edge 2, and the other end (moving end) is slidably connected with the second rib edge 4, with the relative movement of the first rib edge 2 and the second rib edge 4, the end of the first sliding cover plate 302 always tightly fits the second rib edge 4, and the fourth sliding cover plate 1302 has one end fixed on the eighth rib edge 14 and the other end as a moving end is slidably connected with the seventh rib edge 12, with the relative movement of the eighth rib edge 14 and the seventh rib edge 12, the moving end of the fourth sliding cover 1302 is always in close contact with the seventh rib edge 12.

In order to enable the first wing control unit 500 at the front of the wing rib to still achieve wing control capability under the complex deformation of the first wing rib edge 2, the second wing rib edge 4, the seventh wing rib edge 12 and the eighth wing rib edge 14, and to transmit the relative movement of the first sliding ring 25 and the first sliding rod 26, therefore, the first sliding ring connecting rod 24 and the wing leading edge connecting rod 110 are connected in a ball hinge manner, the first sliding rod 26 and the wing middle connecting rod 210 are connected in a ball hinge manner, further, as shown in fig. 9 as an example, the third hinge support 48 is connected with the second wing rib edge 4 through a rotation shaft 48a, and similarly, the first hinge support 44 is connected with the first wing rib edge 2 through a rotation shaft 44, and the fifth hinge support 52 is connected with the eighth wing rib edge 14 through a rotation shaft, the fourth pivot bearing 56 is connected to the seventh rib edge 12 by a pivot, so that the first sliding bar 26 can easily slide on the first sliding ring 25 under the deformation of the rib outer frame 400.

As mentioned above, the wing middle link connector 210 and the wing trailing edge link connector 310 are connected by the second wing control unit 600, as shown in fig. 10, fig. 10 shows the three-dimensional structure of the second wing control unit 600 and the connection relationship between the wing middle link connector 210 and the wing trailing edge link connector 310, the second wing control unit 600 has the same structure as the first wing control unit 500, and the disclosure will not be explained in too much.

Through the rib structure of the present embodiment, based on the adjustment of the wing profile control unit, for example, through the movement of the wing link set or the change of the relative position, the movement of the rib structure, that is, the deformation of various wing profiles, can be realized, so as to realize the basic action of plane wing profile transformation, where fig. 11 and 12 are schematic diagrams of wing profile attack angle change, and the sections of the rib structure where the wing leading edge link 100, the wing middle link 200, and the wing trailing edge link 300 are located are in the same straight line through the movement of the wing structure, so as to realize the downward motion shown in fig. 11 and the upward motion shown in fig. 12. Of course, as shown in fig. 13 and 14, the embodiment of the present disclosure can also implement a change of the wing rib structure, that is, a wing profile expansion deformation, for example, the wing rib structure is reduced by being driven by the two wing profile control units, for example, the distance between the wing leading edge link 100, the wing middle link 200, and the wing trailing edge link 300 is reduced by the relative movement between the first slip ring link 24 and the first sliding bar 26, so as to implement the wing profile reducing action shown in fig. 13, or the wing rib structure is increased by being driven by the two wing profile control units, that is, the distance between the wing leading edge link 100, the wing middle link 200, and the wing trailing edge link 300 is increased, so as to implement the wing profile increasing action shown in fig. 14. The disclosed embodiment can also realize the wing profile plane bending action, and fig. 15 and 16 are schematic diagrams of the wing profile plane bending action of the wing rib structure, wherein fig. 15 shows a schematic diagram of the wing rib structure bending upwards, and fig. 16 shows a schematic diagram of the wing rib structure bending downwards.

Of course, the above wing profile changing actions can realize the complex actions of plane wing profile transformation by combination: the transformation adopts the permutation and combination of the basic actions of the plane wing profile, belongs to the combined motion and realizes the complex transformation of the wing profile, and the disclosure is not excessively elaborated.

Through the wing rib structure of the embodiment, based on the adjustment of the wing profile control unit, various wing profile deformations can be realized, and the complex motions of space wing profile transformation can also be realized, such complex transformations can be based on the change of the attack angle of the basic motions of plane wing profile transformation, similar stretching compression deformation and plane bending, and the basic motions of wing rib side face distortion caused by the unparallel motions of the wing leading edge connecting rod 100, the wing middle connecting rod 200 and the wing trailing edge connecting rod 300 can be increased. Since the spatial wing profile transformation is difficult to describe in detail in a two-dimensional image, only the lateral distortion motion of the wing rib is supplemented, and the spatial wing profile complex transformation is based on the permutation and combination of four basic motions of attack angle change, similarity deformation, plane bending and lateral distortion. Figures 17 and 18 show schematic views of the two-sided twist of the rib structure side twist.

A second aspect of an embodiment of the present disclosure provides an airfoil structure comprising the rib structure of any of the embodiments described above. The wing structure here is composed of the rib structure, and it is disposed at any position on the aircraft main body, for example, it may be disposed at the side of the aircraft main body, it may be disposed at a single side, or it may be disposed at two symmetrical sides of the aircraft main body, and the disclosure is not limited to the position of the wing structure.

The wing structure in embodiments of the present disclosure includes at least one multi-link structure and the rib structure. In this way, the wing structure can be composed by a multi-link structure to achieve torsional deformation of the wing structure. Different wing structural forms can be realized according to the number of the multi-link structures adopted in the wing structure, so that different swinging postures and degrees are realized.

The wing structure in the embodiment of the disclosure has the characteristics of a wide-range variable wing, has the capability of changing the wing profile, the pitching angle and the pitching angle in a wide range, the capability of vertically swinging along the plane of the main body of the aircraft in a wide range and the capability of longitudinally swinging along the main body of the aircraft in a wide range, can be adjusted according to a complex flow field or environment, greatly improves the movement speed and the movement efficiency, and can realize high maneuvering action.

A third aspect of an embodiment of the disclosure provides an ornithopter-type vehicle comprising the wing structure of any of the embodiments described above. The flapping wing type aircraft can realize navigation, flying, gliding and other high maneuvering actions based on the swinging and other movements of the wing structure in the air or in water, the structure of the aircraft can be a bionic structure similar to a bionic bird, a bionic fish and the like, and can also be an airplane type double-wing aircraft and the like, and the specific structure of the aircraft is not limited by the disclosure.

The wing rib structure, the wing structure and the flapping wing type aircraft in the embodiment of the disclosure have the characteristics of wide-range variable wings in the chordwise direction and the spanwise direction, the wing structure has the capability of changing the wing profile, changing the pitch angle in a wide range, swinging the aircraft body in a wide range vertically along the plane of the aircraft body and swinging the aircraft body in a wide range longitudinally, and can be adjusted according to a complex flow field or environment, so that the movement speed and the movement efficiency are greatly improved, and high maneuvering actions can be realized.

Moreover, although exemplary embodiments have been described herein, the scope thereof includes any and all embodiments based on the disclosure with equivalent elements, modifications, omissions, combinations (e.g., of various embodiments across), adaptations or alterations. The elements of the claims are to be interpreted broadly based on the language employed in the claims and not limited to examples described in the present specification or during the prosecution of the application, which examples are to be construed as non-exclusive. It is intended, therefore, that the specification and examples be considered as exemplary only, with a true scope and spirit being indicated by the following claims and their full scope of equivalents.

The above description is intended to be illustrative and not restrictive. For example, the above-described examples (or one or more versions thereof) may be used in combination with each other. For example, other embodiments may be used by those of ordinary skill in the art upon reading the above description. In addition, in the foregoing detailed description, various features may be grouped together to streamline the disclosure. This should not be interpreted as an intention that a non-claimed disclosed feature is essential to any claim. Rather, the subject matter of the present disclosure may lie in less than all features of a particular disclosed embodiment. Thus, the following claims are hereby incorporated into the detailed description as examples or embodiments, with each claim standing on its own as a separate embodiment, and it is contemplated that these embodiments may be combined with each other in various combinations or permutations.

The scope of the disclosure should be determined with reference to the appended claims, along with the full scope of equivalents to which such claims are entitled. The above embodiments are merely exemplary embodiments of the present disclosure, which is not intended to limit the present disclosure, and the scope of the present disclosure is defined by the claims. Various modifications and equivalents of the disclosure may occur to those skilled in the art within the spirit and scope of the disclosure, and such modifications and equivalents are considered to be within the scope of the disclosure.

Claims (10)

1. A rib structure, comprising a plurality of rib units, adjacent rib units are connected through a wing control unit and a rib outer edge connector, each rib unit comprises a wing link connector and a plurality of rib edge pieces, the rib edge pieces are connected with the wing link connectors, the wing link connectors in each rib unit are correspondingly connected with a wing link group of an aircraft, the wing control unit comprises a slip ring link, a slip ring and a slide bar, one end of the slip ring link is connected with the side surface of a first wing link connector of a first rib unit, the other end of the slip ring link is connected with the slip ring, the slide bar is arranged on the side surface of a second wing link connector of a second rib unit adjacent to the first rib unit and extends towards the direction of the first wing link connector, the sliding ring is sleeved on the sliding rod and can slide along the sliding rod in a reciprocating manner; the rib leading edge units comprise rib leading edge arc pieces, first rib edge pieces and eighth rib edge pieces, and two ends of each rib leading edge arc piece are connected with one end of each rib leading edge arc piece through a first rotating bearing and a sixth rotating bearing.

2. The rib structure of claim 1 wherein a plurality of the rib elements comprise a rib trailing edge element, at least one mid-rib element being disposed between the rib leading edge element and the rib trailing edge element.

3. The rib structure of claim 2 wherein said rib leading edge element further comprises a rib leading edge link connection, the other ends of said first and eighth rib edge elements being connected to said rib center element by a rib outer edge connection, said first and sixth rotary bearings being connected by a first rib element support, said first rib element support passing through and being connected to said rib leading edge link connection.

4. The rib structure of claim 2 wherein the rib trailing edge unit comprises a rib trailing edge wedge, a fourth rib edge piece, a fifth rib edge piece and a wing trailing edge link connector, wherein both ends of the rib trailing edge wedge are connected to one of the ends of the fourth and fifth rib edge pieces by a third and fourth rotary bearing, wherein the other ends of the fourth and fifth rib edge pieces are connected to the rib center unit by a rib outer edge connector, wherein the third and fourth rotary bearings are connected by a third rib unit support, and wherein the third rib unit support passes through and is connected to the wing trailing edge link connector.

5. The rib structure of claim 2 wherein the mid-rib unit comprises a second rib edge piece, a third rib edge piece, a sixth rib edge piece, a seventh rib edge piece, and a mid-wing link connector, the first end of the second rib edge piece and the first end of the third rib edge piece are connected by a second rotational bearing, the first end of the sixth rib edge piece and the first end of the seventh rib edge piece are connected by a fifth rotational bearing, the second rotational bearing and the fifth rotational bearing are connected by a second rib unit support, the second rib unit support passing through and being connected with the mid-wing link connector.

6. The rib structure of claim 1 wherein said rib edge members of adjacent rib units are connected by said rib rim connectors, said rib rim connectors comprising flexible connectors for telescopically connecting adjacent rib edge members and a sliding cover plate, one end of said sliding cover plate being fixedly connected to an end of one of said rib edge members and the other end of said sliding cover plate being slidably connected to an end of the other of said rib edge members.

7. The rib structure of claim 1 wherein a slide bar base is provided on top of the slide bar, two slide bar base articulations are provided on opposite first and second sides of the slide bar base, respectively, each slide bar base articulation being connected to a corresponding slide ring articulation on the slide ring by a linkage.

8. The rib structure of claim 1, wherein the linkage comprises a front bar and a rear bar connected to each other on a first side or a second side of the slide bar base, a first end of the front bar being connected to the corresponding slide bar base hinge mount, a second end of the front bar being connected to the corresponding rib edge member by one hinge mount, a middle portion of the front bar being connected to a first end of the rear bar by another hinge mount, and a second end of the rear bar being connected to the corresponding slide ring hinge mount on the slide ring.

9. A wing structure comprising the rib structure of any one of claims 1-8.

10. An ornithopter-type aircraft employing the wing structure of claim 9.

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