CN218477633U - Wing and aircraft - Google Patents

Abstract

The utility model relates to the technical field of aircrafts, in particular to a wing and an aircraft, wherein the aircraft comprises a wing, the wing comprises a rib plate frame, a front edge web plate and a front edge supporting plate, the rib plate frame comprises a plurality of rib plates and web plate components, and the plurality of rib plates are all connected with the web plate components and are sequentially distributed at intervals along the length extending direction of the web plate components; the front edge web is connected with the rib plates and is adjacent to the front edge ends of the rib plates; the front edge supporting plate is simultaneously connected with the front edge web plate and the ribbed plate, the front edge supporting plate is respectively distributed at an angle with the ribbed plate and the front edge web plate, and the front edge web plate and the front edge supporting plate are both used for supporting the skin. The utility model discloses a wing structural strength is high, and bending resistance, antitorque performance are excellent.

Description

Wing and aircraft

Technical Field

The utility model relates to an aircraft technical field particularly, relates to a wing and aircraft.

Background

The aircraft has wide application in various fields such as agriculture, surveying and mapping, exploration and the like; especially, unmanned aerial vehicle, it has flexible, the reaction is quick, unmanned flight, operation require advantage such as low, all possess the advantage in the application in a plurality of fields.

The aircraft also comprises a propeller type and a fixed wing type; the wings of the fixed-wing unmanned aerial vehicle provided by the related art usually mainly use conforming materials, the molding mode of the composite material has high requirements on the mold, the processing cost of the mold accounts for a large amount of the research and development cost of the whole unmanned aerial vehicle, and once the mold is opened, the subsequent design adjustment is difficult to change, and even the possibility of scrapping the mold exists. Therefore, the wing is prepared by adopting rib plates, stringers, skins and the like in the related technology, and the mode does not need die sinking, has lower cost and is convenient for adjusting design.

However, the structural strength of the wing provided by the related art has yet to be further improved.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a wing and aircraft, the structural strength of wing is high, and bending resistance, antitorque performance are excellent.

The embodiment of the utility model is realized like this:

in a first aspect, the present invention provides a wing, comprising:

the rib plate framework comprises a plurality of rib plates and web plate components, and the plurality of rib plates are connected with the web plate components and are sequentially distributed at intervals along the length extension direction of the web plate components;

the front edge web is connected with the rib plates and is adjacent to the front edge ends of the rib plates;

the leading edge supporting plates are simultaneously connected with the leading edge web and the rib plates, the leading edge supporting plates are respectively distributed at an angle with the rib plates and the leading edge web, and the leading edge web and the leading edge supporting plates are both used for supporting the skin.

In an alternative embodiment, the leading edge web is inset with a rib; and/or the presence of a gas in the gas,

the front edge support plate is inserted with at least one of the front edge web plate and the rib plate.

In an alternative embodiment, the airfoil further includes leading edge ribs coupled to at least one of the leading edge web and the leading edge support plate, and the leading edge ribs are respectively angularly distributed with respect to the leading edge web and the leading edge support plate.

In an alternative embodiment, the leading edge ribs are inset from at least one of the leading edge web and the leading edge support plate; and/or the presence of a gas in the atmosphere,

and front edge fins are arranged between the two ribbed plates which are distributed at intervals.

In an alternative embodiment, the plurality of ribs includes a first rib and a second rib, both the first rib and the second rib being connected to the web assembly; the web component is used for connecting the skin, the first ribbed plate is used for supporting the skin, the wing further comprises a connecting piece connected with the second ribbed plate, the connecting piece is used for being connected with the edge of the skin, and the second ribbed plate is used for being connected with the aircraft body.

In an alternative embodiment, the web assembly includes a first stringer and a web, the plurality of rib plates are connected to the first stringer, and the length extension direction of the first stringer is sequentially distributed at intervals, the web is connected to the first stringer, and the web is distributed between two rib plates which are opposite and distributed at intervals; and/or the presence of a gas in the gas,

the first stringer is spliced with the rib plate; and/or the presence of a gas in the gas,

the web plate assembly comprises two first stringers, and the upper end and the lower end of the rib plate and the upper end and the lower end of the web plate are connected with the first stringers; and/or the presence of a gas in the gas,

the first stringer comprises a first stringer and a second stringer which are connected in an angle mode, at least one of the first stringer and the second stringer is spliced with the rib plate, the first stringer is used for connecting the skin, and the second stringer is connected with the web.

In an alternative embodiment, the wing includes a plurality of web assemblies each connected to a rib, and the plurality of web assemblies are spaced apart along the length of the rib.

In an alternative embodiment, the wing further includes a second stringer, each of the plurality of ribs is connected to the second stringer, and the second stringer is for supporting the skin.

In an optional embodiment, the wing further comprises a bracket, the bracket is connected with the rib plate, and the bracket is used for mounting the antenna; and/or the presence of a gas in the atmosphere,

the wing also comprises a wiring pipe, the wiring pipe is arranged on the rib plate and extends along the length extending direction of the web plate component, and the wiring pipe is used for penetrating a cable; and/or the presence of a gas in the atmosphere,

the rib plate is provided with lightening holes, and the wiring pipe is spliced with the lightening holes.

In a second aspect, the present invention provides an aircraft comprising a wing according to any one of the preceding embodiments.

The utility model discloses beneficial effect of wing includes: the wing provided by the embodiment of the utility model comprises a ribbed slab frame, a front edge web plate and a front edge supporting plate, wherein the ribbed slab frame comprises a plurality of ribbed slabs and web plate components, and the plurality of ribbed slabs are all connected with the web plate components and are sequentially distributed at intervals along the length extending direction of the web plate components; the front edge web is connected with the rib plates and is adjacent to the front edge ends of the rib plates; the front edge supporting plate is simultaneously connected with the front edge web plate and the ribbed plate, the front edge supporting plate is respectively distributed at an angle with the ribbed plate and the front edge web plate, and the front edge web plate and the front edge supporting plate are both used for supporting the skin. The rib plates are connected with the web plate assembly and the front edge web plate, and the front edge web plate and the rib plates are simultaneously connected with the front edge support plate; thus, the plurality of rib plates can be positioned together through the leading edge web and the leading edge support plate to ensure stability among the plurality of rib plates, further ensure structural stability of the rib plate framework and improve structural stability and structural strength of the wing.

The utility model discloses aircraft's beneficial effect includes: the utility model discloses the aircraft includes aforementioned wing, and this wing has excellent structural stability and structural strength.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

Fig. 1 is a schematic structural view of a wing according to an embodiment of the present invention;

fig. 2 is a schematic view of a partial structure of a wing according to an embodiment of the present invention;

FIG. 3 is a schematic structural view of a ribbed slab frame according to an embodiment of the present invention;

fig. 4 is a schematic view of a partial structure of a wing according to an embodiment of the present invention;

FIG. 5 is a schematic view of a partially exploded structure of an embodiment of the present invention;

FIG. 6 is an exploded view of the first stringer, first rib and second rib in an embodiment of the present invention;

FIG. 7 is an enlarged view taken at VII in FIG. 4;

FIG. 8 is a schematic view of an embodiment of the present invention showing the structure of the rib plate and the first stringer;

fig. 9 is a schematic structural view of a web assembly according to an embodiment of the present invention;

FIG. 10 is an exploded view of a rib, first stringer, and second stringer according to an embodiment of the present invention.

An icon: 010-an airfoil; 100-a rib plate frame; 110-rib plate; 111-a first rib; 112-second ribs; 113-lightening holes; 114-a third mating groove; 115-a rib plate body; 116-a connecting plate; 117-sixth mating groove; 118-an eighth mating groove; 119-a plug hole; 120-a web assembly; 130-a first stringer; 131-a first truss panel; 132-a second truss panel; 133-a seventh mating groove; 140-a web; 210-a leading edge web; 211-a first plug socket; 212-a first aperture; 213-a second well; 220-leading edge support plate; 221-a first projection; 222-a second mating groove; 223-a fifth plug groove; 230-leading edge rib; 231-a fourth mating groove; 232-a second projection; 240-a connector; 241-a first plate; 242-a second plate; 250-a second stringer; 251-a ninth mating groove; 260-a scaffold; 270-a wiring pipe; 300-skin.

Detailed Description

To make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the attached drawings in the embodiments of the present invention are combined to clearly and completely describe the technical solution in the embodiments of the present invention, and obviously, the described embodiments are part of the embodiments of the present invention, rather than all embodiments. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "upper", "lower", "front", "rear", etc. are based on the directions or positional relationships shown in the drawings, or the directions or positional relationships that the utility model is conventionally placed when in use, and are only for convenience of describing the present invention and simplifying the description, but not for indicating or implying that the device or element indicated must have a specific direction, be constructed and operated in a specific direction, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed" and "connected" are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood as a specific case by those skilled in the art.

This embodiment provides an aircraft, it can be referred to fixed wing drone. Of course, in other embodiments, the aircraft may also refer to other fixed-wing aircraft; and is not particularly limited herein.

The aircraft comprises an aircraft body and a wing 010 (shown in fig. 1) fitted to the aircraft body. Referring to fig. 1 and 2, wing 010 includes a rib cage 100 and a skin 300, the skin 300 being connected to the rib cage 100.

Further, referring to fig. 2 and 3, the ribbed slab frame 100 includes a plurality of ribbed slabs 110 and web assemblies 120, wherein the plurality of ribbed slabs 110 are connected to the web assemblies 120 and are sequentially spaced along the length of the web assemblies 120; the web assembly 120 is connected with the skin 300, and the rib plate 110 is used for supporting the skin 300; in this manner, the skin 300 can be securely attached to the rib frame 100 and made flatter under the support of the rib 110 to reduce wind resistance.

Still further, referring to fig. 4, the wing 010 further includes a leading edge web 210 and a leading edge support plate 220, wherein the leading edge web 210 is connected to the plurality of ribs 110 and is adjacent to the leading edge end of the rib 110; the leading edge support panel 220 is connected to both the leading edge web 210 and the rib panel 110, and the leading edge support panel 220 is disposed at an angle to the rib panel 110 and the leading edge web 210, respectively, and both the leading edge web 210 and the leading edge support panel 220 are used to support the skin 300. The plurality of ribs 110 are connected not only to web assembly 120, but also to leading edge web 210, and leading edge web 210 and ribs 110 are also connected to leading edge support plate 220 at the same time; in this way, the plurality of ribs 110 can also be co-located by the leading edge web 210 and the leading edge support plate 220 to ensure stability between the plurality of ribs 110, thereby ensuring structural stability of the rib cage 100 and improving structural stability and structural strength of the wing 010.

It should be noted that the leading edge of the rib 110 refers to the end of the wing 010 facing the wind when the aircraft is flying; the leading edge web 210 and the leading edge support plate 220 are arranged at the leading edge end of the rib plate 110, so that the structural strength of the leading edge of the wing 010 can be effectively enhanced, namely the structural strength of the windward end of the wing 010 is enhanced, and the flight stability of the aircraft is ensured.

The connection mode of the leading edge web 210 and the rib plate 110 can be selected according to requirements; to improve the ease of assembly of the wing 010, the leading edge web 210 is spliced with the rib plate 110; specifically, referring to fig. 5, at least one of the front edge web 210 and the rib plate 110 is provided with a first insertion groove 211, and the front edge web 210 and the rib plate 110 are inserted through the first insertion groove 211.

Referring to fig. 5, in the present embodiment, the front edge web 210 and the rib plate 110 are both provided with a first inserting-connecting groove 211, the rib plate 110 is inserted into the first inserting-connecting groove 211 formed in the front edge web 210, and the front edge web 210 is inserted into the first inserting-connecting groove 211 formed in the rib plate 110. The front edge web 210 and the rib plate 110 are provided with the first inserting-connecting grooves 211, when the front edge web 210 and the rib plate 110 are assembled, the first inserting-connecting grooves 211 arranged on the front edge web 210 and the first inserting-connecting grooves 211 arranged on the rib plate 110 can be oppositely inserted, positioning can be rapidly and accurately carried out when the front edge web 210 and the rib plate 110 are assembled, and therefore assembling accuracy is guaranteed.

Of course, in other embodiments, one of the front edge web 210 and the rib 110 is formed with a first insertion groove 211, and the other is inserted into the first insertion groove 211.

It should be understood that in other embodiments, the connection manner of the leading edge web 210 and the rib plate 110 may also be welding, or connection with a fastener such as a bolt, etc., and is not limited in particular.

The connection between the leading edge support plate 220 and the leading edge web 210 and the rib plate 110 can be selected as desired; referring to FIG. 4, to improve the assembly efficiency of the wing 010 and reduce the assembly difficulty, the leading edge support plate 220 is inserted into at least one of the leading edge web 210 and the rib plate 110.

Further, in the present embodiment, the leading edge supporting plate 220 is inserted into the leading edge web 210 and the rib plate 110; therefore, the assembling efficiency of the wing 010 can be effectively improved, and the assembling difficulty of the wing 010 is reduced.

Further, referring to fig. 5, the front edge supporting plate 220 is connected with a first protrusion 221, the front edge supporting plate 220 is provided with a second inserting groove 222, and the first protrusion 221 and the third inserting groove 114 are distributed on the same side of the front edge supporting plate 220; the front edge web 210 is provided with a first hole 212, and the front edge end of the ribbed plate 110 is provided with a third inserting groove 114; the front edge supporting plate 220 is inserted into the third insertion groove 114, and the corresponding rib plate 110 is inserted into the second insertion groove 222, while the first protrusion 221 is inserted into the first hole 212. Thus, the leading edge support plate 220 can be reliably inserted into the leading edge web 210 and the rib plate 110 at the same time; moreover, the third inserting groove 114 is provided at the front end of the rib plate 110, and the first protrusion 221 and the second inserting groove 222 are provided at the same side of the front edge support plate 220, so that when the front edge support plate 220 and the rib plate 110 are inserted through the second inserting groove 222 and the third inserting groove 114, the first protrusion 221 is inserted into the first hole 212, thereby ensuring the assembling operability of the front edge support plate 220. When the front edge supporting plate is inserted into the rib plate 110 and the front edge supporting plate 220, the second inserting groove 222 and the third inserting groove 114 are opposite and matched with each other in an inserting manner, so that the front edge supporting plate 220 and the rib plate 110 can be quickly and conveniently assembled and positioned, and the assembly accuracy is ensured.

Of course, in other embodiments, one of the leading edge support plate 220 and the rib plate 110 is provided with a mating slot, and the other is mated with the mating slot.

It should be understood that in other embodiments, the connection manner of the leading edge support plate 220 and the leading edge web 210, the connection manner of the leading edge support plate 220 and the rib plate 110 can also be welding, or connection by fasteners such as bolts, etc., and is not limited in particular.

It should be noted that the included angle between the leading edge support plate 220 and the leading edge web 210 can be set according to the requirement, for example: 90 °, 88 °, 92 °, or the like, and is not particularly limited herein. Further, the angle between the leading edge support plate 220 and the rib 110 can be set as desired, for example: 90 °, 88 °, 92 °, or the like, and is not particularly limited herein.

It should also be noted that the leading edge web 210 is connected to the rib 110 at an angle, and the included angle between the two can be set according to the requirement, for example: 90 °, 88 °, 92 °, or the like, and is not particularly limited herein.

To further ensure that the frame of the wing 010 can reliably support the skin 300; referring to FIG. 4, the wing 010 further includes leading edge ribs 230, the leading edge ribs 230 are connected to at least one of the leading edge web 210 and the leading edge support plate 220, and the leading edge ribs 230 are respectively disposed at an angle to the leading edge web 210 and the leading edge support plate 220 for supporting the skin 300. Through the arrangement of the leading edge fins 230, the structural strength of the leading edge end of the wing 010 can be further enhanced on one hand, and on the other hand, the skin 300 is supported by additionally arranging the leading edge fins 230, so that the flatness of the skin 300 can be further ensured, the wind resistance is reduced, and the stable flight of an aircraft is ensured.

The angle between the leading edge rib 230 and the leading edge web 210, and the angle between the leading edge rib 230 and the leading edge support plate 220 can be set as desired, such as 90 °, 88 °, or 92 °, and is not limited herein.

Further, the leading edge rib 230 is inset with at least one of the leading edge web 210 and the leading edge support plate 220; thus, the ease of assembling the leading edge rib 230 can be improved, and the assembling efficiency of the wing 010 can be improved.

Further, referring to fig. 5, the front edge rib 230 is provided with a fourth inserting groove 231, the front edge rib 230 is further connected with a second protrusion 232, the fourth inserting groove 231 and the second protrusion 232 are disposed on the same side of the front edge rib 230, the front edge web 210 is provided with a second hole 213, the front edge support plate 220 is provided with a fifth inserting groove 223, and the fifth inserting groove 223 and the second inserting groove 222 are distributed on two opposite sides of the front edge support plate 220. When the leading edge rib 230 is assembled, the leading edge rib 230 only needs to be moved towards one direction, the leading edge support plate 220 is inserted into the fourth insertion groove 231, the leading edge rib 230 is inserted into the fifth insertion groove 223, meanwhile, the leading edge rib 230 can be simultaneously inserted into the leading edge web 210 through the insertion matching of the second protrusion 232 and the second hole 213, and thus, the leading edge rib 230 is inserted into and matched with both the leading edge web 210 and the leading edge support plate 220, so that the easy assembly of the leading edge rib 230 is ensured, and the assembly stability of the leading edge rib is also ensured; moreover, the front edge rib 230 and the front edge support plate 220 are inserted and matched through the fourth insertion groove 231 and the fifth insertion groove 223, so that the positioning accuracy during the assembly of the front edge rib 230 can be improved.

It should be appreciated that in other embodiments, the leading edge ribs 230 and at least one of the leading edge web 210 and the leading edge support plate 220 may be welded or fastened with fasteners such as bolts, etc., and are not particularly limited herein.

In order to reliably support the skin 300 with the leading edge ribs 230, and further ensure a reliable fit between the leading edge support plate 220 and the leading edge web 210 by the leading edge ribs 230; referring to fig. 4 and 5, the wing 010 includes a plurality of leading edge ribs 230, and the leading edge ribs 230 are disposed between two ribs 110 that are spaced apart from each other; specifically, a plurality of spaced apart leading edge ribs 230 are disposed between two opposing and spaced apart ribs 110. This arrangement allows the plurality of leading edge ribs 230 to be more densely spaced to reliably support the skin 300 at the leading edge of the wing 010 and to provide improved structural stability between the leading edge support plate 220 and the leading edge web 210 via the plurality of leading edge ribs 230.

It should be noted that the specific number of leading edge ribs 230 between two opposing and spaced ribs 110 can be selected as desired, for example: one, two, three, four, etc., and are not specifically limited herein.

It should also be noted that the leading edge rib 230 is shaped to fit the leading edge of the rib 110, i.e., the leading edge rib 230 is shaped similar to the leading edge of the rib 110; in this way, it is ensured that the leading edge of the rib and the leading edge rib 230 together reliably support the skin 300, ensuring the flatness of the skin 300.

Referring to fig. 4 and 6, in the present embodiment, the plurality of ribs 110 includes a first rib 111 and a second rib 112, and both the first rib 111 and the second rib 112 are connected to the web assembly 120; the web assembly 120 is used for connecting the skin 300, the first rib 111 is used for supporting the skin 300, the wing 010 further comprises a connecting member 240 connected with the second rib 112, the connecting member 240 is used for connecting with the edge of the skin 300, and the second rib 112 is used for connecting with the aircraft body. In this way, not only can the flatness of the skin 300 connected to the web assembly 120 be ensured by the first ribs 111, but also the reliability of the assembly of the wing 010 to the aircraft body can be ensured by the second ribs 112; in addition, the edge of the skin 300 is connected by the connecting member 240 connected to the second rib 112, so that the problem of edge curling of the skin 300 can be solved, the flatness of the skin 300 can be ensured, the air resistance can be reduced, and the stability of flight can be ensured.

Further, the plurality of ribs 110 includes at least two second ribs 112, at least one second rib 112 being coupled to the fuselage of the aircraft body, and at least another second rib 112 being coupled to the power bar of the aircraft body. In this way, the stability of the wing 010 assembled to the aircraft body by the second rib 112 can be ensured.

The specific number of second ribs 112 can be selected as desired; the wing 010 of this embodiment includes six second rib plates 112, the six second rib plates 112 are divided into three groups, each group includes two second rib plates 112 that are opposite and distributed at an interval, and along the length direction of the web assembly 120, one group of the six second rib plates is distributed approximately in the middle of the length extending direction of the web assembly 120 and is connected with the fuselage of the aircraft body, and the other two groups of the six second rib plates are distributed at two ends of the length extending direction of the web assembly 120 and are connected with the power rod of the aircraft body.

Of course, in other embodiments, the number of the second ribs 112 may also be three, nine, etc., and is not limited herein.

The number of first ribs 111 can be selected as desired, for example: one, two, three, four, six, eight, etc., and is not specifically limited herein. In a preferred embodiment, the first ribs 111 are disposed on both sides of the group of second ribs 112 distributed in the middle of the web assembly 120, and are symmetrically distributed.

Referring to fig. 6, the second rib 112 includes a rib body 115 and a connecting plate 116, the connecting plate 116 is connected to a lower end of the rib body 115, and the connecting plate 116 is used for connecting a fuselage or a power rod of the aircraft body; the rib body 115 is substantially the same shape as the first rib 111; in this way, it is ensured that the rib body 115 can reliably support the skin 300 as well, so that the flatness of the skin 300 is ensured, and that the second rib 112 can reliably be connected to the fuselage or the power bar.

The connection mode of the connecting plate 116 and the machine body or the power rod can be riveting; thus, the easy operability of the wing 010 in assembling the aircraft body is ensured.

It should be noted that the number of the connecting members 240 connected to the second rib 112 can be selected according to the requirement, for example: one, two, three, ten, etc., and are not specifically limited herein. In order to stably and reliably fix the edge of the skin 300 by using the connecting member 240, and effectively improve the problem of edge curling of the skin 300, the number of the connecting members 240 is greater than or equal to two, and the connecting member 240 is connected to at least one of the rib body 115 and the connecting plate 116.

The connector 240 may be selected as desired; referring to fig. 7, the connecting member 240 of the present embodiment is an angle block, which includes a first plate 241 and a second plate 242 connected at an angle, the first plate 241 is connected to the second rib 112, and the second plate 242 is connected to the edge of the skin 300; in this way, it is ensured on the one hand that the corner block can be reliably connected to the second rib 112 and on the other hand that the corner block can be reliably connected to the edge of the skin 300.

The included angle between the first plate 241 and the second plate 242 can be set according to the requirement, for example: 90 °, 88 °, 92 °, etc., and is not particularly limited herein.

The connection mode of the first plate 241 and the second rib plate 112 and the connection mode of the second plate 242 and the skin 300 can be selected according to requirements; in this embodiment, to ensure the easy operability of the wing 010, the first plate 241 is riveted to the second rib 112 and the second plate 242 is riveted to the skin 300; specifically, the riveting may be performed by a riveting member such as a blind rivet.

Of course, in other embodiments, the connection manner of the first plate 241 and the second rib plate 112 may also be welding, screwing, or the like; the connection manner of the skin 300 and the second plate 242 may also be welding, etc., and is not particularly limited herein.

It should be noted that the connecting member 240 may be made of cut-off angle aluminum to reduce the weight and ensure the reliability of connecting the skin 300 to the second rib 112.

It should be understood that in other embodiments, the connecting member 240 can also be a positioning plate or the like connected to the second rib 112, and the positioning plate or the like can also be integrally formed with the second rib 112, which is not particularly limited herein.

The structure of the web assembly 120 may be arranged as desired; referring to fig. 8 and 9, the web assembly 120 of the present embodiment includes a first stringer 130 and a web 140, a plurality of ribs 110 are connected to the first stringer 130, a first rib 111 and a second rib 112 are connected to the first stringer 130, and the plurality of ribs 110 are sequentially distributed at intervals along the length extending direction of the first stringer 130; first stringer 130 is used to join skin 300; a web 140 is connected to the first stringer 130, and the web 140 is disposed between two opposing and spaced apart ribs 110. The plurality of ribs 110 are all connected to the first stringer 130, and the web 140 is provided between the two ribs 110 that are opposite and spaced apart, so that the structural strength of the wing 010 can be improved.

Further, the web assembly 120 includes a plurality of webs 140, and at least one web 140 is disposed between each two opposite and spaced ribs 110; thus, the structural strength of the wing 010 can be effectively improved.

Still further, web assembly 120 includes two first stringers 130, with first stringers 130 attached to the upper and lower ends of rib plate 110 and to the upper and lower ends of web 140. With this arrangement, a plurality of ribs 110 can be disposed between the two first stringers 130, and the webs 140 can be assembled between the two opposing ribs 110 spaced apart from each other, so as to sufficiently improve the structural strength of the wing 010.

The connection mode of the first stringer 130 and the rib plate 110 can be selected according to requirements; to improve the ease of assembly and handling of wing 010, first stringer 130 is spliced into rib plate 110.

The structure of first stringer 130 may be configured as desired; referring to fig. 10, in the present embodiment, in order to ensure that the first stringer 130 is stably assembled with the web 140 and the rib plate 110, and to ensure that the first stringer 130 can be stably and reliably connected with the skin 300, the first stringer 130 includes a first stringer 131 and a second stringer 132 which are connected at an angle, at least one of the first stringer 131 and the second stringer 132 is inserted into the rib plate 110, the first stringer 131 is used for connecting the skin 300, and the second stringer 132 is connected with the web 140. As described above, the first stringer 131 and the second stringer 132, which are connected at an angle, ensure that the first stringer 130 can be reliably connected to the web 140 and the rib 110, and that the first stringer 130 can be reliably connected to the skin 300.

The angle between the first truss 131 and the second truss 132 can be selected according to the requirement, for example: 90 °, 88 °, 92 °, etc., and the connection manner of the first truss panel 131 and the second truss panel 132 may be integrally formed or welded, etc., which are not particularly limited herein.

Further, referring to fig. 10, the rib plate 110 has a sixth inserting groove 117, and the second truss plate 132 has a seventh inserting groove 133; the first stringer 130 is plugged with the sixth plugging groove 117, the rib plate 110 is plugged with the seventh plugging groove 133, specifically, the first stringer 131 and the second stringer 132 are plugged in the sixth plugging groove 117, and the sixth plugging groove 117 and the seventh plugging groove 133 are opposite and matched with each other in a plugging manner. Thus, not only is the ease of assembly and the structural stability after assembly of the rib plate 110 and the first stringer 130 ensured, but also the positioning accuracy of the rib plate 110 and the first stringer 130 during assembly is improved by the cooperation of the sixth inserting groove 117 and the seventh inserting groove 133; the first stringer 131 is also inserted into the sixth insertion groove 117, so that the problem that the first stringer 130 protrudes relative to the rib 110 can be solved, and the skin 300 can be supported by the rib 110 reliably.

It should be understood that in other embodiments, only the second stringer 132 of the first stringer 130 is spliced to the sixth splicing groove 117.

It should be noted that, when the rib 110 is the second rib 112, the sixth inserting groove 117 is opened in the rib body 115 to avoid interference between the connecting plate 116 and the aircraft body.

The skin 300 is connected to the first stringer 131 in a manner including, but not limited to, riveting with a rivet such as a blind rivet; the second truss 132 and the web 140 are connected by riveting or welding, wherein the riveting ensures the convenience of assembly, which is beneficial to improving the assembly and production efficiency.

In this embodiment, referring to fig. 4, the wing 010 includes a plurality of web assemblies 120, the web assemblies 120 are all connected to the rib 110, and the web assemblies 120 are spaced apart along the length extending direction of the rib 110, that is, the web assemblies 120 are spaced apart along the direction from the leading edge of the rib 110 to the trailing edge thereof. Thus, when the skin 300 is connected to the first stringers 130 of the web assemblies 120 and covers the outer surface of the frame of the wing 010, the plurality of web assemblies 120 and the plurality of ribs 110 define a plurality of substantially rectangular spaces, so that the skin 300 and the stressed frame structure form a bending and torsion resistant box of the wing 010 as a whole, i.e., the wing 010 has a multi-girder box structure, thereby improving the bending and torsion resistance of the wing 010.

It should be noted that, referring to fig. 6, the upper end and the lower end of the first rib plate 111 are provided with sixth inserting grooves 117, so that the upper end and the lower end of the first rib plate 111 can be inserted with a first stringer 130. Further, the upper end and the lower end of the first rib plate 111 are provided with a plurality of sixth inserting grooves 117, so as to ensure that the upper end and the lower end of the first rib plate 111 can be inserted into the first stringers 130 of the plurality of web assemblies 120, thereby ensuring easy assembly and structural stability of the rib plate frame 100.

It should be further noted that, referring to fig. 6, a plurality of sixth inserting-connecting grooves 117 are disposed at an upper end of the second rib plate 112, that is, a plurality of sixth inserting-connecting grooves 117 are disposed at an upper end of the rib plate body 115, that is, a plurality of sixth inserting-connecting grooves 117 are disposed at an end of the rib plate body 115 away from the connecting plate 116, so that the second rib plate 112 is reliably inserted into a portion of the first stringers 130 of the web assemblies 120. The lower end of the second rib plate 112 is provided with not only a plurality of sixth inserting-connecting grooves 117 but also an inserting-connecting hole 119, specifically, the lower end of the rib plate body 115 is provided with a plurality of sixth inserting-connecting grooves 117, and the connecting position of the rib plate body 115 and the connecting plate 116 is provided with the inserting-connecting hole 119. In this way, another portion of the first stringers 130 of the plurality of web assemblies 120 may be respectively inserted into the lower end of the second rib 112 through the sixth insertion groove 117 and the insertion hole 119.

Referring to fig. 4 and 10, the wing 010 of the embodiment further includes a second stringer 250, the plurality of rib plates 110 are all connected to the second stringer 250, the second stringer 250 is used for supporting the skin 300, and the arrangement of the second stringer 250 can further improve the stability of the plurality of rib plates 110, so as to ensure the structural stability and the structural strength of the wing 010.

Optionally, the second stringer 250 is a long plate structure, and is inserted into the rib plate 110; when the rib plate 110 is the second rib plate 112, the second stringer 250 is inserted into the rib plate body 115; in this way, the stability of the structure of the wing 010 is ensured, as well as the ease of assembly of the wing 010.

Further, referring to fig. 10, the rib plate 110 is provided with an eighth inserting groove 118, the second stringer 250 is provided with a ninth inserting groove 251, the second stringer 250 is inserted into the eighth inserting groove 118, the rib plate 110 is inserted into the ninth inserting groove 251, and the eighth inserting groove 118 is opposite to and matched with the ninth inserting groove 251; in this way, on the one hand, stability of connection of the second stringer 250 to the plurality of ribs 110 and ease of assembly can be ensured, and on the other hand, accurate positioning of the assembly can be ensured, and assembly efficiency can be improved.

Still further, the rib 110 is generally designed to be streamlined to ensure that the wing 010 is streamlined, the width of the trailing edge end of the rib 110 is gradually narrowed, only one second stringer 250 may be assembled at the trailing edge end with a narrow width, and one second stringer 250 may be assembled at both the upper end and the lower end of the rib 110 at a position with a relatively wide width to improve the structural stability among the plurality of ribs 110, thereby improving the structural stability and the structural strength of the wing 010.

It should be noted that the trailing edge of the rib 110 refers to the end of the wing 010 that is leeward when the aircraft is flying.

In order to reduce the overall weight of the wing 010, the rib plates 110, the web plates 140, the leading edge web plates 210 and the leading edge support plates 220 are all provided with lightening holes 113, and the number and the inner diameter of the lightening holes 113 can be set according to requirements, so that sufficient strength is ensured under the condition of reducing the overall weight of the wing 010.

The materials of skin 300, rib 110, web 140, first stringer 130, second stringer 250, leading edge web 210, leading edge support plate 220, and leading edge rib 230 of wing 010 can be selected as desired; the skin 300 may be a glass fiber board, and specifically may be a soft glass fiber board with thickness dimensions of 0.5mm, 0.3mm, and the like; the second rib plate 112 is used as a main bearing structure and can be made of a carbon fiber plate; the first rib 111 mainly supports the skin 300, and can adopt a laminated plate; the first stringer 130 may be directly thin walled angle aluminum; the web 140 may be made of hard glass fiber board to ensure structural strength; the leading edge web 210, leading edge support panel 220, leading edge rib 230, and second stringer 250 may each be laminated to securely support the skin 300 and position the rib 110.

The materials such as angle aluminum, glass fiber boards, laminates and the like are simple to obtain, the cost is low, and the method can be widely used for finished products or research, development, test and proofing; the materials are simple to process, the production period is short, and the time can be effectively saved.

Referring to fig. 4, the wing 010 of this embodiment further includes a bracket 260, the bracket 260 is connected to the rib 110, and the bracket 260 is used for mounting an antenna, for example: mount 260 is used to mount an RTK antenna. By the provision of the bracket 260, ease of assembly of the antenna to the wing 010 is ensured.

Further, the bracket 260 is connected between the two second ribs 112 located at the end of the web assembly 120 in the length extending direction; in this way, the antenna can be disposed at the end of the wing 010 in the longitudinal direction through the bracket 260, so as to reduce various interferences on the antenna.

The connection mode of the bracket 260 and the second rib plate 112 can be selected according to requirements; the bracket 260 of the present embodiment is riveted to the second rib 112 by a blind rivet. Of course, in other embodiments, the bracket 260 can also be connected to the second rib 112 by welding, clamping, etc.

Optionally, the wing 010 needs to be equipped with two antennas, the wing 010 includes two brackets 260, the two antennas and the two brackets 260 are assembled in a one-to-one correspondence manner, and the two brackets 260 are respectively connected to the second rib 112 located at two ends of the length extending direction of the web assembly 120, so that the two brackets 260 are distributed at two ends of the length extending direction of the web assembly 120, and a sufficient distance is provided between the two antennas respectively assembled to the two brackets 260, so as to reduce interference received by the antennas.

It should be noted that the bracket 260 may be a CNC machined part, and may also be an injection molded part, and is not limited in detail herein.

Referring to fig. 4, the wing 010 of the embodiment further includes a routing tube 270, the routing tube 270 is disposed on the rib plate 110 and extends along the length extending direction of the web assembly 120, and the routing tube 270 is used for passing through a cable. Through the setting of walking spool 270 for the cable of assembling in the device part of wing 010 such as antenna can wear to locate wherein, has improved the inside clean and tidy nature of wing 010 structure, and the easy operability of cable setting.

Further, the routing tube 270 is inserted into the lightening hole 113 of the rib plate 110; specifically, the routing tubes 270 are sequentially inserted into the lightening holes 113 of the plurality of rib plates 110. In this manner, the ease of operation and stability of the mounting of the routing tube 270 to the cross brace 110 is ensured.

It should be noted that the routing tube 270 may have a glass fiber plate rolled up, and the thickness of the glass fiber plate may be selected according to the requirement, for example: 0.1mm, 0.12mm, etc., and is not particularly limited herein. Of course, in other embodiments, the routing tube 270 may also be an injection molded PVC (polyvinyl chloride) pipe or the like, and is not limited herein.

The assembly process of the wing 010 provided by the embodiment includes: connecting the second rib 112 to the connecting member 240; splicing each rib plate 110 to the first stringer 130; connecting web 140 and first stringer 130; connecting the bracket 260 to the second rib 112; connecting the leading edge web 210 to the rib 110; assembling leading edge support panel 220, leading edge rib 230, and second stringer 250; assembling the wiring pipe 270 on the rib plate 110; skin 300 is assembled to connect with first stringer 130.

To sum up, the utility model discloses a wing 010 can be used for aircraft such as unmanned aerial vehicle, and this wing 010's structural strength is high, and bending resistance, antitorque property are excellent.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. An airfoil, comprising:

a rib frame (100), the rib frame (100) comprising a plurality of ribs (110) and a web assembly (120), the plurality of ribs (110) being connected to the web assembly (120) and being spaced apart in sequence along the length of the web assembly (120);

a leading edge web (210), said leading edge web (210) being connected to a plurality of said ribs (110) and being adjacent a leading edge end of said ribs (110);

the leading edge support plate (220), the leading edge support plate (220) is connected with the leading edge web (210) and the ribbed plate (110) simultaneously, the leading edge support plate (220) is respectively distributed at an angle with the ribbed plate (110) and the leading edge web (210), and the leading edge web (210) and the leading edge support plate (220) are both used for supporting the skin (300).

2. The wing as claimed in claim 1, characterized in that the leading edge web (210) is plugged into the rib (110); and/or the presence of a gas in the gas,

the leading edge support plate (220) is plugged with at least one of the leading edge web (210) and the rib plate (110).

3. The wing as recited in claim 1 further comprising leading edge ribs (230), the leading edge ribs (230) being connected to at least one of the leading edge web (210) and the leading edge support plate (220), and the leading edge ribs (230) being angularly distributed with respect to the leading edge web (210) and the leading edge support plate (220), respectively.

4. The wing as claimed in claim 3, characterized in that the leading edge rib (230) is plugged with at least one of the leading edge web (210) and the leading edge support plate (220); and/or the presence of a gas in the gas,

the leading edge rib (230) is arranged between the two rib plates (110) which are distributed at intervals.

5. The airfoil of claim 1, wherein the plurality of ribs (110) includes a first rib (111) and a second rib (112), the first rib (111) and the second rib (112) each being connected to the web assembly (120); the web component (120) is used for connecting the skin (300), the first rib (111) is used for supporting the skin (300), the wing further comprises a connecting piece (240) connected with the second rib (112), the connecting piece (240) is used for connecting with the edge of the skin (300), and the second rib (112) is used for connecting with an aircraft body.

6. The wing as claimed in claim 1, wherein the web assembly (120) includes a first stringer (130) and a web (140), a plurality of ribs (110) are connected to the first stringer (130), the first stringer (130) is spaced apart in a length extending direction, the web (140) is connected to the first stringer (130), and the web (140) is distributed between two opposing and spaced apart ribs (110); and/or the presence of a gas in the gas,

the first stringer (130) is spliced with the rib plate (110); and/or the presence of a gas in the gas,

the web assembly (120) includes two of the first stringers (130), the first stringers (130) being connected to upper and lower ends of the ribs (110) and upper and lower ends of the web (140); and/or the presence of a gas in the gas,

the first stringer (130) comprises a first stringer (131) and a second stringer (132) which are connected in an angle mode, at least one of the first stringer (131) and the second stringer (132) is plugged with the rib plate (110), the first stringer (131) is used for connecting the skin (300), and the second stringer (132) is connected with the web (140).

7. The wing as claimed in claim 1, characterized in that the wing comprises a plurality of web assemblies (120), a plurality of web assemblies (120) each being connected to the rib (110), and a plurality of web assemblies (120) being spaced apart along the length extension of the rib (110).

8. The wing as claimed in claim 1 further comprising a second stringer (250), wherein a plurality of the ribs (110) are each connected to the second stringer (250), and wherein the second stringer (250) is configured to support the skin (300).

9. The airfoil as claimed in claim 1 further comprising a bracket (260), the bracket (260) being connected to the rib (110), the bracket (260) being for mounting an antenna; and/or the presence of a gas in the gas,

the wing further comprises a wiring pipe (270), the wiring pipe (270) is arranged on the rib plate (110) and extends along the length extending direction of the web plate component (120), and the wiring pipe (270) is used for penetrating through a cable; and/or the presence of a gas in the gas,

the rib plate (110) is provided with lightening holes (113), and the wiring pipe (270) is spliced with the lightening holes (113).

10. An aircraft comprising a wing as claimed in any one of claims 1 to 9.

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