A morphing wing for an aircraft and a method of assembling the same

Abstract

The application relates to the technical field of aircraft wing design, in particular to a variable wing of an aircraft, which comprises a leading edge, a wing body and a trailing edge connected in sequence, the wing body comprises a plurality of single cell structures, two adjacent single cell structures are connected to each other, each single cell structure comprises a chiral structure and a zero Poisson ratio structure connected to each other; all the chiral structures are arranged on a transverse section of the variable wing, each chiral structure has a tensile rotation characteristic, so that the variable wing changes the camber when subjected to tensile and compressive loads; all the zero Poisson ratio structures are arranged on a longitudinal section of the variable wing, each zero Poisson ratio structure has a tensile deformation characteristic, so that the variable wing changes the span when subjected to tensile and compressive loads. The scheme can solve the problems of small adjustable range and discontinuous shape change in the related art.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft wing design, and in particular to a variable wing of an aircraft and an assembling method thereof. BACKGROUND

[0002] The technology that an aircraft changes the structural shape to adapt to different flight environmental conditions to maintain the optimal performance and efficiency during flight is called variable structure technology, and the wing using the variable structure technology is called a variable wing.

[0003] In the related art, the variable function of the variable wing is usually realized by a driving mechanism composed of a complex linkage mechanism. However, the above scheme has the problems of small adjustable range of the wing and discontinuous shape change.

[0004] Therefore, there is an urgent need to provide a variable wing of an aircraft and an assembling method thereof to solve the above technical problems. SUMMARY

[0005] The variable wing of an aircraft and the assembling method thereof provided by the embodiments of the present application can solve the problems of small adjustable range of the wing and discontinuous shape change in the related art.

[0006] In a first aspect, the embodiments of the present application provide a variable wing of an aircraft, comprising a leading edge, a wing body and a trailing edge connected in sequence, the wing body comprising a plurality of unit cell structures, two adjacent unit cell structures being connected to each other, each unit cell structure comprising a chiral structure and a zero Poisson's ratio structure connected to each other.

[0007] All the chiral structures are arranged on a transverse cross section of the variable wing, each chiral structure having a tensile rotation characteristic to make the variable wing change the camber when subjected to tensile and compressive loads.

[0008] All the zero Poisson's ratio structures are arranged on a longitudinal cross section of the variable wing, each zero Poisson's ratio structure having a tensile deformation characteristic to make the variable wing change the span when subjected to tensile and compressive loads.

[0009] In a possible design, each chiral structure is a four-strut configuration, and each chiral structure is provided with four first connecting parts.

[0010] Each first connecting part is arranged at the end of one strut in the chiral structure.

[0011] The first connecting part is used to connect two adjacent chiral structures by rivets, or is used to connect one chiral structure and one zero Poisson's ratio structure by rivets.

[0012] In a possible design, each first connecting part comprises a first rivet hole and a second rivet hole, one end of the first rivet hole is connected with the ligament, the other end of the first rivet hole is connected with the second rivet hole, the first rivet hole is in the same plane as the ligament, and the plane where the second rivet hole is located is at an angle of 45 degrees with the plane where the first rivet hole is located.

[0013] In a possible design, each zero Poisson's ratio structure is in a rhombus configuration, and each zero Poisson's ratio structure is provided with two second connecting parts.

[0014] Each second connecting part is arranged at two acute angle ends of the zero Poisson's ratio structure.

[0015] The second connecting part is used for connecting two adjacent zero Poisson's ratio structures through rivets, or is used for connecting one chiral structure and one zero Poisson's ratio structure through rivets.

[0016] In a possible design, each second connecting part comprises a third rivet hole and a fourth rivet hole, one end of the third rivet hole is connected with one acute angle end, the other end of the third rivet hole is connected with the fourth rivet hole, the third rivet hole is in the same plane as the acute angle end, and the plane where the third rivet hole is located is at an angle of 45 degrees with the plane where the fourth rivet hole is located.

[0017] In a possible design, each unit cell structure comprises two chiral structures and four zero Poisson's ratio structures.

[0018] Four second rivet holes of a first chiral structure are sequentially connected with the fourth rivet holes at one end of four zero Poisson's ratio structures, and four second rivet holes of a second chiral structure are sequentially connected with the fourth rivet holes at the other end of the four zero Poisson's ratio structures.

[0019] In a possible design, the unit cell structures are not completely the same in size, unit cell structures of the same size are connected with each other to form a constituent unit, and multiple constituent units are connected with each other to form the morphing wing.

[0020] In a second aspect, an embodiment of the present application provides an assembly method of a morphing wing of an aircraft, as described in any one of claims 1-7, and the assembly method comprises:

[0021] Connecting the chiral structures and the zero Poisson's ratio structures to obtain a unit cell structure;

[0022] Connecting multiple unit cell structures to obtain a wing body;

[0023] Connecting the leading edge, the wing body and the trailing edge to obtain the morphing wing.

[0024] Compared with the prior art, the present application has at least the following beneficial effects:

[0025] In the present application, by applying the chiral structure with pressure-torsion characteristics to the transverse section of the wing, and applying the zero-Poisson ratio structure with large tensile deformation characteristics to the longitudinal section of the wing, the structure of the variable geometry wing can meet the requirements of variable camber and variable span at the same time, multiple deformation functions are integrated on the same wing, and the problems of small adjustable range and discontinuous shape change in the related art can be solved. BRIEF DESCRIPTION OF DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor.

[0027] Figure 1 is a structural schematic diagram of a variable geometry wing of an aircraft provided by an embodiment of the present application;

[0028] Figure 2 is a front view structural schematic diagram of a variable geometry wing of an aircraft provided by an embodiment of the present application;

[0029] Figure 3 is a top view structural schematic diagram of a variable geometry wing of an aircraft provided by an embodiment of the present application;

[0030] Figure 4 is a side view structural schematic diagram of a variable geometry wing of an aircraft provided by an embodiment of the present application;

[0031] Figure 5 is a normal state schematic diagram of a chiral structure provided by an embodiment of the present application;

[0032] Figure 6 is a variable camber schematic diagram of a chiral structure provided by an embodiment of the present application;

[0033] Figure 7 is a normal state schematic diagram of a zero-Poisson ratio structure provided by an embodiment of the present application;

[0034] Figure 8 is a variable span schematic diagram of a zero-Poisson ratio structure provided by an embodiment of the present application;

[0035] Figure 9 is a structural schematic diagram of a unit cell structure provided by an embodiment of the present application;

[0036] Figure 10is a structural schematic diagram of a chiral structure provided by an embodiment of the present application;

[0037] Figure 11 is a structural schematic diagram of a zero Poisson's ratio structure provided by an embodiment of the present application;

[0038] Figure 12 is a flow chart of an assembly method of a morphing wing of an airplane provided by an embodiment of the present application.

[0039] Reference signs:

[0040] 10-wing body;

[0041] 1-unit cell structure;

[0042] 11-chiral structure;

[0043] 111- ligament;

[0044] 112-first connecting part;

[0045] 112a-first rivet hole;

[0046] 112b-second rivet hole;

[0047] 12-zero Poisson's ratio structure;

[0048] 121-second connecting part;

[0049] 121a-third rivet hole;

[0050] 121b-fourth rivet hole;

[0051] 20-leading edge;

[0052] 30-trailing edge. DETAILED DESCRIPTION

[0053] In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are some of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0054] A morphing wing of an airplane provided by an embodiment of the present application will be described below in conjunction with the drawings.

[0055] In one implementation of the present application, the bending angles of the leading edge and the trailing edge are changed, the middle wing mainly serves as a support for loading and mounting parts of the wing, thereby meeting the requirements of the variable wing of the aircraft, but the space for designing and deforming the leading edge and the trailing edge is small, and the method cannot meet the requirements of complex flight environments.

[0056] Therefore, the present application provides another implementation, i.e., the leading edge and the trailing edge of the aircraft do not deform, and serve as a support for loading and mounting parts, and the wing of the aircraft realizes various deformation functions.

[0057] As shown in Figures 1 to 4 , the embodiment of the present application provides a variable wing of an aircraft, which comprises a leading edge 20, a wing 10 and a trailing edge 30 connected in sequence, the wing 10 comprises a plurality of unit cell structures 1, and adjacent two unit cell structures 1 are connected to each other, each unit cell structure 1 comprises a chiral structure 11 and a zero Poisson's ratio structure 12 connected to each other.

[0058] The chiral structure 11 is arranged on a transverse cross section of the variable wing, wherein the transverse direction is perpendicular to the wingspan of the wing (for reference Figure 2 ), and each chiral structure 11 has a tensile rotation characteristic, which can change the bending of the wing when the variable wing is subjected to tensile and compressive loads (for reference Figures 5 to 6 ).

[0059] The zero Poisson's ratio structure 12 is arranged on a longitudinal cross section other than the above transverse cross section (for reference Figures 3 to 4 ), and each zero Poisson's ratio structure 12 has a tensile deformation characteristic, which can change the thickness and length of the wing when the variable wing is subjected to tensile and compressive loads (for reference Figures 7 to 8 ).

[0060] In one embodiment of the present application, considering that the variable wing needs to meet the requirements of variable bending and variable wingspan at the same time, the inventor creatively combines the two structures to form an anisotropic unit cell structure 1 with different surfaces, different configurations and different deformation functions, as shown in Figure 9 .

[0061] When the surface part controlling the performance of a certain direction in the unit cell structure 1 deforms, it will affect the surface parts of adjacent different directions, i.e., the deformations of different direction surfaces are coupled together. For example, when the chiral structure 11 controlling the variable bending deforms, the zero Poisson's ratio structure 12 directly connected to the chiral structure 11 will be greatly reduced in deformation degree or even not deformed due to structural constraints; the same is true for the zero Poisson's ratio structure 12 which deforms.

[0062] Therefore, in order to solve the constraint caused by the direct connection of the chiral structure 11 and the zero Poisson's ratio structure 12, the decoupling processing needs to be performed on the unit cell structure 1, and the coupling coefficient M in the following form is defined:

[0063]

[0064] In the formula, L is the original deformation, and AL is the difference between the original deformation and the deformation after coupling.

[0065] The coupling performance of the unit cell structure 1 can be judged according to the coupling coefficient M. For example, when M is 0, it indicates that the unit cell structure 1 is in a completely free deformation state without restriction; when M is 1, it indicates that the unit cell structure 1 is in a completely restricted state and cannot deform.

[0066] Through the measurement experiment of the coupling performance of the unit cell structure 1, the inventors creatively decouple the design of the unit cell structure 1, that is, the connection mode of the chiral structure 11 and the zero Poisson's ratio structure 12 in the unit cell structure 1 is changed from direct connection to fixed connection through rivets and rivet holes. This method not only can ensure the stability of the unit cell structure 1, but also can maximize the deformation of the two kinds, greatly improving the deformation ability of the unit cell structure 1.

[0067] Specifically, the above-mentioned chiral structure 11 is a four-tendon configuration, as shown in Figure 7 The end of each tendon 111 of the chiral structure 11 is provided with a first connecting part 112, and the rivet hole is fixed by the rivet. The first connecting part 112 can realize the connection of two chiral structures 11 or the connection of one chiral structure 11 and one zero Poisson's ratio structure 12.

[0068] The first connecting part 112 includes two parts, which are a first rivet hole 112a and a first rivet hole 112b. One end of the first rivet hole 112a is connected with the end of the tendon 111 of the chiral structure 11, and the other end is connected with the first rivet hole 112b. The first rivet hole 112a and the tendon 111 are located in the same plane, and the plane where the first rivet hole 112b is located and the plane where the first rivet hole 112b is located are at an angle of 45 degrees.

[0069] In an embodiment of the present application, the above-mentioned zero Poisson's ratio structure 12 is a rhombus configuration, as shown in Figure 8 The two acute angle ends of the zero Poisson's ratio structure 12 are provided with a second connecting part 121, which is similar to the first connecting part 112. The second connecting part 121 can realize the connection of two zero Poisson's ratio structures 12 or the connection of one chiral structure 11 and one zero Poisson's ratio structure 12.

[0070] The second connecting part 121 comprises two parts, i.e. a third rivet hole 121a and a fourth rivet hole 121b. One end of the third rivet hole 121a is connected with the acute angle end of the zero Poisson's ratio structure 12, and the other end is connected with the fourth rivet hole 121b. The third rivet hole 121a and the acute angle end are located in the same plane, and the plane where the fourth rivet hole 121b is located is at an angle of 45 degrees with the plane where the third rivet hole 121a is located.

[0071] It can be understood that, by improving the connecting part of the chiral structure 11 and the zero Poisson's ratio structure 12 in the above manner, the adjacent two structures can be connected in both horizontal and vertical directions. The specific implementation manner is described below.

[0072] In an embodiment of the present application, considering that the single cell structure 1 needs to be tested for load bearing and deformation during the assembly process when manufacturing the morphing wing, and the connecting part of different single cell structures 1 also needs to be improved in design, the inventor creatively proposes to use the discrete assembly method to realize the rapid assembly of the morphing wing. That is, first, the chiral structure 11 and the zero Poisson's ratio structure 12 are improved in the above manner, then the chiral structure 11 and the zero Poisson's ratio structure 12 are connected to form the single cell structure 1, and finally the single cell structures 1 are connected to form the wing body 10 of the morphing wing.

[0073] For example, each single cell structure 1 comprises two chiral structures 11 and four zero Poisson's ratio structures 12. The chiral structures 11 and the zero Poisson's ratio structures 12 are connected through the first connecting part 112 and the second connecting part 121. The four first rivet holes 112b of the first chiral structure 11 are connected with the fourth rivet holes 121b at one end of the four zero Poisson's ratio structures 12 in sequence, and the four first rivet holes 112b of the second chiral structure 11 are connected with the fourth rivet holes 121b at the other end of the four zero Poisson's ratio structures 12 in sequence. The rivet holes are fixed by rivets to form the single cell structure 1 as shown in FIG. 4. Figure 6

[0074] Since the sizes of the selected chiral structures 11 and zero Poisson's ratio structures 12 are not completely the same due to the different stress degrees of different parts of the wing body 10, the sizes of the single cell structures 1 obtained through the above connection are also not completely the same. Each single cell structure 1 of the same size is connected to form a constituent unit. Then, different sizes of constituent units are installed in different parts according to the different deformation needs of the wing body 10 in the actual flight process, and multiple constituent units are connected to form the morphing wing.

[0075] ​The way of connecting each same size of the unit cell structure 1 to form a component unit includes two kinds, one is to realize the connection of two unit cell structures 1 through the zero Poisson's ratio structure 12, and the other is to realize the connection of two unit cell structures 1 through the chiral structure 11. For example, if the connection of two unit cell structures 1 is realized through the zero Poisson's ratio structure 12, then the two zero Poisson's ratio structures 12 are connected together through the rivet and the first rivet hole 112a, and then the two unit cell structures 1 are connected together. Similarly, if the connection of two unit cell structures 1 is realized through the chiral structure 11, then the two chiral structures 11 are connected together through the rivet and the third rivet hole 121a, and then the two unit cell structures 1 are connected together. In addition, the component unit is also connected through the above-mentioned way, and finally the fuselage 10 of the morphing wing is formed.

[0076] As shown in Figure 9 The embodiment of the present application provides an assembly method of a morphing wing of an airplane, which is applied to the morphing wing of the airplane mentioned in any one of the above-mentioned embodiments, and the method comprises the following steps:

[0077] Step S1, connecting the chiral structure 11 and the zero Poisson's ratio structure 12 to obtain a unit cell structure 1.

[0078] Step S2, connecting a plurality of unit cell structures 1 to obtain a fuselage 10.

[0079] Step S3, connecting the leading edge 20, the fuselage 10 and the trailing edge 30 to obtain the morphing wing.

[0080] It can be understood that the method embodiment provided by the embodiment of the present application and the above-mentioned device embodiment belong to the same inventive concept, so they have the same beneficial effects, which will not be repeated here.

[0081] It should be noted that in this paper, relationship terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between the entities or operations. Moreover, the terms "include", "contain" or any other variants thereof are intended to cover non-exclusive inclusion, so that the process, method, article or equipment including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or equipment. Without more limitation, the element defined by the statement "including a..." does not exclude the presence of other identical elements in the process, method, article or equipment including the element.

[0082] It should be pointed out finally that the above embodiments are only used to illustrate the technical solutions of the present application, but not to limit the same; and although the present application has been described in detail with reference to the foregoing embodiments, it should be appreciated by those skilled in the art that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features thereof can be replaced equivalently; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A variant wing for an aircraft, characterized in that, It includes a leading edge, a wing body, and a trailing edge connected in sequence. The wing body includes multiple unit cell structures, with adjacent unit cell structures interconnected. Each unit cell structure includes interconnected chiral structures and zero Poisson's ratio structures. All of the chiral structures are disposed on the transverse section of the morphing wing, and each chiral structure has tensile-rotational characteristics to enable the morphing wing to change camber when subjected to tensile or compressive loads. All of the zero Poisson's ratio structures are disposed on the longitudinal section of the morphing wing, and each of the zero Poisson's ratio structures has tensile deformation characteristics so that the morphing wing varies in span when subjected to tensile or compressive loads; Each of the zero Poisson's ratio structures is a rhombic configuration, and each of the zero Poisson's ratio structures is provided with two second connecting parts; Each of the second connecting portions is disposed at the two acute-angled ends of the zero Poisson's ratio structure; The second connecting part is used to connect two adjacent zero Poisson's ratio structures by means of a rivet, or to connect one chiral structure and one zero Poisson's ratio structure by means of a rivet; Each of the second connecting parts includes a third rivet hole and a fourth rivet hole. One end of the third rivet hole is connected to an acute angle end, and the other end is connected to the fourth rivet hole. The third rivet hole and the acute angle end are located on the same plane, and the plane where the third rivet hole is located is at a 45-degree angle to the plane where the fourth rivet hole is located.

2. The variant wing of the aircraft according to claim 1, characterized in that, Each of the chiral structures is a four-ligament configuration, and each of the chiral structures is provided with four first connecting parts; Each of the first connecting portions is disposed at the end of a ligament in the chiral structure; The first connecting portion is used to connect two adjacent chiral structures by means of a rivet, or to connect one chiral structure and one zero Poisson's ratio structure by means of a rivet.

3. The variant wing of the aircraft according to claim 2, characterized in that, Each of the first connecting parts includes a first rivet hole and a second rivet hole. One end of the first rivet hole is connected to the ligament, and the other end is connected to the second rivet hole. The first rivet hole and the ligament are located in the same plane, and the plane where the second rivet hole is located is at a 45-degree angle to the plane where the first rivet hole is located.

4. The variant wing of the aircraft according to claim 3, characterized in that, Each of the said unit cell structures includes two of the said chiral structures and four of the said zero Poisson's ratio structures; The four second rivet holes of the first chiral structure are sequentially connected to the fourth rivet holes at one end of the four zero Poisson's ratio structures, and the four second rivet holes of the second chiral structure are sequentially connected to the fourth rivet holes at the other end of the four zero Poisson's ratio structures.

5. The variant wing of the aircraft according to any one of claims 1-4, characterized in that, The unit cell structures are not all the same size. Each unit cell structure of the same size is connected to each other to form a component unit. Multiple component units are connected to each other to form the variant wing.

6. A method for assembling a variant wing of an aircraft as described in any one of claims 1-4, characterized in that, include: By connecting the chiral structure and the zero Poisson's ratio structure, a single-cell structure is obtained; The wing body is obtained by connecting multiple of the aforementioned unit cell structures; The leading edge, the wing body, and the trailing edge are connected to obtain the variant wing.

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