Skin and aircraft

Abstract

The application relates to a skin and an aircraft, the skin comprising, in order along the thickness direction, a surface layer, a buffer layer, a tension layer and a support layer, the buffer layer and the tension layer each comprising at least one pleat structure, the pleat structure comprising a plurality of bends so that the unfolded length of the pleat structure is greater than the length covered by the pleat structure, and the unfolded length of the buffer layer is less than the unfolded length of the tension layer. The above scheme, when the pleat structure is stressed, the pre-pleated structure is unfolded to bear the local impact load with more area, the influence of the local dynamic change of the load on the skin is reduced, part of the impact force is consumed through the unfolding of the pleat structure, the size of the impact force required for tearing the skin is increased, the impact resistance is better, the structural integrity of the skin can be better maintained, the energy absorption efficiency of the fuselage structure during the water landing process of the aircraft is facilitated, the anti-crash capability of the aircraft during the water landing process is improved, and thus the safety of passengers and equipment is ensured as much as possible.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft, in particular to a skin and an aircraft. BACKGROUND

[0002] Water ditching is an emergency landing scenario that must be considered for aircraft flying across water, although the system reliability of existing aircraft is extremely high, but the water ditching is clearly required for airworthiness compliance verification in the civil aircraft airworthiness regulations of various countries. After the aircraft touches water, the water load first acts on the skin, and the skin deforms greatly in the process of absorbing impact energy, and transmits the impact load to the energy-absorbing framework structure of the fuselage. If the tension skin can ensure the structural integrity in this process, it can improve the crashworthiness of the aircraft. The load changes dynamically during the water landing process, and the dynamic deformation of the skin generated thereby will affect the action of the local load, which may cause the tension skin to be damaged in the local heavily loaded area. The existing tension skin has the problems of poor buffering performance and easy damage, which seriously weakens the energy absorption efficiency of the fuselage structure and endangers the safety of passengers and equipment. SUMMARY

[0003] Therefore, it is necessary to provide a skin and an aircraft aiming at the problems of poor buffering performance and easy damage of the skin.

[0004] A skin includes, in order along a thickness direction, a surface layer, a buffer layer, a tension layer and a support layer, the buffer layer and the tension layer each include at least one pleat structure, the pleat structure includes a plurality of folds such that an unfolded length of the pleat structure is greater than a length covered by the pleat structure, and the unfolded length of the buffer layer is less than the unfolded length of the tension layer.

[0005] In one of the embodiments, in a transverse direction perpendicular to the thickness direction, the skin includes laminated portions and interlayer portions arranged alternately, the pleat structure is located in the interlayer portion, and the pleat structure extends along a longitudinal direction, the longitudinal direction being perpendicular to the thickness direction and the transverse direction.

[0006] In one of the embodiments, the buffer layer adopts a fiber reinforced composite material, and a fiber direction of the buffer layer is arranged along the transverse direction.

[0007] In one of the embodiments, the tension layer adopts a fiber reinforced composite material, and a fiber direction of the tension layer is arranged along the transverse direction and / or the longitudinal direction.

[0008] In one of the embodiments, the buffer layer is provided with first pleats, the tension layer is provided with second pleats, and an unfolded length of the second pleats is greater than an unfolded length of the first pleats.

[0009] In one of the embodiments, the thickness of the tension layer is greater than the thickness of the buffer layer.

[0010] In one of the embodiments, the buffer layer and the tension layer each comprise a connecting section connected between adjacent corrugated structures, the corrugated structures being convexly arranged towards a direction away from the surface layer and at least partially superimposed on the connecting sections, the corrugated structures and the connecting sections on both sides thereof forming openings towards the surface layer.

[0011] In one of the embodiments, the buffer layer and the tension layer each comprise a connecting section connected between adjacent corrugated structures, the corrugated structures being convexly arranged towards a direction away from the surface layer and at least partially superimposed on the connecting sections, the corrugated structures and the connecting sections on both sides thereof forming openings towards the surface layer.

[0012] In one of the embodiments, the elongation at break of the buffer layer and the tension layer is greater than the elongation at break of the surface layer.

[0013] In one of the embodiments, the elongation at break of the tension layer is greater than the elongation at break of the buffer layer.

[0014] An aircraft comprising a fuselage and a skin as in any one of the preceding embodiments, the support layer of the skin being attached to a surface of the fuselage.

[0015] The skin provided in the above solutions has the corrugated structures with an unfolding length greater than a covering length, when the corrugated structures are subjected to force, the pre-corrugated structures are unfolded to bear the local impact load with more area, reducing the influence of local dynamic changes of the load on the skin, and part of the impact force is consumed by the unfolding of the corrugated structures, increasing the size of the impact force required for tearing of the skin, having better impact resistance, better maintaining the structural integrity of the skin, and being conducive to ensuring the energy absorption efficiency of the fuselage structure during water landing of the aircraft, improving the crashworthiness of the aircraft during water landing, and thus ensuring the safety of passengers and equipment as much as possible. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 FIG. 1 is a structural schematic diagram of a skin in an embodiment of the present application.

[0017] FIG. 1 is a structural schematic diagram of a skin in an embodiment of the present application.

[0018] 100, skin; 110, laminated part; 120, sandwich part; 130, surface layer; 141, buffer layer; 1411, first corrugation; 142, tension layer; 1421, second corrugation; 143, corrugated structure; 1431, opening; 144, connecting section; 150, support layer. DETAILED DESCRIPTION

[0019] In order to make the above objectives, features and advantages of the present application more clear and comprehensible, the specific embodiments of the present application will be described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, the present application can be practiced in a number of different ways beyond the specific embodiments described herein and by one of ordinary skill in the art without departing from the spirit and scope of the present application, and it is therefore intended that all such variations be considered as falling within the scope of the present application. Accordingly, the present application should not be limited by the following description and examples.

[0020] In the description of the present application, it should be understood that, if there are terms such as "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. appear, these terms indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0021] In addition, if the terms "first", "second" appear, these terms are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implying the number of technical features indicated. Therefore, the features limited by "first", "second" can include at least one of the features explicitly or implicitly. In the description of the present application, if the term "a plurality of" appears, the meaning of "a plurality of" is at least two, such as two, three, etc., unless otherwise specifically limited.

[0022] In the present application, unless otherwise specifically defined and limited, if the terms "mounting", "connecting", "connecting", "fixing" and the like appear, these terms should be broadly understood. For example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements, unless otherwise specifically limited. For those of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0023] In the present application, unless specifically stated and limited otherwise, if there is a description of a first feature "on" or "under" a second feature, etc., it can mean that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature "on", "above" and "over" the second feature can be that the first feature is directly above or obliquely above the second feature, or only means that the first feature is horizontally higher than the second feature. The first feature "under", "below" and "under" the second feature can be that the first feature is directly below or obliquely below the second feature, or only means that the first feature is horizontally lower than the second feature.

[0024] It should be noted that if an element is referred to as being "fixed" or "attached" to another element, it can be directly on the other element or there can be an intervening element. If an element is referred to as being "connected" to another element, it can be directly connected to the other element or there can be an intervening element. If present, the terms "vertical", "horizontal", "up", "down", "left", "right", and similar terms as used herein are for purposes of explanation only and are not intended to be limiting.

[0025] The present application provides an aircraft, comprising a fuselage and a skin 100 in any of the embodiments described below, and the skin 100 is attached to the surface of the fuselage. The aircraft can be a civil passenger aircraft, freighter, etc., without limitation.

[0026] Referring to Figure 1 , Figure 1 The structure of the skin 100 in an embodiment of the present application is shown, and in combination with Figure 1 In the present application, unless specifically stated and limited otherwise, if there is a description of a first feature "on" or "under" a second feature, etc., it can mean that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature "on", "above" and "over" the second feature can be that the first feature is directly above or obliquely above the second feature, or only means that the first feature is horizontally higher than the second feature. The first feature "under", "below" and "under" the second feature can be that the first feature is directly below or obliquely below the second feature, or only means that the first feature is horizontally lower than the second feature.

[0027] As Figure 1As shown in the figure, an embodiment of this application provides a skin 100, which includes a surface layer 130, a buffer layer 141, a tension layer 142, and a support layer 150 stacked sequentially along the thickness direction. The order of the skin 100 in the thickness direction is as follows: the buffer layer 141 covers the surface layer 130, the tension layer 142 covers the buffer layer 141, and the support layer 150 covers the tension layer 142. The surface layer 130 is the outer surface, i.e., the surface that bears the force first when the skin 100 is under stress. During normal flight, each layer of the skin 100 participates in bearing aerodynamic loads. The surface layer 130 has the function of isolating the external environment and protecting the internal layers of the skin 100 (i.e., the buffer layer 141, the tension layer 142, and the support layer 150). The support layer 150 is the inner surface, and it is in contact with the surface of the aircraft skin support structure (such as beams or ribs). The buffer layer 141 and tension layer 142 are sandwiched between the surface layer 130 and the support layer 150, and play a role in buffering and absorbing energy to improve the impact resistance of the skin 100.

[0028] Understandably, although the skin 100 comprises a layered surface layer 130, a buffer layer 141, a tension layer 142, and a support layer 150 in the thickness direction, after being stacked, the skin 100 is co-cured into a single integral structure. When the skin 100 is subjected to impact, such as when an aircraft lands on water, the skin 100 begins to deform outward toward the interior of the aircraft after being loaded. At this time, because the skin 100 is co-cured into a single integral structure, the surface layer 130, buffer layer 141, tension layer 142, and support layer 150 in the skin 100 are all subjected to in-plane loads and undergo tensile deformation.

[0029] like Figure 1 As shown, both the buffer layer 141 and the tension layer 142 include at least one pleated structure 143. The pleated structure 143 includes multiple bends so that the unfolded length of the pleated structure 143 is greater than the length covered by the pleated structure 143. When the pleated structure 143 is subjected to force, the bends of the pleated structure 143 are unfolded to consume part of the impact force. The impact energy is consumed through the pre-folded part in its pleated structure 143, thereby increasing the magnitude of the impact force required for the skin 100 to tear, and unfolding the pre-pleated structure to bear the local impact load with more area, reducing the impact of local dynamic changes in load on the skin 100.

[0030] When the skin 100 is subjected to an impact force, the impact force tends to cause the skin 100 to stretch and tear. When the impact force acts on the pleated structure 143, it tends to cause the pleated structure 143 to unfold. Thus, the unfolding of the pleated structure 143 consumes part of the impact force, thereby increasing the magnitude of the impact force required for the skin 100 to tear. In this way, the pleated structure 143 can buffer and absorb energy, increasing the possibility of maintaining the structural integrity of the skin 100 when subjected to force, and thus improving the aircraft's crash resistance during water landing.

[0031] As shown in the drawings, Figure 1 In one embodiment, the skin 100 includes laminated portions 110 and interlayer portions 120 arranged alternately in the transverse direction perpendicular to the thickness direction, and the corrugated structure 143 is located in the interlayer portions 120. The interlayer portions 120 of the skin 100 are used to absorb the energy generated by the impact, and the load is transmitted to the fuselage energy-absorbing structure through the laminated portions 110. After the skin 100 is loaded, it begins to deform out of the plane towards the inside of the aircraft. The corrugated structure 143 extends in the longitudinal direction, and when the skin 100 is subjected to an impact force, the force direction of the skin 100 is in the plane of the transverse and longitudinal directions. Since the corrugated structure 143 extends in the longitudinal direction, the transverse direction is the main direction of deformation of the skin 100.

[0032] In one embodiment, the buffer layer 141 is provided with first corrugations 1411, and the tension layer 142 is provided with second corrugations 1421, so as to form a two-stage buffer structure through the buffer layer 141 and the tension layer 142, so as to more effectively cope with complex working conditions during the water landing of the aircraft. The buffer layer 141 provides primary protection for the tension layer 142, and after the impact load capacity is weakened by the buffer layer 141, the tension layer 142 can withstand more impact, so as to achieve the structural completeness of the tension layer 142 with a higher probability. At the same time, the buffer layer 141 also protects the tension layer 142 to a certain extent, reducing the damage of foreign matter to the tension layer 142 during water landing.

[0033] In some embodiments, the deployment length of the buffer layer 141 is less than the deployment length of the tension layer 142. When the impact load is large, since the deployment length of the buffer layer 141 is less than the deployment length of the tension layer 142, the buffer layer 141 will reach the strength limit earlier than the tension layer 142, and then break. Then the tension layer 142 will continue to deploy to absorb the remaining impact load capacity.

[0034] As shown in the drawings, Figure 1 In one embodiment, the deployment length of the second corrugations 1421 is greater than the deployment length of the first corrugations 1411, so that when the number of the first corrugations 1411 and the second corrugations 1421 is comparable, the deployment length of the buffer layer 141 is less than the deployment length of the tension layer 142. At the same time, the deployment length of the second corrugations 1421 is greater than the deployment length of the first corrugations 1411, which also makes the deployment speed of the buffer layer 141 and the tension layer 142 not related when they are stressed and deployed, avoiding the synchronous deployment speed caused by the consistent deployment length of the first corrugations 1411 and the second corrugations 1421, and avoiding the decrease in the impact load capacity that can be absorbed when the first corrugations 1411 and the second corrugations 1421 are deployed synchronously.

[0035] Optionally, as shown in the drawings, Figure 1In the embodiment shown, two second folds 1421 and four first folds 1411 are provided in one interlayer 120. In other embodiments, the number of first folds 1411 and second folds 1421 is not limited, and there is no correlation between the number of first folds 1411 and the number of second folds 1421.

[0036] In one embodiment, the thickness of the tension layer 142 is greater than the thickness of the buffer layer 141. Because the ply thickness of the buffer layer 141 is less than the ply thickness of the tension layer 142, the buffer layer 141 will drive the tension layer 142 to unfold through the interlayer force between the plies 100, so as to absorb impact energy through the buffer layer 141.

[0037] In one embodiment, the surface layer 130 is made of fiber-reinforced composite material, and the fiber direction of the surface layer 130 is arranged at an angle with the transverse direction. The fiber direction is a very important element in the composite laminated structure. The material direction of the unit serves as a reference for the ply angle, which can determine the fiber direction of each ply. Generally, the fiber direction of each ply is the material direction of this ply. All fibers extend in the same direction, and the strength and stiffness in the fiber path and extension direction are fully utilized. In this specification, the fiber direction is the fiber extension direction.

[0038] In this embodiment, the surface layer 130 is made of carbon fiber reinforced resin-based composite material. The carbon fiber reinforced resin-based composite material is a resin-based composite material reinforced by carbon fiber and its products. It has high specific strength and modulus, excellent creep resistance and fatigue resistance, low friction coefficient and wear rate, self-lubricating property, and excellent chemical corrosion resistance. It is suitable for the outer side of the skin 100 to isolate the external environment and protect the internal plies of the skin 100, i.e., the buffer layer 141, the tension layer 142, and the support layer 150.

[0039] In this embodiment, the surface layer 130 includes two layers of carbon fiber reinforced resin-based composite material, and the angles between the fiber directions of the two layers of carbon fiber reinforced resin-based composite material and the transverse direction are 45° and -45°, respectively, so that the surface layer 130 has good shear resistance.

[0040] The buffer layer 141 and the tension layer 142 are both made of fiber-reinforced composite material. In this embodiment, the buffer layer 141 and the tension layer 142 are made of different material systems. Alternatively, in this embodiment, the elongation at break of the tension layer 142 is greater than the elongation at break of the buffer layer 141, so that the fold structure 143 of the buffer layer 141 is unfolded faster and absorbs a portion of the impact energy first. In other embodiments, the elongation at break of the tension layer 142 can be equal to the elongation at break of the buffer layer 141.

[0041] The fiber direction of the buffer layer 141 is arranged along the transverse direction. Exemplarily, the buffer layer 141 adopts aramid fiber reinforced resin-based composite material, which has high specific modulus, good specific strength, excellent impact resistance, and the like. The fiber direction of the buffer layer 141 is arranged along the transverse direction, so that when the skin 100 is subjected to in-plane tensile deformation, the advantage of high breaking elongation of the buffer layer 141 is fully utilized, and premature structural failure of the buffer layer 141 before the surface layer is damaged is avoided. In the embodiment, the buffer layer 141 is one layer of aramid fiber reinforced resin-based composite material.

[0042] The fiber direction of the tension layer is arranged along the transverse direction and / or the longitudinal direction. Exemplarily, the tension layer 142 adopts ultra-high molecular weight polyethylene fiber reinforced resin-based composite material. Ultra-high molecular weight polyethylene is polyethylene with a molecular weight of 1 million to 5 million, which is the third generation of high-performance fibers after carbon fiber / aramid fiber, and has excellent impact resistance, low-temperature resistance, wear resistance, chemical corrosion resistance, self-lubrication, and impact energy absorption performance.

[0043] In the embodiment, the tension layer 142 adopts four layers of ultra-high molecular weight polyethylene fiber reinforced resin-based composite material, and the fiber directions of the four layers of ultra-high molecular weight polyethylene fiber reinforced resin-based composite material are arranged along the transverse direction and the longitudinal direction, respectively. The extension directions of adjacent ultra-high molecular weight polyethylene fiber reinforced resin-based composite materials are different, and the fiber direction of the ultra-high molecular weight polyethylene fiber reinforced resin-based composite material covering the buffer layer 141 is consistent with the fiber direction of the buffer layer 141, so that the tension layer 142 can absorb more impact force.

[0044] In one embodiment, the support layer 150 adopts fiber reinforced composite material, and the fiber direction of the support layer 150 is arranged at an angle with the transverse direction and / or the fiber direction of the support layer 150 is arranged along the transverse direction.

[0045] In the embodiment, the support layer 150 adopts three layers of carbon fiber reinforced resin-based composite material, and the angles between the extension directions of the three layers of carbon fiber reinforced resin-based composite material and the transverse direction are 45°, 0°, and -45°, respectively.

[0046] In one embodiment, the buffer layer 141 and the tension layer 142 further comprise a connecting section 144 connected between adjacent corrugated structures 143, the corrugated structures 143 are convex and at least partially stacked on the connecting section 144 in a direction away from the surface layer 130, the corrugated structures 143 are connected to the connecting section 144 on both sides to form an opening 1431 in a direction towards the surface layer 130, when the surface layer 130 is subjected to force, the force direction is perpendicular to the surface layer 130 and away from the surface layer 130, at this time, the corrugated structures 143 will gradually increase the transverse length at the opening 1431 under the action of impact force to unfold and absorb the impact force during the unfolding process.

[0047] In one embodiment, the elongation at break of the buffer layer 141 and the tension layer 142 is greater than the elongation at break of the surface layer 130, the elongation at break refers to the ratio of the elongation length after stretching to the length before stretching when the fiber is subjected to external force until it is pulled apart. The elongation at break is generally the relative elongation at break, that is, the ratio of the elongation to the initial length when the fiber breaks, expressed in percentage. It is an index to characterize the softness and elasticity of the fiber. The greater the elongation at break, the better the softness and elasticity. The elongation at break of the buffer layer 141 and the tension layer 142 is greater than the elongation at break of the surface layer 130, so that when the buffer layer 141, the tension layer 142 and the surface layer 130 are subjected to the same impact force, the surface layer 130 will break first than the buffer layer 141 and the tension layer 142.

[0048] When the skin 100 is subjected to force, the skin 100 begins to deform out-of-plane towards the inside of the aircraft, the surface layer 130, the buffer layer 141, the tension layer 142 and the support layer 150 in the skin 100 are subjected to in-plane load and produce tensile deformation, because the elongation at break of the surface layer 130 is low, the surface layer 130 will break first.

[0049] When the skin 100 is impacted by a force, for example when the aircraft is landing on water, the sandwich part 120 of the skin 100 absorbs the energy generated by the impact and transmits the load to the fuselage energy-absorbing structure through the laminated part 110. After the skin 100 is loaded, the skin 100 begins to deform out of the plane in the direction of the interior of the aircraft. At this time, since the skin 100 is co-cured as an integral structure, the surface layer 130, the buffer layer 141, the tension layer 142 and the support layer 150 in the skin 100 are all subjected to in-plane loads and produce tensile deformation. According to the elongation at break characteristics of their own materials, the surface layer 130, the buffer layer 141, the tension layer 142 and the support layer 150 have different performances. Since the surface layer 130 has a low elongation at break, the surface layer 130 will break first, and then the support layer 150 breaks. At the same time, the buffer layer 141 and the tension layer 142 consume impact energy by the pre-folded part of the wrinkle structure 143 and unfold the pre-wrinkled structure. Since the buffer layer 141 has a smaller ply thickness than the tension layer 142, the wrinkle structure 143 of the buffer layer 141 is unfolded faster and absorbs a part of the impact energy first. Through the interlaminar force between the plies, the buffer layer 141 will drive the tension layer 142 to unfold to absorb the impact energy through the buffer layer 141.

[0050] When the impact load is large, since the unfolding length of the buffer layer 141 is longer than that of the tension layer 142, the buffer layer 141 will reach the strength limit earlier than the tension layer 142, and then break. Then the tension layer 142 will continue to unfold to absorb the remaining capacity of the impact load. And after the weakening of the impact load capacity by the buffer layer 141, the tension layer 142 can withstand more impact. At the same time, the buffer layer 141 also protects the tension layer 142 to some extent, reducing the damage of foreign matter to the tension layer 142 during the landing on water.

[0051] The skin 100 provided in the above scheme sets the wrinkle structure 143 with an unfolding length greater than the covering length. When the wrinkle structure 143 is forced, the pre-wrinkled structure is unfolded to bear the local impact load with more area, reduce the influence of local dynamic changes of the load on the skin 100, and consume part of the impact force through the unfolding of the wrinkle structure 143, thereby increasing the size of the impact force required for tearing the skin 100, having better impact resistance, better maintaining the structural integrity of the skin 100, and being conducive to protecting the energy-absorbing efficiency of the fuselage structure during the water landing of the aircraft, improving the crashworthiness of the aircraft during the water landing, and thus protecting the safety of the passengers and equipment as much as possible.

[0052] The technical features of the above-described embodiments can be combined in any manner. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described, but as long as the combinations of the technical features do not exist contradictions, they should be considered as the scope of the present disclosure.

[0053] The above-described embodiments are merely illustrative of several embodiments of the present application, which are described in more detail and in a more specific and detailed manner, but should not be construed as limiting the scope of the patent application. It should be noted that, for those of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent of the present application should be subject to the appended claims.

Claims

1. A skin characterised in that, The skin comprises, in sequence along a thickness direction, a surface layer, a buffer layer, a tension layer and a support layer, the buffer layer and the tension layer each comprise at least one pleat structure, the pleat structure comprises a plurality of folds such that an unfolded length of the pleat structure is greater than a length covered by the pleat structure, and an unfolded length of the buffer layer is less than an unfolded length of the tension layer In a transverse direction perpendicular to the thickness direction, the skin comprises alternating laminated portions and interlayer portions, the pleat structure is located in the interlayer portion, and the pleat structure extends along a longitudinal direction, the longitudinal direction being perpendicular to the thickness direction and the transverse direction The buffer layer is provided with first pleats, the tension layer is provided with second pleats, and an unfolded length of the second pleats is greater than an unfolded length of the first pleats The buffer layer and the tension layer each comprise a connecting section, the connecting section is connected between adjacent pleat structures, the pleat structure is convex towards a direction away from the surface layer and is at least partially laminated to the connecting section, and the pleat structure and the connecting sections on both sides thereof form openings towards the surface layer The buffer layer and the tension layer each have an elongation at break greater than an elongation at break of the surface layer The tension layer has an elongation at break greater than an elongation at break of the buffer layer 2. The skin of claim 1, wherein The buffer layer is made of a fiber-reinforced composite material, and a fiber direction of the buffer layer is arranged along the transverse direction 3. The skin of claim 1, wherein, The tension layer is made of a fiber-reinforced composite material, and a fiber direction of the tension layer is arranged along the transverse direction and / or the longitudinal direction 4. The skin of claim 1, wherein The tension layer has a thickness greater than a thickness of the buffer layer 5. An aircraft, characterized in that A machine body and a skin as claimed in any one of claims 1-4, the support layer of the skin is attached to a surface of the machine body.

Images