Novel bionic anti-layering composite material laminated plate

Abstract

The invention discloses a novel bionic anti-layering composite material laminated plate. A plurality of through holes are formed in a composite material lamination layer, and bidirectional wintercherry squid tentacle barb structure rods are arranged in the through holes; a plurality of barb structures are fixed on the cylindrical surface of the bidirectional wintercherry squid tentacle barb structure imitating rod, and each barb structure is composed of a main barb and two auxiliary hooks which are located on the two sides of the main barb and are integrally formed; the cylindrical surface of the rod body I and the cylindrical surface of the rod body II are respectively and fixedly provided with a hooking structure which consists of a plurality of nanotubes and is used for simulating bird wing feather middle feather branchlet; a connecting structure is filled between the bidirectional wintercherry squid tentacle barb structure rod and the hole wall in the through hole, the connecting structure is formed by mixing resin and a plurality of fibers, and the fibers are wound on the corresponding main barbs, auxiliary hooks or nanotubes. The composite material has relatively good layering resistance, and can effectively prevent generation or expansion of interlayer cracks when being impacted, so that layering damage is reduced.

Description

Technical Field

[0001] The invention belongs to the field of aerospace technology, and in particular relates to a novel bionic anti-delamination composite material laminate. Background Art

[0002] Composite materials have been widely used in the field of aerospace due to their excellent performance. With the advancement of manufacturing technology and the improvement of production capacity, more and more important parts on aircraft are made of composite materials. Composite components have good durability, reliability, corrosion resistance and specific strength. The amount of composite materials used in large passenger aircraft has become an important parameter to measure the performance superiority of commercial aircraft. The wall panel of a wide-body aircraft is a very important component and the main load-bearing structure of the aircraft. In addition to bearing and transmitting conventional aerodynamic loads, its main function is to protect the interior of the aircraft and passengers from the harsh external environment. Composite laminates are widely used in wall panels. However, during use, composite laminates will have different forms of delamination damage from traditional metal materials. Delamination damage occurs inside the structural layers and is not easy to be found. It will continue to expand under continuous loading, resulting in a decrease in the overall stiffness and strength of the wall panel structure. When the delamination damage reaches a certain extent, the material will fail as a whole, resulting in serious consequences. Therefore, it is urgent to design the structure of composite laminates to improve their ability to resist delamination, effectively prevent the expansion of interlaminar cracks, play a role in resisting delamination, and thus reduce the damage caused by delamination. Summary of the invention

[0003] The purpose of the invention is to overcome the deficiencies of the prior art and to provide a novel bionic anti-delamination composite laminate.

[0004] To achieve the above object, the present invention adopts the following technical solutions:

[0005] The invention discloses a novel bionic anti-delamination composite laminate, comprising a composite laminate layer, a bidirectional imitation giant squid tentacle barb structure rod, an imitation bird wing feather middle feather barb hook connection structure and a connection structure.

[0006] The composite laminate layer is provided with a plurality of through holes arranged in an array, and a bidirectional imitation giant squid tentacle barb structure rod is provided in each through hole. The bidirectional imitation giant squid tentacle barb structure rod comprises a main body, a barb structure and an interlocking structure. The main body is composed of a rod body 1 and a rod body 2 coaxially arranged with the corresponding through holes, and a plurality of barb structure groups uniformly distributed along the circumferential direction are fixed on the cylindrical surfaces of the rod body 1 and the rod body 2, and the barb structure group is composed of a plurality of barb structures uniformly distributed along the axial direction, and the barb structure is composed of an integrally formed main barb and two auxiliary hooks, and the two auxiliary hooks are located on both sides of the main barb and are perpendicular to the central axis of the main body. The main barbs on the rod body 1 and the main barbs on the rod body 2 are arranged opposite to each other along the axial direction of the main body. The interlocking structure includes a lock head and a lock chamber. The lock head is fixed to one end of the rod body one close to the rod body two. A lock hole is provided on one end of the rod body two close to the rod body one, and a lock chamber connected to the lock hole is provided. The lock head passes through the lock hole and is embedded in the lock chamber, and the two end surfaces of the rod body one and the rod body two are in contact with each other.

[0007] The cylindrical surfaces of the rod body 1 and the rod body 2 are both provided with hook-connecting structures imitating the barbs in the wing feathers of birds. The hook-connecting structures imitating the barbs in the wing feathers of birds are composed of multiple nanotubes arranged at intervals, and each nanotube is fixed obliquely on the cylindrical surface of the rod body 1 or the rod body 2. A connecting structure is filled between the main body and the wall of the through hole in each through hole, and each main body is fixed in each through hole through the corresponding connecting structure. The connecting structure is formed by mixing resin and multiple fibers, and each fiber is wound around the corresponding main hooks, each auxiliary hook or each nanotube; the resin fills the gap between each main body and the corresponding through hole to fix the main body in the through hole.

[0008] Preferably, the composite laminate layer is formed by stacking multiple layers of unidirectional carbon fiber resin composite materials at a helix angle of 45°.

[0009] Preferably, the through holes are perpendicular to the composite laminate layers.

[0010] Preferably, the thickness of the composite laminate layer is greater than 3 mm, the diameter of the bidirectional imitation giant squid tentacle barb structural rod is 0.1 mm to 1 mm, and the diameter of the through hole is 0.1 mm larger than the diameter of the bidirectional imitation giant squid tentacle barb structural rod.

[0011] Preferably, the volume of the bidirectional giant squid tentacle barb structural rod accounts for 2.0% of the volume of the composite laminate layer.

[0012] Preferably, the materials of the rod body 1 and the rod body 2 are both carbon fiber-bismaleimide composite materials, and the nanotubes are single-walled carbon fiber nanotubes.

[0013] Preferably, the nanotubes are adhered to the cylindrical surface of the first rod or the second rod by a mixed solution of an acetone solution and an epoxy resin without a curing agent.

[0014] Preferably, the fiber is aramid pulp fiber, the resin is epoxy resin, and the concentration of the aramid pulp fiber in the connection structure is 2.0%.

[0015] Preferably, the composite laminate layer is in a prepreg state when each through hole is opened, and when the composite laminate layer is in the prepreg state, a connecting structure and a combined structure consisting of a bidirectional giant squid tentacle barb structure rod and a bird wing feather barb hook structure are injected into the through hole in sequence.

[0016] More preferably, the process of placing the combined structure into the corresponding through hole is: inserting rod body 1 and rod body 2 from both ends of the corresponding through hole, allowing the lock head to pass through the lock hole and embed into the lock chamber, and allowing rod body 1 and rod body 2 to rotate relative to each other so that the lock head is interlocked with the lock chamber.

[0017] The present invention has the following beneficial effects:

[0018] 1. The present invention has a good ability to resist delamination, thereby inhibiting the generation of interlayer cracks or effectively preventing the expansion of interlayer cracks when delamination damage occurs, reducing delamination damage; specifically, the present invention forms a mechanical interlocking by connecting the barb structures of the bidirectional imitation giant squid tentacle barb structure rod and the nanotubes of the hook connection structure between the barbules in the wing feathers of birds with the fiber hooks in the connection structure, so that the energy consumed by pulling out each rod when the composite laminate is damaged is increased, thereby inhibiting the pulling out of the bidirectional imitation giant squid tentacle barb structure rod, improving the ability of the laminate to resist delamination, thereby inhibiting the generation or expansion of interlayer cracks; further, when the laminate is severely delaminated due to impact, the corresponding bidirectional imitation giant squid tentacle barb structure rod is used to prevent the laminate from being damaged. Part of the bidirectional imitation giant squid tentacle hook structure rod and each nanotube is pulled out, and interlaminar cracks appear in the resin around the pulled out parts of the bidirectional imitation giant squid tentacle hook structure rod and each nanotube. At this time, the two surfaces of the interlaminar crack are connected by the corresponding nanotubes and fibers like a bridge. The nanotubes and fibers play the role of a crack bridging mechanism, preventing the further opening and expansion of the interlaminar crack. At the same time, they share part of the stress concentration acting on the tip of the interlaminar crack, bear part of the tensile and shear stress, and friction and debonding occur at the interface in contact with the resin, consuming the energy of the interlaminar crack expansion, which increases the energy required for further expansion of the interlaminar crack, further inhibiting the expansion of the interlaminar crack and reducing the delamination damage.

[0019] 2. The present invention opens a plurality of through holes on the composite laminate layer, and arranges bidirectional imitation giant squid tentacle barb structure rods, imitation bird wing feather barb structure and connection structure in the through holes, without significantly increasing the overall weight of the laminate. Through the synergistic effect of the bidirectional imitation giant squid tentacle barb structure rods, imitation bird wing feather barb structure and connection structure, the laminate's anti-delamination ability is improved on the basis of ensuring the overall lightweight of the laminate, and the in-plane shear strength, interlaminar fracture toughness and impact damage resistance of the laminate are improved.

[0020] 3. In the present invention, the resin in the added connection structure fills the gaps in the composite laminate prepreg caused by the addition of the bidirectional imitation giant squid tentacle barb structure rods and the hook connection structure between the barbules in the bird wing feathers, forming a pure resin aggregation area, which effectively reduces the generation of low stiffness local areas on the laminate. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of the present invention;

[0022] Figure 2 It is a schematic diagram of stacking the layers of unidirectional carbon fiber resin composite materials in the composite material laminate layer of the present invention;

[0023] Figure 3 It is a schematic diagram of the structure of the composite material laminate layer in the present invention;

[0024] Figure 4 It is a schematic structural diagram of the bidirectional giant squid tentacle barb structural rod and the bird wing feather barb-to-barb hook connecting structure in the present invention;

[0025] Figure 5 It is a structural schematic diagram of the bidirectional giant squid tentacle barb structural rod when the rod body 1 and the rod body 2 are separated in the present invention;

[0026] Figure 6 for Figure 5 A top view of

[0027] Figure 7 It is a structural schematic diagram of the barb structure in the present invention;

[0028] Figure 8 It is a structural schematic diagram of the lock head and part of the rod body in the present invention;

[0029] Fig. 9 It is a schematic diagram of the structure of the lock hole, the lock chamber and part of the rod body 2 in the present invention;

[0030] Fig.10 for Fig. 9 A partial cross-sectional view of

[0031] Fig.11It is a schematic diagram of the structure of the composite material lamination layer and the connection structure in the present invention;

[0032] Fig.12 It is a schematic diagram of the combined structure of the present invention when it is placed in the corresponding through hole. DETAILED DESCRIPTION

[0033] The present invention is further described below in conjunction with the accompanying drawings.

[0034] like Figure 1 As shown, a novel bionic anti-delamination composite laminate of the present invention comprises a composite laminate layer 1, a bidirectional barb structure rod 2 imitating the tentacles of giant squid, a hook connection structure 3 imitating the inter-barb hook connection structure of bird wing feathers, and a connection structure 4.

[0035] like Figure 2 and Figure 3 As shown, the composite laminate layer 1 is formed by stacking multiple layers of unidirectional carbon fiber resin composite materials at a spiral angle of 45°; the composite laminate layer 1 is provided with a plurality of through holes arranged in an array (which can be opened by a needle), each through hole is perpendicular to the surface of the composite laminate layer 1, and each through hole is provided with a bidirectional imitation giant squid tentacle barb structural rod 2. Among them, the thickness of the composite laminate layer 1 is greater than 3mm, the diameter of the bidirectional imitation giant squid tentacle barb structural rod 2 is 0.1mm to 1mm, and the diameter of the through hole is 0.1mm larger than the diameter of the bidirectional imitation giant squid tentacle barb structural rod 2.

[0036] like Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 , Fig. 9 and Fig.10As shown, the bidirectional imitation giant squid tentacle barb structure rod 2 comprises a main body 201, a barb structure 205 and an interlocking structure 206. The main body 201 is composed of a rod body 1 203 and a rod body 204 coaxially arranged with the corresponding through hole, and a plurality of barb structure groups uniformly distributed along the circumferential direction are fixed on the cylindrical surfaces of the rod body 1 203 and the rod body 2 204, and the barb structure group is composed of a plurality of barb structures uniformly distributed along the axial direction, and the barb structure 205 is composed of an integrally formed main barb 207 and two auxiliary hooks 208, and the two auxiliary hooks 208 are located on both sides of the main barb 207 and are perpendicular to the central axis of the main body 201. The main barbs 207 on the rod body 1 203 and the main barbs 207 on the rod body 2 204 are arranged opposite to each other along the axial direction of the main body 201. The interlocking structure 206 includes a lock head 209 and a lock chamber 211. The lock head 209 is fixed to one end of the rod body 1 203 close to the rod body 204. The rod body 204 has a lock hole 210 at one end close to the rod body 1 203 and a lock chamber 211 connected to the lock hole 210. The lock head 209 passes through the lock hole 210 and is embedded in the lock chamber 211. The two end surfaces of the rod body 1 203 and the rod body 204 are fitted. The rod body 1 203 and the rod body 204 are made of carbon fiber-bismaleimide composite materials.

[0037] The cylindrical surfaces of rod body 1 203 and rod body 2 204 are both provided with hook-connecting structures 3 imitating the inter-barblets of bird wing feathers, which are composed of a plurality of nanotubes 202 arranged at intervals, and each nanotube 202 is fixed obliquely on the cylindrical surface of rod body 1 203 or rod body 2 204. A connecting structure 4 is filled between the main body 201 and the wall of the through hole in each through hole, and each main body 201 is fixed in each through hole through the corresponding connecting structure 4. Fig.11 As shown, the connection structure 4 is formed by mixing resin 302 and multiple fibers 301, and each fiber 301 is wound around the corresponding main hooks 207, each auxiliary hook 208 or each nanotube 202 to form a mechanical interlock, which inhibits the pullout of the rod body 1 203 and the rod body 2 204 when the composite laminate layer 1 is delaminated and damaged, thereby inhibiting the further expansion of the crack, and the resin 302 fills the gap between each main body 201 and the corresponding through hole, thereby fixing the main body 201 in the through hole. Among them, the nanotube 202 is a single-walled carbon fiber nanotube.

[0038] As a preferred embodiment, the nanotube 202 is adhered to the cylindrical surface of the rod 1 203 or the rod 2 204 by a mixed solution of acetone solution and epoxy resin without a curing agent.

[0039] As a preferred embodiment, the volume of the bidirectional giant squid tentacle barb structural rod 2 accounts for 2.0% of the volume of the composite laminate layer.

[0040] As a preferred embodiment, the fiber 301 is made of aramid pulp fiber, and the resin 302 is made of epoxy resin.

[0041] More preferably, the concentration of the aramid pulp fibers in the connecting structure 4 is 2.0%.

[0042] As a preferred embodiment, when the through holes are opened in the composite laminate layer, the unidirectional carbon fiber resin composite material is in a prepreg state (the state before the final hot molding process), and when the unidirectional carbon fiber resin composite material is in the prepreg state, the connecting structure 4 and the combined structure composed of a bidirectional giant squid tentacle barb structure rod 2 and a bird wing feather barb hook structure 3 are injected into the through hole in sequence (can be pressed in through a medical needle).

[0043] More preferably, the process of placing the combined structure into the corresponding through hole is as follows: Fig.12 As shown, the rod body 1 203 and the rod body 204 are inserted from both ends of the through hole, so that the lock head 209 passes through the lock hole 210 and is embedded in the lock chamber 211, and the rod body 1 203 and the rod body 204 are relatively rotated so that the lock head 209 and the lock chamber 211 are interlocked.

[0044] More preferably, when the unidirectional carbon fiber resin composite material is in a prepreg state, a connecting structure 4 and a combined structure composed of a bidirectional imitation giant squid tentacle hook structure rod 2 and an imitation bird wing feather barb-like hook connection structure 3 are sequentially injected into the through hole, and then the composite laminate layer 1, the bidirectional imitation giant squid tentacle hook structure rod 2, the imitation bird wing feather barb-like hook connection structure 3 and the connecting structure 4 are hot-molded to obtain a new type of bionic anti-delamination composite laminate in this embodiment.

[0045] The working principle of the novel bionic anti-delamination composite laminate of the present invention is as follows:

[0046] The present invention can be used to make the wall panels of wide-body passenger aircraft. When the present invention is impacted, the impact force is dispersed to the bidirectional imitation giant squid tentacle barb structure rod 2, the bird-like wing feather barb structure 3 and the connection structure 4 in each adjacent through hole. The barb structures 205 on the bidirectional imitation giant squid tentacle barb structure rod 2 and the bird-like wing feather barb structure 3 hook the fibers 301 in the connection structure 4 to form a mechanical interlock. At the same time, the main barbs 207 of the rod body 1 203 and the main barbs 207 of the rod body 2 204 on the bidirectional imitation giant squid tentacle barb structure rod 2 are arranged opposite to each other, which increases the energy consumed by the rod bodies when the composite material laminate layer 1 is damaged, thereby inhibiting the bidirectional imitation giant squid tentacle barb structure rod 2 from being pulled out, improving the ability to resist delamination, and thus inhibiting the generation or expansion of interlayer cracks. When the present invention is severely delaminated due to impact, the corresponding bidirectional imitation giant squid tentacle barb structure rod 2 is The structural rod 2 and each nanotube 202 are partially pulled out, and cracks appear in the resin 302 in the surrounding connecting structure 4. The corresponding nanotubes 202 in the inter-barb hook connection structure 3 of the bird wing feather and the corresponding fibers 301 in the connecting structure 4 span across the two surfaces of the interlaminar crack like a bridge, connecting the two surfaces of the interlaminar crack, playing the role of a crack bridging mechanism, and preventing the further opening and expansion of the interlaminar crack. At the same time, the corresponding nanotubes 202 and fibers 301 share part of the stress concentration acting on the tip of the interlaminar crack, bear part of the tensile and shear stress, and friction and debonding occur at the interface in contact with the resin 302, consuming the energy of the interlaminar crack expansion, so that the energy required for the expansion of the interlaminar crack increases, thereby increasing the resistance to the expansion of the interlaminar crack, inhibiting the further pulling out of the bidirectional giant squid tentacle hook structural rod 2, and inhibiting the further increase of the delamination damage.

Claims

1. A novel bionic anti-delamination composite laminate, comprising a composite laminate layer, characterized in that: It also includes a bidirectional imitation giant squid tentacle barb structure rod, a hook connection structure and a connection structure between the barbules of the wing feathers of birds; the composite material laminate layer is provided with a plurality of through holes arranged in an array, and each through hole is provided with a bidirectional imitation giant squid tentacle barb structure rod; the bidirectional imitation giant squid tentacle barb structure rod includes a main body, a barb structure and an interlocking structure; the main body is composed of a rod body 1 and a rod body 2 coaxially arranged with the corresponding through holes, and a plurality of barb structure groups uniformly distributed along the circumferential direction are fixed on the cylindrical surfaces of the rod body 1 and the rod body 2, and the barb structure group is composed of a barb structure arranged along the axial direction The barb structure is composed of a plurality of evenly distributed barb structures, the barb structure is composed of an integrally formed main barb and two auxiliary hooks, the two auxiliary hooks are located on both sides of the main barb and are perpendicular to the central axis of the main body; the main barbs on the rod body one and the main barbs on the rod body two are arranged opposite to each other along the axial direction of the main body; the interlocking structure includes a locking head and a locking chamber, the locking head is fixed to one end of the rod body one close to the rod body two, the end of the rod body two close to the rod body one is provided with a locking hole, and a locking chamber connected with the locking hole is provided, the locking head passes through the locking hole and is embedded in the locking chamber, and the two end faces of the rod body one and the rod body two are in contact with each other; The cylindrical surfaces of the rod body one and the rod body two are both provided with hook-connecting structures imitating the barbs in bird wing feathers, which are composed of multiple nanotubes arranged at intervals, and each nanotube is obliquely fixed on the cylindrical surface of the rod body one or the rod body two; each through hole is filled with a connecting structure between the main body and the wall of the through hole, and each main body is fixed in each through hole through the corresponding connecting structure; the connecting structure is formed by a mixture of resin and multiple fibers, and each fiber is wound around the corresponding main hooks, each auxiliary hook or each nanotube; the resin fills the gap between each main body and the corresponding through hole to fix the main body in the through hole.

2. The novel bionic anti-delamination composite laminate according to claim 1, characterized in that: The composite laminate layer is formed by stacking multiple layers of unidirectional carbon fiber resin composite materials at a spiral angle of 45 degrees.

3. The novel bionic anti-delamination composite laminate according to claim 1, characterized in that: The through holes are perpendicular to the composite laminate layers.

4. The novel bionic anti-delamination composite laminate according to claim 1, characterized in that: The thickness of the composite laminate layer is greater than 3mm, the diameter of the bidirectional imitation giant squid tentacle barb structure rod is 0.1mm-1mm, and the diameter of the through hole is 0.1mm larger than the diameter of the bidirectional imitation giant squid tentacle barb structure rod.

5. The novel bionic anti-delamination composite laminate according to claim 1, characterized in that: The volume of the bidirectional giant squid tentacle barb structural rod accounts for 2.0% of the volume of the composite material laminate layer.

6. The novel bionic anti-delamination composite laminate according to claim 1, characterized in that: The materials of the rod body 1 and the rod body 2 are both carbon fiber-bismaleimide composite materials, and the nanotubes are single-walled carbon fiber nanotubes.

7. The novel bionic anti-delamination composite laminate according to claim 1, characterized in that: The nanotube is adhered to the cylindrical surface of the first rod or the second rod through a mixed solution of an acetone solution and an epoxy resin without a curing agent.

8. The novel bionic anti-delamination composite laminate according to claim 1, characterized in that: The fiber is aramid pulp fiber, the resin is epoxy resin, and the concentration of the aramid pulp fiber in the connection structure is 2.0%.

9. The novel bionic anti-delamination composite laminate according to claim 1, characterized in that: When the composite laminate layer is opened with each through hole, it is in a prepreg state, and when the composite laminate layer is in the prepreg state, a connection structure is injected into the through hole in sequence, and a combined structure consisting of a bidirectional giant squid tentacle barb structure rod and a bird wing feather middle feather barb hook connection structure is placed.

10. The novel bionic anti-delamination composite laminate according to claim 9, characterized in that: The process of placing the combined structure into the corresponding through hole is as follows: inserting the rod body 1 and the rod body 2 from both ends of the corresponding through hole, allowing the lock head to pass through the lock hole and be embedded in the lock chamber, and allowing the rod body 1 and the rod body 2 to rotate relative to each other, so that the lock head and the lock chamber are interlocked.

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