Airplane cargo hold floor structure

Abstract

The application discloses an aircraft cargo hold bottom structure. The aircraft cargo hold bottom structure comprises a machine body, a floor, a heat insulation layer and a connecting piece. The floor is located in the machine body and connected with the machine body, and the floor and the machine body enclose a first cabin. The heat insulation layer is located in the first cabin and connected with the floor through the connecting piece and is spaced apart from the machine body, so that the heat insulation layer is not directly attached to the machine body, the heat insulation layer can avoid absorbing water on the machine body, thereby slowing down aging of the heat insulation layer, and water on the machine body can be normally evaporated and removed, the machine body can be prevented from being in a humid state frequently, and thus corrosion of the machine body is reduced.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, and more specifically to a bottom structure of an aircraft cargo hold. Background Technology

[0002] The aircraft cargo hold is a crucial component, primarily used for loading cargo, fuel, and various equipment. However, the bottom structure of current aircraft cargo holds is frequently exposed to moisture, making it susceptible to corrosion. Summary of the Invention

[0003] This application provides an aircraft cargo hold bottom structure to solve the problem of corrosion that easily occurs in existing aircraft cargo hold bottom structures.

[0004] On the one hand, this application provides a bottom structure for an aircraft cargo hold, including: a fuselage, a floor, a heat insulation layer, and connecting parts;

[0005] The floor is located within and connected to the fuselage; the floor and the fuselage together form a first compartment;

[0006] The heat insulation layer is located in the first compartment and is connected to the floor via the connector, and is spaced apart from the body.

[0007] In some possible implementations, the connector includes a fastener connected to the floor and a clamping member connected to the fastener;

[0008] The heat insulation layer includes a first heat insulation element located between the fastener and the clamping element.

[0009] In some possible implementations, the fastener includes a fixing plate connected to the floor and a fixing rod connected to the fixing plate;

[0010] The first heat insulation component is fitted onto the fixing rod.

[0011] In some possible implementations, the fastener further includes a plurality of protrusions provided on the fixing rod; the plurality of protrusions are spaced apart along the extending direction of the fixing rod;

[0012] The clamping element is fitted onto the fixing rod and located between two adjacent protrusions, engaging with the fixing rod.

[0013] In some possible implementations, the protrusion is a ring of protrusions on the fixing rod.

[0014] In some possible implementations, the clamping member includes a clamping plate connected to the fixing member and a gripping portion connected to the clamping plate, the gripping portion extending in a direction away from the floor.

[0015] In some possible implementations, the floor includes a panel and at least one floor beam located in the first compartment and connected to the panel;

[0016] The connector also includes an elastic clamping member corresponding to the floor beam;

[0017] The insulation layer also includes a second insulation element located between the floor beam and the elastic clamping member.

[0018] In some possible implementations, the floor beam includes a first part connected to the slab, a second part connected vertically to the first part, and a third part connected horizontally to the second part.

[0019] In some possible implementations, the aircraft cargo hold bottom structure also includes fireproof and shock-absorbing components located between the plate and the floor beam.

[0020] In some possible implementations, one side of the fireproof shock absorber is bonded to the body.

[0021] The aircraft cargo hold bottom structure provided in this application includes a fuselage, a floor, a heat insulation layer, and connectors. The floor is located in the fuselage and connected to it. The floor and the fuselage enclose a first compartment. The heat insulation layer is located in the first compartment and connected to the floor via connectors, and is spaced apart from the fuselage. This prevents the heat insulation layer from directly adhering to the fuselage, thus avoiding the heat insulation layer from absorbing water accumulated on the fuselage. This slows down the aging of the heat insulation layer and allows water accumulated on the fuselage to evaporate and drain normally, preventing the fuselage from being in a damp state and reducing corrosion of the fuselage. Attached Figure Description

[0022] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a perspective view of the bottom structure of an aircraft cargo hold provided in one embodiment of this application;

[0024] Figure 2 This is a simplified schematic diagram of the bottom structure of an aircraft cargo hold provided in one embodiment of this application;

[0025] Figure 3 This is a simplified schematic diagram of the bottom structure of an aircraft cargo hold provided in another embodiment of this application;

[0026] Figure 4 This is a partial schematic diagram of the bottom structure of an aircraft cargo hold provided in one embodiment of this application;

[0027] Figure 5 yes Figure 4 Cross-sectional view at point AA;

[0028] Figure 6 yes Figure 5 An enlarged view of point B;

[0029] Figure 7 This is a schematic diagram of the first or second heat insulation component of the bottom structure of an aircraft cargo hold provided in an embodiment of this application;

[0030] Figure 8 This is a schematic diagram of a fastener for the bottom structure of an aircraft cargo hold provided in an embodiment of this application;

[0031] Figure 9 This is a schematic diagram of a clamping component for the bottom structure of an aircraft cargo hold, provided in one embodiment of this application. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "a plurality of" means two or more, unless otherwise explicitly specified.

[0034] Please see Figures 1 to 9 This application provides an aircraft cargo hold bottom structure, including: fuselage 1, floor 2, heat insulation layer 3 and connector 4;

[0035] Floor 2 is located inside and connected to fuselage 1; floor 2 and fuselage 1 form the first compartment 5.

[0036] The heat insulation layer 3 is located in the first compartment 5 and is connected to the floor 2 via connector 4, and is spaced apart from the body 1.

[0037] It should be noted that a heat insulation layer 3 needs to be installed on the bottom structure of the aircraft cargo hold to reduce heat loss from the aircraft during flight and to reduce the impact of external noise on the cargo hold or passenger cabin. The inventors of this application have discovered that directly attaching the heat insulation layer 3 to the fuselage 1 causes the bottom structure of the aircraft cargo hold to be constantly damp, leading to corrosion. Specifically, water vapor generated by various equipment on the aircraft and condensation generated during flight accumulate on the fuselage 1, forming water deposits. Therefore, the heat insulation layer 3, directly attached to the fuselage 1, absorbs this water, remaining damp. This makes it difficult for the water to evaporate or drain, and the heat insulation layer 3 ages faster after absorbing water, causing the aged material to detach, thus resulting in the fuselage 1 being constantly damp and corroded.

[0038] In this application, the floor 2 of the aircraft cargo hold bottom structure is located in and connected to the fuselage 1. The floor 2 and the fuselage 1 form a first compartment 5. The heat insulation layer 3 is located in the first compartment 5 and connected to the floor 2 through a connector 4, and is spaced apart from the fuselage 1. Compared with the technical solution of directly attaching the heat insulation layer 3 to the fuselage 1, this application raises the position of the heat insulation layer 3, so that the heat insulation layer 3 is not directly attached to the fuselage 1. This can prevent the heat insulation layer 3 from absorbing water accumulated on the fuselage 1, thereby slowing down the aging of the heat insulation layer 3. It can also allow the water accumulated on the fuselage 1 to evaporate and be discharged normally, preventing the fuselage 1 from being in a humid state, thereby reducing the corrosion of the fuselage 1.

[0039] In this embodiment, in order to conform to aerodynamics and reduce flight drag, the fuselage 1 is usually cylindrical. After the floor 2 and the fuselage 1 form a compartment 5, the floor 2 and the fuselage 1 will also form a second compartment 6 on the side away from the first compartment 5. That is, the aircraft cargo hold includes the first compartment 5 and the second compartment 6. Some reinforcing structures can be placed in the first compartment 5, while the second compartment 6 is the main compartment of the cargo hold, used to load cargo, fuel and various equipment.

[0040] In addition, please see Figure 2 The aircraft cargo hold bottom structure of this application can be applied to small aircraft. Small aircraft only need one floor 2, meaning the cargo hold floor and passenger cabin floor are shared. Therefore, the second compartment 6 can be either a cargo hold or a passenger cabin, meaning it can be shared by both. Please refer to... Figure 3 The aircraft cargo hold bottom structure of this application can also be applied to medium and large aircraft. Medium and large aircraft need to be equipped with two floors 2, the upper floor is the passenger cabin floor, the lower floor is the cargo hold floor, the upper floor and the fuselage 1 form a third cabin 7 as the passenger cabin, and the lower floor, the upper floor and the fuselage 1 form a first cabin 5 and a second cabin 6.

[0041] In some embodiments, please refer to Figure 5 and Figure 6 The connector 4 includes a fixing member 41 connected to the floor 2 and a clamping member 42 connected to the fixing member 41; the heat insulation layer 3 includes a first heat insulation member 31 located between the fixing member 41 and the clamping member 42. The clamping member 42 clamps the first heat insulation member 31 to the floor 2. This application can achieve the goal of preventing the heat insulation layer 3 from being directly attached to the body 1 by the cooperation of the fixing member 41 and the clamping member 42, thereby reducing the corrosion of the body 1. The structure is simple and the cost is low.

[0042] In this embodiment, please refer to Figure 7 The first thermal insulation component 31 includes a thermal insulation core 311 and a wrapping layer 312 that surrounds the thermal insulation core 311. The thermal insulation core 311 is mainly used to reduce heat loss from the aircraft interior during flight, and also to reduce the impact of external noise on the cargo hold or passenger cabin. The wrapping layer 312 is used to protect the thermal insulation core 311 and extend its service life. Both the thermal insulation core 311 and the wrapping layer 312 are made of materials that meet aerospace material specifications. In addition, the wrapping layer 312 can be sealed using a heat-sealing process to ensure that the thermal insulation core 311 is completely wrapped, thereby improving the protective effect.

[0043] In this embodiment, there can be multiple fasteners 41 and clamping members 42. The number of first heat insulation members 31 corresponds to the number of fasteners 41, and there can also be multiple fasteners 41. The positions of multiple fasteners 41 can be reasonably set according to the size of the first heat insulation members 31, so that the distance between two adjacent first heat insulation members 31 is close to 0. This ensures the heat insulation effect while avoiding excessive increase in the number of first heat insulation members 31 and the weight of the bottom structure of the aircraft cargo hold.

[0044] Further, please refer to Figure 6 The fixing member 41 includes a fixing plate 411 connected to the floor 2 and a fixing rod 412 connected to the fixing plate 411. The first heat insulation member 31 is fitted onto the fixing rod 412. For example, a hole can be made in the first heat insulation member 31 and then fitted onto the fixing rod 412, or the fixing rod 412 can be directly passed through the first heat insulation member 31. This can prevent the first heat insulation member 31 from falling off the fixing rod 412, improve the connection stability of the first heat insulation member 31, prevent the first heat insulation member 31 from falling onto the machine body 1, and thus reduce the corrosion of the machine body 1.

[0045] In this embodiment, the fixing rod 412 can be perpendicular to the fixing plate 411; the fixing plate 411 can be bonded to the floor 2 with epoxy resin adhesive, the epoxy resin adhesive being made of a material that meets aerospace material specifications.

[0046] Further, please refer to Figure 8 and Figure 9 The fixing member 41 also includes a plurality of protrusions 413 provided on the fixing rod 412; the plurality of protrusions 413 are spaced apart along the extending direction of the fixing rod 412, and the clamping member 42 is sleeved on the fixing rod 412 and located between two adjacent protrusions 413 to engage with the fixing rod 412. That is, by providing a plurality of protrusions 413 on the fixing rod 412, a groove is formed between two adjacent protrusions 413, and the clamping member 42 can be located in the groove to engage with the fixing rod 412. Moreover, the clamping member 42 can also be located in grooves at different positions to accommodate first heat insulation members 31 of different sizes. Furthermore, the plurality of protrusions 413 can also improve the stability of the first heat insulation member 31 sleeved on the fixing rod 412, further preventing the first heat insulation member 31 from falling off the fixing rod 412, further preventing the first heat insulation member 31 from falling onto the body 1, thereby reducing corrosion of the body 1.

[0047] Furthermore, multiple protrusions 413 can be integrally formed with the fixing rod 412 to improve strength. The thickness of the protrusions 413 can gradually increase towards the fixing plate 411, which not only facilitates the fitting of the first heat insulation member 31 and the clamping member 42 onto the fixing rod 412, but also further improves the stability of the first heat insulation member 31 and the clamping member 42 fitting onto the fixing rod 412. In addition, the multiple protrusions 413 and the fixing rod 412 are made of non-metallic materials, which can reduce the overall weight of the connector 4, and the non-metallic material also has a certain degree of plastic deformation, which facilitates the clamping member 42 to engage with the fixing rod 412 and the first heat insulation member 31 to fit onto the fixing rod 412.

[0048] In this embodiment, the end of the fixing rod 412 away from the fixing plate 411, that is, the end of the fixing rod 412 that is not connected to the fixing plate 411, is shaped like a frustum with a curved top surface, so that the first heat insulation member 31 and the clamping member 42 can be fitted onto the fixing rod 412.

[0049] In this embodiment, please refer to Figure 8 The protrusion 413 can be a ring of protrusions on the fixing rod 412. Multiple protrusions 413 can be multiple rings of protrusions on the fixing rod 412, and the multiple rings of protrusions are spaced apart along the extension direction of the fixing rod 412, that is, the axial direction of the fixing rod 412. The groove between two adjacent rings of protrusions is also a ring of surface around the fixing rod 412, which can improve the snapping effect between the clamping member 42 and the fixing rod 412, and also improve the stability of the engagement between the first heat insulation member 31 and the fixing rod 412. This can further prevent the first heat insulation member 31 from falling off the fixing rod 412, further prevent the first heat insulation member 31 from falling onto the machine body 1, and thus reduce the corrosion of the machine body 1.

[0050] In other embodiments, the protrusion 413 may not be a ring of protrusions, but may be at least one protrusion provided on the fixing rod 412. In this case, a groove may also be formed between two adjacent protrusions spaced apart along the extension direction of the fixing rod 412, thereby realizing the snap-fit ​​between the fastener and the fixing rod 412, and also reducing costs.

[0051] Further, please refer to Figure 6 and Figure 9 The clamping member 42 includes a clamping plate 421 connected to the fixing member 41 and a gripping part 422 connected to the clamping plate 421. The gripping part 422 extends away from the floor 2. The gripping part 422 facilitates manual operation of the clamping member 42, thereby improving the efficiency of installation and replacement of the first heat insulation member 31.

[0052] Furthermore, the clamping plate 421 may be provided with a through hole 4211. The diameter of the through hole 4211 may be the same as or close to the diameter of the fixing rod 412, and smaller than the sum of the diameters of the fixing rod 412 and the protrusion 413. This allows the clamping plate 421 to be fitted onto the fixing rod 412 and engaged with it, thereby securing the first heat insulation member 31. The distance between the clamping plate 421 and the fixing plate 411 may be less than or equal to the thickness of the first heat insulation member 31, thus improving the clamping effect of the clamping plate 421 on the first heat insulation member 31. The shape of the clamping plate 421 may match the shape of the groove between two adjacent protrusions 413, thereby improving the engagement stability between the clamping plate 421 and the fixing rod 412.

[0053] Alternatively, the gripping part 422 can be at least two gripping rods arranged opposite each other, or it can be a ring of gripping plates connected to the locking plate 421 to facilitate manual operation of the locking member 42. The gripping rods or gripping plates can be arc-shaped to further facilitate gripping.

[0054] In some embodiments, please refer to Figure 5 and Figure 6 The floor 2 includes a plate 21 and at least one floor beam 22 located in the first compartment 5 and connected to the plate 21. The floor beam 22 is a load-bearing component that can not only transfer the gravity of the internal structure in the first compartment 5 and the second compartment 6 to the body 1, but also improve the load capacity of the body 1.

[0055] The connector 4 also includes an elastic clamping member 43 corresponding to the floor beam 22, and the heat insulation layer 3 also includes a second heat insulation member 32 located between the floor beam 22 and the elastic clamping member 43. That is, by using the elastic clamping member 43 to clamp the second heat insulation member 32 onto the floor beam 22, this application can achieve the goal of preventing the heat insulation layer 3 from directly adhering to the body 1, reducing the corrosion of the body 1, and achieving a simple structure and low cost.

[0056] In this embodiment, the fixing member 41 is connected to the plate body 21, and the clamping member 42 clamps the first heat insulation member 31 onto the plate body 21. The second heat insulation member 32 may have the same structure as the first heat insulation member 31, and also includes a heat insulation cotton core 311 and a wrapping layer 312 that wraps the heat insulation cotton core 311. The difference between the first heat insulation member 31 and the second heat insulation member 32 lies in their different sizes, so that they can respectively adapt to the sizes of the plate body 21 and the floor beam 22, thereby improving the heat insulation effect of the first heat insulation member 31 and the second heat insulation member 32.

[0057] Further, please refer to Figure 6 , the floor beam 22 includes a first part 221 connected to the plate body 21, a second part 222 vertically connected to the first part 221, and a third part 223 horizontally connected to the second part 222. The first part 221 to the third part 223 are all beam bodies of the floor beam 22. The elastic clamping member 43 can surround the second part 222 and the third part 223, and clamp the second heat insulation member 32 onto the second part 222 and the third part 223 through elastic force. Moreover, the third part 223 can bear the second heat insulation member 32 and the elastic clamping member 43, preventing the second heat insulation member 32 and the elastic clamping member 43 from detaching from the floor beam 22, and improving the connection stability of the second heat insulation member 32.

[0058] In this embodiment, the shape of the elastic clamping member 43 matches the shape of the floor beam 22. For example, when the third part 223 extends in the direction away from the first part 221 towards the second part 222, the shape of the floor beam 22 is similar to a "Z" shape, and the shape of the elastic clamping member 43 can match the shape of the "Z" shape, such as a shape similar to a "Ji" shape, which can increase the contact area between the elastic clamping member 43 and the second heat insulation member 32, improve the clamping effect, and prevent the second heat insulation member 32 from detaching from the fixing rod 412. When the third part 223 extends in the direction towards the first part 221 towards the second part 222, the shape of the floor beam 22 is similar to a "C" shape, and the shape of the elastic clamping member 43 can match the shape of the "C" shape, which can increase the contact area between the elastic clamping member 43 and the second heat insulation member 32, improve the clamping effect, and prevent the second heat insulation member 32 from detaching from the fixing rod 412. The first part 221 and the plate body 21 can be connected by screws, and of course, other connection methods can also be used, such as riveting, and this application does not limit this here. The elastic clamping member 43 can be a spring clip, and of course, it can also be of other structures, and this application does not limit this here.

[0059] In this embodiment, the floor beam 22 is relatively long, requiring multiple elastic clamping members 43 and multiple second heat insulation members 32 to correspond to one floor beam 22. Therefore, the positions of the multiple elastic clamping members 43 can be reasonably set according to the size of the second heat insulation member 32, so that the distance between two adjacent second heat insulation members 32 on a floor beam 22 is close to 0, thereby ensuring the heat insulation effect while avoiding excessive increase in the number of second heat insulation members 32 and the weight of the bottom structure of the aircraft cargo hold.

[0060] Further, please refer to Figure 6 The aircraft cargo hold bottom structure also includes a fireproof and shock-absorbing component 8 located between the plate 21 and the floor beam 22 to increase the fireproof and shock-absorbing functions of the floor 2, and can also fill the gap between the plate 21 and the floor beam 22 to increase the sealing of the floor 2.

[0061] In this embodiment, the fireproof and shock-absorbing component 8 can be a fireproof and shock-absorbing adhesive, and the material of the fireproof and shock-absorbing adhesive is a material that meets the specifications of aerospace materials.

[0062] Furthermore, one side of the fireproof shock absorber 8 is bonded to the body 1 to increase the connection stability of the fireproof shock absorber 8. Also, the fireproof shock absorber 8 is only adhesive on the side in contact with the body 1, and not on the side in contact with the floor beam 22. This prevents the fireproof shock absorber 8 from bonding with the second heat insulation component 32, facilitating the replacement of the second heat insulation component 32 and preventing the aged second heat insulation component 32 from remaining on the floor beam 22.

[0063] In some embodiments, please refer to Figure 4 The body 1 includes a frame 11 and a skin 12 covering the frame 11. The floor 2 is located in the frame 11 and connected to the frame 11. The frame 11 includes a plurality of longitudinally arranged stringers 111 and a plurality of transversely arranged partitions 112. The overall shape of the frame 11 and the shape of the skin 12 are both cylindrical. The plate 21 and the floor beam 22 are both connected to the frame 11.

[0064] In some embodiments, the connector 4 may not include the fixing plate 411, fixing rod 412, clamping member 42 and elastic clamping member 43, but may use other connectors 4 and connection methods to fix the first heat insulation member 31 and the second heat insulation member 32. This application does not impose any restrictions on this.

[0065] For example, the first heat insulation component 31 and the second heat insulation component 32 can be fixed by snap-fitting. Then the connector 4 can be a snap-fit ​​and a snap-fit ​​fixing seat that can be snapped into the snap-fit. By setting multiple snap-fits on the first heat insulation component 31 and the second heat insulation component 32, and setting multiple snap-fit ​​fixing seats on the plate 21 and the floor beam 22 that correspond to the multiple snap-fits respectively, the first heat insulation component 31 and the second heat insulation component 32 can be fixed by simply snapping the multiple snap-fits into the multiple snap-fit ​​fixing seats respectively.

[0066] For example, the first heat insulation component 31 and the second heat insulation component 32 can be fixed by adhesive. In this case, the connector 4 can be double-sided adhesive, which can be used to directly bond the first heat insulation component 31 and the second heat insulation component 32 to the plate 21 and the floor beam 22, respectively. In order to facilitate the replacement and disassembly of the first heat insulation component 31 and the second heat insulation component 32, the connector 4 can also be a first hook and loop fastener with a rough surface and a second hook and loop fastener with a hook surface. By setting multiple first hook and loop fasteners on the first heat insulation component 31 and the second heat insulation component 32, and setting multiple second hook and loop fasteners on the plate 21 and the floor beam 22, the first heat insulation component 31 and the second heat insulation component 32 can be fixed simply by sticking the multiple first hook and loop fasteners and the multiple second hook and loop fasteners.

[0067] For example, the first heat insulation component 31 and the second heat insulation component 32 can be fixed by magnetic attraction. In this case, the connector 4 can be a first magnet and a second magnet or metal part that can be attracted to the first magnet. By setting multiple first magnets on the first heat insulation component 31 and the second heat insulation component 32, and setting multiple second magnets or metal parts corresponding to the multiple first magnets on the plate 21 and the floor beam 22, the first heat insulation component 31 and the second heat insulation component 32 can be fixed by simply attracting the multiple first magnets to the multiple second magnets or metal parts respectively.

[0068] For example, the first heat insulation component 31 and the second heat insulation component 32 can be fixed by using a snap hook connection. In this case, the connector 4 can be a first snap hook and a second snap hook or snap hole that can be connected to the first snap hook. By setting multiple first snap hooks on the first heat insulation component 31 and the second heat insulation component 32, and setting multiple second snap hooks or snap holes on the plate 21 and the floor beam 22 that correspond to the multiple first snap hooks respectively, the first heat insulation component 31 and the second heat insulation component 32 can be fixed by simply connecting the multiple first snap hooks to the multiple second snap hooks or snap holes respectively.

[0069] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the detailed descriptions of other embodiments above, which will not be repeated here.

[0070] In practice, each of the above components or structures can be implemented as an independent entity or can be arbitrarily combined to be implemented as the same or several entities. For specific implementation of each of the above components or structures, please refer to the previous embodiments, which will not be repeated here.

[0071] The above provides a detailed description of an aircraft cargo hold bottom structure provided by the embodiments of the present invention. Specific examples have been used to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is only for the purpose of helping to understand the method and core ideas of the present invention. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. A bottom structure for an aircraft cargo hold, characterized in that, include: Body, floor, insulation layer and connectors; The floor is located within and connected to the fuselage; the floor and the fuselage together form a first compartment; The heat insulation layer is located in the first compartment and is connected to the floor via the connector, and is spaced apart from the body; The connector includes a fixing member connected to the floor and a clamping member connected to the fixing member; The heat insulation layer includes a first heat insulation component located between the fixing component and the clamping component, the first heat insulation component including a heat insulation cotton core and a wrapping layer that wraps the heat insulation cotton core; The fastener includes a fixing plate connected to the floor and a fixing rod connected to the fixing plate; The first heat insulation component is fitted onto the fixing rod; The floor includes a panel and at least one floor beam located in the first compartment and connected to the panel; The connector also includes an elastic clamping member corresponding to the floor beam; The insulation layer also includes a second insulation component located between the floor beam and the elastic clamping member. The second insulation component has the same structure as the first insulation component, but different dimensions.

2. The aircraft cargo hold bottom structure as described in claim 1, characterized in that, The fastener also includes a plurality of protrusions provided on the fixing rod; the plurality of protrusions are spaced apart along the extension direction of the fixing rod; The clamping element is fitted onto the fixing rod and located between two adjacent protrusions, engaging with the fixing rod.

3. The aircraft cargo hold bottom structure as described in claim 2, characterized in that, The protrusion is a ring of protrusions on the fixing rod.

4. The aircraft cargo hold bottom structure as described in claim 3, characterized in that, The clamping member includes a clamping plate connected to the fixing member and a gripping part connected to the clamping plate, the gripping part extending away from the floor.

5. The aircraft cargo hold bottom structure as described in claim 1, characterized in that, The floor beam includes a first part connected to the slab, a second part perpendicularly connected to the first part, and a third part horizontally connected to the second part.

6. The aircraft cargo hold bottom structure as described in claim 1, characterized in that, It also includes fireproof and shock-absorbing components located between the plate and the floor beam.

7. The aircraft cargo hold bottom structure as described in claim 6, characterized in that, One side of the fireproof and shock-absorbing component is bonded to the machine body.

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