阅读说明：本技术 飞机货舱底部结构 (Aircraft cargo bay bottom structure ) 是由 童健 袁庆铭 徐明先 崔伟 余青平 于 2020-12-28 设计创作，主要内容包括：本申请公开了一种飞机货舱底部结构。该飞机货舱底部结构包括机体、地板、隔热层及连接件,地板位于机体中并与机体连接,地板与机体围成第一舱室。隔热层位于第一舱室中通过连接件与地板连接,并与机体间隔设置,从而使隔热层不直接与机体贴合,可以避免隔热层吸收机体上的积水,从而可以减缓隔热层的老化,并且可以使机体上的积水能够正常蒸发及排除,避免机体经常处于潮湿状态,进而减少机体的腐蚀。(The application discloses aircraft cargo hold bottom structure. The bottom structure of the aircraft cargo compartment comprises a machine body, a floor, a heat insulation layer and a connecting piece, wherein the floor is positioned in the machine body and is connected with the machine body, and the floor and the machine body enclose a first compartment. The insulating layer is arranged in the first cabin and is connected with the floor through a connecting piece, and is arranged at an interval with the machine body, so that the insulating layer is not directly attached to the machine body, accumulated water on the machine body can be prevented from being absorbed by the insulating layer, aging of the insulating layer can be slowed down, the accumulated water on the machine body can be normally evaporated and removed, the machine body is prevented from being frequently in a wet state, and corrosion of the machine body is reduced.)

1. An aircraft cargo bay substructure, comprising: the machine body, the floor, the heat insulation layer and the connecting piece;

the floor is positioned in the machine body and connected with the machine body; the floor and the machine body enclose a first cabin;

the heat insulation layer is positioned in the first cabin, is connected with the floor through the connecting piece and is arranged at intervals with the machine body.

2. An aircraft cargo bay substructure according to claim 1, wherein said connection members comprise a fastener member connected to said floor, and a retainer member connected to said fastener member;

the insulating layer includes a first insulating member located between the securing member and the clamping member.

3. An aircraft cargo bay substructure according to claim 2, wherein said fasteners comprise a fastening plate attached to said floor and a fastening bar attached to said fastening plate;

the first heat insulation piece is sleeved on the fixing rod.

4. An aircraft cargo bay substructure as defined in claim 3, wherein said fixture further comprises a plurality of bosses provided on said beams; the plurality of protruding parts are arranged at intervals along the extending direction of the fixing rod;

the clamping piece is sleeved on the fixed rod and positioned between two adjacent protrusions to be clamped with the fixed rod.

5. An aircraft cargo bay substructure as claimed in claim 4, wherein said protrusion is a ring of protrusions provided on said fastening bars.

6. An aircraft cargo bay substructure according to claim 2, wherein said clamp comprises a clamping plate connected to said fixture and a gripping portion connected to said clamping plate, said gripping portion extending away from said floor.

7. An aircraft cargo compartment substructure according to any of claims 1 to 6, wherein said floor comprises a panel and at least one floor beam located in said first compartment and connected to said panel;

the connecting piece also comprises an elastic clamping piece corresponding to the floor beam;

the insulation layer further comprises a second insulation between the floor beam and the resilient clip.

8. An aircraft cargo bay substructure according to claim 7, wherein said floor beams comprise a first section connected to said panel, a second section connected vertically to said first section, and a third section connected horizontally to said second section.

9. An aircraft cargo bay substructure according to claim 7, further comprising fire-resistant bumpers between said panels and said floor beams.

10. An aircraft cargo bay substructure according to claim 9, wherein one side of said fire-resistant cushion is bonded to said airframe.

Technical Field

The invention relates to the technical field of aviation, in particular to a bottom structure of a cargo hold of an airplane.

Background

An aircraft cargo bay is an important part of an aircraft, primarily intended for carrying cargo, fuel and various equipment. However, the bottom structure of the cargo hold of the prior art aircraft is often in a wet state and is susceptible to corrosion.

Disclosure of Invention

The application provides an aircraft cargo hold substructure to solve the problem that prior art aircraft cargo hold substructure corrodes easily.

In one aspect, the present application provides an aircraft cargo bay bottom structure comprising: the machine body, the floor, the heat insulation layer and the connecting piece;

the floor is positioned in the machine body and connected with the machine body; the floor and the machine body enclose a first cabin;

the heat insulation layer is positioned in the first cabin, is connected with the floor through the connecting piece and is arranged at intervals with the machine body.

In some possible implementations, the connecting member includes a fixing member connected to the floor panel, and a clamping member connected to the fixing member;

the insulating layer includes a first insulating member located between the securing member and the clamping member.

In some possible implementations, the fixing member includes a fixing plate connected to the floor and a fixing rod connected to the fixing plate;

the first heat insulation piece is sleeved on the fixing rod.

In some possible implementations, the fixing further includes a plurality of protrusions provided on the fixing rod; the plurality of protruding parts are arranged at intervals along the extending direction of the fixing rod;

the clamping piece is sleeved on the fixed rod and positioned between two adjacent protrusions to be clamped with the fixed rod.

In some possible implementations, the protrusion is a ring of protrusions provided on the fixing lever.

In some possible implementations, the clamping member includes a clamping plate connected with the fixing member and a grip portion connected with the clamping plate, the grip portion extending away from the floor.

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;

the connecting piece also comprises an elastic clamping piece corresponding to the floor beam;

the insulation layer further comprises a second insulation between the floor beam and the resilient clip.

In some possible implementations, the floor beam includes a first portion connected to the panel, a second portion vertically connected to the first portion, and a third portion horizontally connected to the second portion.

In some possible implementations, the aircraft cargo compartment substructure further includes a fire damper located between the panel and the floor beam.

In some possible implementations, one side of the fireproof damping member is bonded to the body.

The bottom structure of the aircraft cargo hold comprises an aircraft body, a floor, a heat insulation layer and a connecting piece, wherein the floor is positioned in the aircraft body and is connected with the aircraft body; the floor and the machine body enclose a first cabin; the insulating layer is arranged in the first cabin and is connected with the floor through a connecting piece, and is arranged at an interval with the machine body, so that the insulating layer is not directly attached to the machine body, accumulated water on the machine body can be prevented from being absorbed by the insulating layer, aging of the insulating layer can be slowed down, the accumulated water on the machine body can be normally evaporated and removed, the machine body is prevented from being frequently in a wet state, and corrosion of the machine body is reduced.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a schematic perspective view of an aircraft cargo bay bottom structure provided in accordance with an embodiment of the present application;

FIG. 2 is a simplified schematic illustration of an aircraft cargo bay bottom structure provided in accordance with an embodiment of the present application;

FIG. 3 is a simplified schematic illustration of an aircraft cargo bay bottom structure provided in accordance with another embodiment of the present application;

FIG. 4 is a schematic illustration of a portion of an aircraft cargo bay bottom structure provided in accordance with an embodiment of the present application;

FIG. 5 is a cross-sectional view taken at A-A of FIG. 4;

FIG. 6 is an enlarged schematic view at B of FIG. 5;

FIG. 7 is a schematic view of a first insulation or a second insulation of an aircraft cargo bay bottom structure provided in accordance with an embodiment of the present application;

FIG. 8 is a schematic illustration of a fixture for a cargo bay bottom structure of an aircraft provided in accordance with an embodiment of the present application;

figure 9 is a schematic illustration of a retainer for an aircraft cargo bay substructure provided in accordance with an embodiment of the present application.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered as limiting the present invention. Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present application, "a plurality" means two or more unless specifically limited otherwise.

Referring to fig. 1 to 9, in an embodiment of the present application, there is provided an aircraft cargo compartment bottom structure including: the device comprises a machine body 1, a floor 2, a heat insulation layer 3 and a connecting piece 4;

the floor 2 is positioned in the machine body 1 and connected with the machine body 1; the floor 2 and the machine body 1 enclose a first cabin 5;

the heat insulation layer 3 is located in the first compartment 5 and connected with the floor 2 by a connecting piece 4 and is arranged at a distance from the machine body 1.

It should be noted that the bottom structure of the cargo compartment of the aircraft needs to be provided with an insulating layer 3 to reduce the dissipation of heat inside the aircraft during flight and also reduce the influence of external noise on the inside of the cargo compartment or the passenger cabin. The inventor of the present application finds that directly attaching the thermal insulation layer 3 to the airframe 1 may cause the bottom structure of the aircraft cargo compartment to be often in a wet state and corrode, specifically: because the condensate water that the steam that various equipment produced on the aircraft and aircraft flight produced gathers and forms ponding on organism 1, consequently, insulating layer 3 directly laminates can absorb ponding and be in the humid state on organism 1, leads to ponding difficult evaporation, also difficult discharge to insulating layer 3 absorbs the back and can be ageing with higher speed, produces ageing material and drops, thereby leads to organism 1 often to be in the humid state, and takes place to corrode.

The utility model provides an aircraft cargo hold substructure's floor 2 is arranged in organism 1 and is connected with organism 1, floor 2 encloses into first cabin 5 with organism 1, insulating layer 3 is arranged in first cabin 5 and is connected with floor 2 through connecting piece 4, and set up with 1 interval of organism, compare in the technical scheme with insulating layer 3 direct laminating on organism 1, this application is through raising the position of insulating layer 3, thereby make insulating layer 3 not direct laminate with organism 1, can avoid insulating layer 3 to absorb the ponding on the organism 1, thereby can slow down the ageing of insulating layer 3, and can make the ponding on the organism 1 normally evaporate and get rid of, avoid organism 1 often to be in humid state, and then reduce the corruption of organism 1.

In this embodiment, in order to be aerodynamic and reduce the flight resistance, the body 1 is generally cylindrical, and after the floor 2 and the body 1 enclose a compartment 5, the floor 2 and the body 1 also enclose a second compartment 6 on the side remote from the first compartment 5, i.e. the aircraft cargo compartment comprises a first compartment 5 and a second compartment 6, wherein some reinforcing structures can be placed in the first compartment 5, and the second compartment 6 is the main compartment of the cargo compartment for loading cargo, fuel and various equipment.

In addition, referring to fig. 2, the bottom structure of the cargo compartment of the aircraft according to the present application can be applied to a small aircraft, in which only one floor 2 is required, i.e., the cargo compartment floor and the cabin floor are shared, and the second compartment 6 can be a cargo compartment or a cabin, i.e., the cargo compartment and the cabin are shared. Referring to fig. 3, the bottom structure of the cargo compartment of the aircraft according to the present application may also be applied to a medium-large aircraft, where an upper floor and a lower floor 2 are required to be disposed in the medium-large aircraft, the upper floor is a cabin floor, the lower floor is a cargo compartment floor, the upper floor and the aircraft body 1 enclose a third cabin 7 serving as a cabin, and the lower floor, the upper floor and the aircraft body 1 enclose a first cabin 5 and a second cabin 6.

In some embodiments, referring to fig. 5 and 6, the connecting member 4 includes a fixing member 41 connected to the floor panel 2, and a clamping member 42 connected to the fixing member 41; insulating layer 3 is including being located first heat insulating part 31 between mounting 41 and chucking spare 42, and this chucking spare 42 is with first heat insulating part 31 chucking in floor 2, and this application can realize making insulating layer 3 not directly laminate with organism 1 through mounting 41 and chucking spare 42's cooperation, reduces the corruption of organism 1, and simple structure and with low costs.

In this embodiment, referring to fig. 7, the first heat insulating member 31 includes a heat insulating cotton core 311 and a wrapping layer 312 wrapping the heat insulating cotton core 311, the heat insulating cotton core 311 is mainly used to reduce heat dissipation inside the aircraft during flight, and at the same time, the influence of external noise on the interior of the cargo compartment or the passenger cabin can be reduced, and the wrapping layer 312 is used to protect the heat insulating cotton core 311 and prolong the service life of the heat insulating cotton core 311. The materials of the heat insulation cotton core 311 and the wrapping layer 312 are all materials meeting the aviation material specification. In addition, the wrapping layer 312 can be sealed by a hot-melt packaging process, so that the heat-insulating cotton core 311 is completely wrapped, and the protection effect is improved.

In this embodiment, the number of the fixing members 41 and the fastening members 42 may be plural, the number of the first heat insulating members 31 corresponds to the number of the fixing members 41, and may also be plural, and the positions of the plural fixing members 41 may be reasonably set according to the size of the first heat insulating members 31, so that the distance between two adjacent first heat insulating members 31 is close to 0, thereby avoiding excessively increasing the number of the first heat insulating members 31 and the weight of the bottom structure of the cargo compartment of the aircraft on the basis of ensuring the heat insulating effect.

Further, referring to fig. 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 insulating member 31 is sleeved on the fixing rod 412, for example, a hole may be formed in the first heat insulating member 31 and then sleeved on the fixing rod 412, or the fixing rod 412 may directly pass through the first heat insulating member 31, so as to prevent the first heat insulating member 31 and the fixing rod 412 from falling off, improve the connection stability of the first heat insulating member 31, prevent the first heat insulating member 31 from falling off the machine body 1, and further reduce corrosion of the machine body 1.

In this embodiment, the fixing bar 412 may be perpendicular to the fixing bar 411; the fixing plate 411 may be adhered to the floor 2 by epoxy glue, and the epoxy glue is made of a material meeting the specification of aviation materials.

Further, referring to fig. 8 and 9, the fixing member 41 further includes a plurality of protrusions 413 disposed on the fixing rod 412; the plurality of protrusions 413 are spaced along the extending direction of the fixing rod 412, and the clamping member 42 is sleeved on the fixing rod 412 and positioned between two adjacent protrusions 413 to be clamped with the fixing rod 412. That is, in the present application, by providing a plurality of protrusions 413 on the fixing rod 412, a groove is formed between two adjacent protrusions 413, the clamping member 42 can be located in the groove to realize clamping with the fixing rod 412, and the clamping member 42 can also be located in the groove at different positions to adapt to different sizes of the first thermal insulation members 31. Moreover, the plurality of protrusions 413 can also improve the stability of the first heat insulation member 31 sleeved on the fixing rod 412, and can further prevent the first heat insulation member 31 and the fixing rod 412 from falling off, further prevent the first heat insulation member 31 from falling onto the machine body 1, and further reduce the corrosion of the machine body 1.

In addition, a plurality of bosses 413 may be integrally formed with the fixing lever 412 to improve strength. The thickness of the protrusion 413 may be gradually increased toward the fixing plate 411, which not only facilitates the first heat insulation member 31 and the fastening member 42 to be sleeved on the fixing rod 412, but also further improves the stability of the first heat insulation member 31 and the fastening member 42 to be sleeved on the fixing rod 412. In addition, the plurality of protrusions 413 and the fixing rod 412 are made of non-metal materials, so that the overall weight of the connecting piece 4 can be reduced, and the non-metal materials also have certain plastic deformation, so that the clamping piece 42 can be conveniently clamped with the fixing rod 412, and the first heat insulation piece 31 can be conveniently sleeved with the fixing rod 412.

In this embodiment, the end of the fixing rod 412 away from the fixing plate 411, i.e., the end of the fixing rod 412 not connected to the fixing plate 411, is shaped like a truncated cone with a curved top surface, so that the first thermal insulating member 31 and the clamping member 42 are sleeved on the fixing rod 412.

In this embodiment, please refer to fig. 8, the protrusion 413 may be a circle of protrusion disposed on the fixing rod 412, and the protrusions 413 are a plurality of circles of protrusions disposed on the fixing rod 412, and the plurality of circles of protrusions are spaced apart from each other along the extending direction of the fixing rod 412, that is, the axial direction of the fixing rod 412, so that the groove between two adjacent circles of protrusions also surrounds a circle of surface of the fixing rod 412, thereby improving the clamping effect between the clamping member 42 and the fixing rod 412, and also improving the stability of the nesting between the first heat insulating member 31 and the fixing rod 412, further preventing the first heat insulating member 31 and the fixing rod 412 from falling off, further preventing the first heat insulating member 31 from falling onto the machine body 1, and further reducing the corrosion of the machine body 1.

In other embodiments, the protrusion 413 may not be a circle of protrusions, but may be at least one protrusion provided on the fixing rod 412, and a groove may be formed between two adjacent protrusions spaced apart along the extending direction of the fixing rod 412, so as to achieve the clamping of the fastening member with the fixing rod 412, and further reduce the cost.

Further, referring to fig. 6 and 9, the fastening member 42 includes a fastening plate 421 connected to the fixing member 41 and a holding portion 422 connected to the fastening plate 421, and the holding portion 422 extends away from the floor panel 2. The grip portion 422 can facilitate manual manipulation of the retainer 42, thereby improving the efficiency of installation and replacement of the first thermal insulating member 31.

In addition, the clamping plate 421 may be provided with a through hole 4211, a diameter of the through hole 4211 may be the same as or close to a diameter of the fixing rod 412, and is smaller than a sum of diameters of the fixing rod 412 and the protrusion 413, so that the clamping plate 421 may be sleeved on the fixing rod 412 through the through hole 4211 to be clamped with the fixing rod 412 to clamp the first heat insulation member 31, and a distance between the clamping plate 421 and the fixing plate 411 may be smaller than or equal to a thickness of the first heat insulation member 31, so that a clamping effect of the clamping plate 421 on the first heat insulation member 31 may be improved. The shape of the clamping plate 421 can match with the shape of the groove between two adjacent protrusions 413, so as to improve the clamping stability of the clamping plate 421 and the fixing rod 412.

In addition, the holding portion 422 may be at least two holding rods oppositely arranged, or may be a ring of holding plates connected with the clamping plate 421 to facilitate manual operation of the clamping member 42. The holding rod or the holding plate can be arc-shaped, so that the holding is further convenient.

In some embodiments, referring to fig. 5 and 6, the floor 2 includes a plate 21 and at least one floor beam 22 located in the first cabin 5 and connected to the plate 21, and the floor beam 22 is a weight bearing member capable of transmitting the gravity of the internal structures in the first cabin 5 and the second cabin 6 to the machine body 1 and improving the load capacity of the machine body 1.

The connecting member 4 further comprises a resilient clamping member 43 corresponding to the floor beam 22, and the insulation layer 3 further comprises a second insulation member 32 located between the floor beam 22 and the resilient clamping member 43. That is, in the present application, the second heat insulating member 32 is clamped on the floor beam 22 by the elastic clamping member 43, so that the heat insulating layer 3 is not directly attached to the machine body 1, the corrosion of the machine body 1 is reduced, and the structure is simple and the cost is low.

In this embodiment, the fixing member 41 is connected to the plate body 21, and the fastening member 42 fastens the first heat insulating member 31 to the plate body 21. The second thermal insulation member 32 may have the same structure as the first thermal insulation member 31, and also includes a thermal insulation cotton core 311 and a wrapping layer 312 wrapping the thermal insulation cotton core 311. The first and second heat insulators 31 and 32 are different in size so that the sizes of the panel body 21 and the floor beam 22 can be respectively adapted to improve the heat insulating effect of the first and second heat insulators 31 and 32.

Further, referring to fig. 6, the floor beam 22 includes a first portion 221 connected to the plate body 21, a second portion 222 vertically connected to the first portion 221, and a third portion 223 horizontally connected to the second portion 222. The first portion 221 to the third portion 223 are each a beam body of the floor beam 22. The elastic clamping member 43 may surround the second portion 222 and the third portion 223, clamp the second thermal insulation member 32 to the second portion 222 and the third portion 223 by elastic force, and the third portion 223 may bear the second thermal insulation member 32 and the elastic clamping member 43, thereby preventing the second thermal insulation member 32 and the elastic clamping member 43 from falling off the floor beam 22 and improving the connection stability of the second thermal insulation member 32.

In this embodiment, the shape of the resilient clip 43 matches the shape of the floor beam 22, for example, when the third portion 223 extends towards the second portion 222 away from the first portion 221, the floor beam 22 is shaped like a "Z", the resilient clip 43 can be shaped to match the shape of the "Z", for example, the shape like the Chinese character 'ji', which can increase the contact area between the elastic clamp 43 and the second heat insulator 32, increase the clamping effect, prevent the second heat insulator 32 from falling off the fixing rod 412, when the third portion 223 extends toward the second portion 222 in the direction of approaching the first portion 221, the floor beam 22 is shaped like a C, and the elastic clamping member 43 can be matched with the C, so that the contact area between the elastic clamping member 43 and the second heat insulating member 32 can be increased, the clamping effect can be improved, and the second heat insulating member 32 and the fixing rod 412 can be prevented from falling off. The first portion 221 and the plate 21 may be connected by screws, but may also be connected by other connection methods, such as riveting, and the application is not limited herein. The elastic clamping member 43 may be a spring clip, but may also be of other structures, and the application is not limited herein.

In this embodiment, the floor beam 22 is long, and it is necessary that the plurality of elastic clamping members 43 and the plurality of second heat insulating members 32 correspond to one floor beam 22, so that the positions of the plurality of elastic clamping members 43 can be reasonably set according to the size of the second heat insulating members 32, and the distance between two adjacent second heat insulating members 32 on one floor beam 22 is close to 0, thereby avoiding excessively increasing the number of the second heat insulating members 32 and the weight of the bottom structure of the cargo compartment of the aircraft on the basis of ensuring the heat insulating effect.

Further, referring to fig. 6, the bottom structure of the cargo compartment of the aircraft further includes a fireproof vibration-damping member 8 between the panel body 21 and the floor beam 22 to increase the fireproof and vibration-damping functions of the floor 2, and also fills the gap between the panel body 21 and the floor beam 22 to increase the sealability of the floor 2.

In this embodiment, the fireproof damping member 8 may be fireproof damping rubber, and the fireproof damping rubber is made of a material that meets the specification of aviation materials.

Further, one side of the fireproof vibration absorbing member 8 is bonded to the body 1 to increase the coupling stability of the fireproof vibration absorbing member 8. And only one side that fire prevention damping piece 8 contacted with organism 1 has viscidity, does not have viscidity with one side that floor beam 22 contacted to can prevent that fire prevention damping piece 8 from bonding with second heat insulating part 32, be favorable to changing second heat insulating part 32, avoid the second heat insulating part 32 after ageing to remain on floor beam 22.

In some embodiments, referring to fig. 4, the body 1 includes a frame 11 and a skin 12 covering the frame 11, and the floor 2 is located in the frame 11 and connected to the frame 11. The frame 11 includes a plurality of stringers 111 disposed in a longitudinal direction and a plurality of formers 112 disposed in a transverse direction. The overall shape of the frame 11 and the shape of the skin 12 are both cylindrical, and the panel body 21 and the floor beam 22 are both connected to the frame 11.

In some embodiments, the connecting member 4 may not include the fixing plate 411, the fixing rod 412, the clamping member 42 and the elastic clamping member 43, but other connecting members 4 and connecting methods may be used to fix the first and second heat insulating members 31 and 32, which is not limited herein.

For example, the first thermal insulation element 31 and the second thermal insulation element 32 may be fixed by a snap-fit manner, and then the connection element 4 may be a snap and a snap fixing seat that can be correspondingly snapped with the snap, and by providing a plurality of snaps on the first thermal insulation element 31 and the second thermal insulation element 32, and by providing a plurality of snap fixing seats that respectively correspond to the plurality of snaps on the plate body 21 and the floor beam 22, the first thermal insulation element 31 and the second thermal insulation element 32 can be fixed only by respectively snapping the plurality of snaps with the plurality of snap fixing seats.

For another example, the first heat insulating member 31 and the second heat insulating member 32 may be fixed by adhesion, and the connecting member 4 may be a double-sided tape, and the first heat insulating member 31 and the second heat insulating member 32 are directly adhered to the plate body 21 and the floor beam 22 by the double-sided tape. And for the convenience of change and dismantle first heat insulating part 31 and second heat insulating part 32, connecting piece 4 still can be for having the first magic subsides of matte and having the second magic subsides of colluding the face, through set up a plurality of first magic subsides on first heat insulating part 31 and second heat insulating part 32, set up a plurality of second magic subsides that correspond respectively with a plurality of first magic subsides on plate body 21 and floor beam 22, only need paste a plurality of first magic subsides and a plurality of second magic subsides, can realize the fixed of first heat insulating part 31 and second heat insulating part 32.

For another example, the first heat insulating member 31 and the second heat insulating member 32 may be fixed by a magnetic attraction manner, and the connecting member 4 may be a first magnet and a second magnet or a metal member that can be attracted to and attracted to the first magnet, and the first heat insulating member 31 and the second heat insulating member 32 may be fixed by providing a plurality of first magnets on the first heat insulating member 31 and the second heat insulating member 32, and providing a plurality of second magnets or metal members that respectively correspond to the plurality of first magnets on the plate body 21 and the floor beam 22, and only by attracting the plurality of first magnets to the plurality of second magnets or metal members, respectively.

For another example, the first heat insulating element 31 and the second heat insulating element 32 may be fixed by using a hook connection manner, and then the connecting member 4 may be a first hook and a second hook or a hole correspondingly connected to the first hook, and the first heat insulating element 31 and the second heat insulating element 32 are provided with a plurality of first hooks, and the plate body 21 and the floor beam 22 are provided with a plurality of second hooks or holes respectively corresponding to the plurality of first hooks, so that the first heat insulating element 31 and the second heat insulating element 32 can be fixed only by connecting the plurality of first hooks with the plurality of second hooks or holes respectively.

In the above embodiments, the descriptions of the respective embodiments have respective emphasis, and parts that are not described in detail in a certain embodiment may refer to the above detailed descriptions of other embodiments, and are not described herein again.

In a specific implementation, each component or structure may be implemented as an independent entity, or may be combined arbitrarily and implemented as one or several entities, and the specific implementation of each component or structure may refer to the foregoing embodiments, which are not described herein again.

The present invention provides an aircraft cargo compartment bottom structure, which is described in detail above, and the principle and the implementation of the present invention are explained herein by using specific examples, and the above description of the embodiments is only used to help understanding the method and the core idea of the present invention; meanwhile, for those skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.