A storage and transportation box for aircraft

Abstract

The present application relates to a storage and transportation box for aircraft, which includes: a box body and a radiation-proof heat-insulating coating, wherein the box body has a storage room, and a plurality of heat-insulating cavities are arranged in the top plate of the box body; the radiation-proof heat-insulating coating is coated on the surface of the box body. By arranging a plurality of the heat-insulating cavities in the top plate of the box body, solar heat radiation is blocked, and by coating the radiation-proof heat-insulating coating on the surface of the box body, solar heat radiation is reflected and not easy to accumulate heat on the surface of the box body, so that the temperature rise in the box body is controlled within the storage temperature range of the aircraft under solar heat radiation, solving the technical problem in the related art that the heat dissipation of steel storage and transportation boxes is poor, and the temperature rise in the box body is likely to be serious under direct sunlight, and the temperature in the box body may exceed the specified aircraft storage temperature.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft, and in particular to a storage and transportation box for aircraft. Background Art

[0002] At present, the guidance device of the aircraft is modularized into a multifunctional box, which can be temporarily stacked and stored in the field, and can also be stacked and stored for a long time in the warehouse. The box can adapt to the transportation of trucks, trains or ships. The box can also be connected to the aircraft body to launch the aircraft. The modular storage and transportation box solves various needs in storage, transportation and launching, and can realize the universality of aircraft platforms.

[0003] In the related technology, the storage and transportation boxes of active aircraft are generally made of aluminum alloy boxes. Since aluminum is expensive, the cost of storage and transportation boxes is often high. The storage and transportation boxes of active aircraft are also made of fiberglass boxes. The molding of fiberglass requires a large number of molding molds, and the mold preparation cycle is long. Due to the different structures of aircraft, storage and transportation boxes cannot use a universal mold. The production cycle of mold replacement is long and the production cost is high. At the same time, the adhesives used in fiberglass molding contain toxic and harmful materials, which pollute the environment and affect the health of the production personnel. The storage and transportation boxes of active aircraft are rarely made of steel, mainly because steel boxes have poor heat dissipation. In hot weather, the storage and transportation boxes are exposed to direct sunlight, which can easily cause serious temperature rise in the box, and the temperature inside the box may exceed the specified aircraft storage temperature.

[0004] Therefore, it is necessary to design a new storage and transportation box for aircraft to overcome the problems mentioned above. Summary of the invention

[0005] The present application provides an aircraft storage and transportation box, which can solve the technical problem in the related art that the steel storage and transportation box has poor heat dissipation, which easily causes serious temperature rise in the box under direct sunlight and the temperature in the box may exceed the specified aircraft storage temperature.

[0006] In a first aspect, an embodiment of the present application provides a storage and shipping box for an aircraft, comprising: a box body and an anti-radiation and heat-insulating coating, wherein the box body has a storage room, and a plurality of heat-insulating cavities are arranged in a top plate of the box body; the anti-radiation and heat-insulating coating is applied to the surface of the box body.

[0007] Among them, the storage and transportation box of the aircraft also includes a front sealing cover and a rear sealing cover, and the front sealing cover and the rear sealing cover are arranged at both ends of the box body. The box body can be made of steel, such as steel sections and steel plates. The steel sections and steel plates have high strength and low cost, which can effectively reduce the cost of the box body and ensure the economy of the storage and transportation box of the aircraft. The storage room can be used to store aircraft. Due to the low thermal conductivity of air, the thermal conductivity of air at 20°C is 0.023W / (m·°C), and the multiple insulating cavities can reduce the conduction of solar heat radiation into the box body. The anti-radiation heat insulation coating is applied to the outer surface of the box body. The anti-radiation heat insulation coating can highly reflect solar heat radiation and is not easy to accumulate heat on the surface of the box body, so that the temperature rise in the box body under solar heat radiation is controlled within the storage temperature range of the aircraft.

[0008] In combination with the first aspect, in one embodiment, the plurality of heat-insulating cavities are interconnected, and the heat-insulating cavities are connected to the outside. The plurality of heat-insulating cavities are interconnected, so that the hot air in the top plate can circulate, and the heat-insulating cavities are connected to the outside, so that the hot air in the top plate can be exchanged with the cold air outside, so that the plurality of heat-insulating cavities can reduce the conduction of solar heat radiation into the box body, and can also exchange the hot air in the top plate out.

[0009] In combination with the first aspect, in one embodiment, the top plate of the box body includes an upper skin and a top skin, and the upper skin and the top skin are connected by a plurality of support tubes arranged between the upper skin and the top skin, and the plurality of support tubes are staggered horizontally and vertically to separate the upper skin and the top skin into a plurality of the thermal insulation cavities; the plurality of support tubes are intermittently welded to the upper skin to form intermittent welds between the plurality of support tubes and the upper skin, and the plurality of the thermal insulation cavities are interconnected through the intermittent welds, and the thermal insulation cavities are connected to the outside through the intermittent welds.

[0010] Among them, the top skin can ensure that the top appearance of the box body is flat and prevent rainwater from entering the insulation cavity. Multiple supporting tubes are staggered horizontally and vertically to separate the upper skin and the top skin into multiple insulation cavities. Multiple supporting tubes are intermittently welded to the upper skin, so that the multiple insulation cavities can be interconnected through the intermittent welds, and can also be connected to the outside through the intermittent welds, so that the multiple insulation cavities can not only reduce the conduction of solar heat radiation into the box body, but also exchange the hot air of the top plate through the intermittent welds, thereby ensuring air convection and exchange in the top plate.

[0011] In combination with the first aspect, in one embodiment, the main components of the radiation protection and thermal insulation coating include super weather resistant resin, high-reflection and low-thermal conductivity filler, sintered filler and reinforced filler, wherein the main components of the high-reflection and low-thermal conductivity filler include flaky aluminum foil and hollow microspheres, and the thickness of the radiation protection and thermal insulation coating is set to 400-600 μm.

[0012] Among them, the flaky aluminum foil can be set to account for 1% to 2% of the total weight of the material of the radiation protection and heat insulation coating. Preferably, the flaky aluminum foil accounts for 1.5% of the total weight of the material of the radiation protection and heat insulation coating. The flaky aluminum foil can reflect more than 60% to 90% of thermal radiation. The hollow microspheres can be set to account for 10% to 20% of the total weight of the material of the radiation protection and heat insulation coating. Preferably, the hollow microspheres account for 15% of the total weight of the material of the radiation protection and heat insulation coating. The thermal conductivity of the hollow microspheres is low, so that the radiation protection and heat insulation coating has a good heat insulation effect. The thickness of the radiation protection and heat insulation coating can be set to 400 to 600 μm. The radiation protection and heat insulation coating is a main reflective and heat-insulating coating, which highly reflects solar radiation, so that solar thermal radiation is not easy to accumulate heat on the surface of the box, and at the same time, the heat accumulated in the box can be scattered to the outside of the box in the form of far-infrared rays.

[0013] In combination with the first aspect, in one embodiment, the radiation-proof heat-insulating coating contains hollow microspheres. The hollow microspheres are the main heat-insulating material, and the hollow microspheres contain rarefied gas. The hollow microspheres have low thermal conductivity, which is 0.03 to 0.09 W / (m·℃), so that the radiation-proof heat-insulating coating has a good heat-insulating effect and can reduce the conduction of solar heat radiation into the box.

[0014] In combination with the first aspect, in one embodiment, a heat-reflecting heat-insulating and anti-rust coating is coated between the box and the anti-radiation heat-insulating coating, and a protective layer is coated on the outside of the anti-radiation heat-insulating coating. The heat-reflecting heat-insulating and anti-rust coating is coated between the box and the anti-radiation heat-insulating coating, so that the surface of the box can be rust-proof and have a certain heat-insulating function, so that the infrared rays transmitted by the anti-radiation heat-insulating coating are reflected away, and the protective layer is coated on the outside of the anti-radiation heat-insulating coating. The protective layer can be set as a green organic silicone heat-resistant coating, so that the surface of the box has a camouflage concealment function, and the thickness of the protective layer can be set to 25 to 50 μm.

[0015] In combination with the first aspect, in one embodiment, the main components of the heat-reflective heat-insulating anti-rust coating include resin, high-floating aluminum powder and anti-rust pigment, and the thickness of the heat-reflective heat-insulating anti-rust coating is set to 25-35 μm. The anti-rust pigment enables the heat-reflective heat-insulating anti-rust coating to have an anti-rust function, the high-floating aluminum powder is arranged neatly, orderly and tightly in the heat-reflective heat-insulating anti-rust coating, reducing the gaps and defects on the surface of the heat-reflective heat-insulating anti-rust coating, and the heat-reflective heat-insulating anti-rust coating can reflect sunlight and infrared rays transmitted by the anti-radiation heat-insulating coating, so that the heat-reflective heat-insulating anti-rust coating has a certain heat-insulating function, wherein the reflectivity of the heat-reflective heat-insulating anti-rust coating to light can reach 75% to 80%.

[0016] In combination with the first aspect, in one embodiment, the bottom plate of the box body includes a lower skin and a plurality of longitudinal tubes, a plurality of the longitudinal tubes are installed on the lower skin, the plurality of the longitudinal tubes are connected by a plurality of transverse lining tubes, at least two positioning and locking seats are arranged between the plurality of the longitudinal tubes, and an electrical connector mounting seat is installed between two of the longitudinal tubes. The box body also includes a left side plate and a right side plate, the left side plate and the right side plate are arranged on opposite sides between the top plate and the bottom plate, so that the box body forms a whole, the positioning and locking seat is used to position the storage and transportation box of the aircraft on the transport vehicle and lock it with the transport vehicle, and the electrical connector mounting seat is used to install an electrical connector so that the electrical components in the storage room can communicate with external devices.

[0017] In combination with the first aspect, in one embodiment, a plurality of stacking blocks are symmetrically arranged on the bottom surface of the lower skin corresponding to the position of the positioning locking seat. The plurality of stacking blocks are symmetrically arranged on the bottom surface of the lower skin corresponding to the position of the positioning locking seat, so that the box can be temporarily or long-term stacked and stored at a set position, thereby improving the adaptability of the aircraft in storage, transportation and shipping.

[0018] In combination with the first aspect, in one embodiment, the bottom plate is installed with a guide rail mechanism, the guide rail mechanism includes a front guide rail and a rear guide rail, the front guide rail is installed at one end of the bottom plate, the rear guide rail is installed at the other end of the bottom plate, the rear guide rail includes a rear guide rail body, and the rear guide rail body is installed with symmetrically arranged guide rails. The front guide rail and the rear guide rail cooperate to make the box body adapt to different types of aircraft, increase the flexibility of the storage, transportation and dispatch box of the aircraft, and at the same time, the interior of the storage, transportation and dispatch box of the aircraft can be adaptively modified to store, transport and launch multiple types of aircraft, so that the storage, transportation and dispatch box of the aircraft can be widely promoted.

[0019] The beneficial effects brought by the technical solution provided in the embodiments of the present application include:

[0020] By arranging multiple insulating cavities in the top plate of the box, solar heat radiation is blocked, and by coating the surface of the box with an anti-radiation heat-insulating coating, solar heat radiation is reflected and heat is not easily accumulated on the surface of the box. The temperature rise in the box under solar heat radiation is controlled within the storage temperature range of the aircraft, which solves the technical problem in the related technology that the heat dissipation of steel storage and transportation boxes is poor, which may cause serious temperature rise in the box under direct sunlight and the temperature inside the box may exceed the specified aircraft storage temperature. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0022] Figure 1 A schematic diagram of the structure of a storage and transportation box for an aircraft provided in an embodiment of the present application;

[0023] Figure 2 A schematic diagram of the structure of the box provided in the embodiment of the present application;

[0024] Figure 3 A schematic diagram of the structure of the top plate provided in the embodiment of the present application;

[0025] Figure 4 A schematic diagram of the structure of the base plate provided in an embodiment of the present application;

[0026] Figure 5 A schematic diagram of a structure in which a guide rail mechanism provided in an embodiment of the present application is installed on a base plate;

[0027] Figure 6 Schematic diagram of hot and cold air exchange in multiple insulation cavities provided in an embodiment of the present application.

[0028] In the figure: 1. box body; 11. top plate; 111. upper skin; 112. top skin; 113. support tube; 114. intermittent weld; 12. bottom plate; 121. lower skin; 122. longitudinal tube; 123. transverse lining tube; 124. positioning locking seat; 125. electrical connector mounting seat; 13. left side plate; 14. right side plate; 2. stacking block; 3. guide rail mechanism; 31. front guide rail; 32. rear guide rail; 321. rear guide rail body; 322. guide rail; 4. front sealing cover; 5. rear sealing cover. DETAILED DESCRIPTION

[0029] In order to enable those skilled in the art to better understand the solution of the present application, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0030] An embodiment of the present application provides an aircraft storage, transportation and dispatch box, which can solve the technical problem in the related art that steel storage, transportation and dispatch boxes have poor heat dissipation, are prone to serious temperature rise in the box under direct sunlight, and the temperature in the box may exceed the specified aircraft storage temperature.

[0031] See also Figure 1 and Figure 2 As shown, the present application provides a storage and shipping box for an aircraft, which includes: a box body 1 and an anti-radiation and heat-insulating coating, wherein the box body 1 has a storage room, and a plurality of heat-insulating cavities are arranged in a top plate 11 of the box body 1; the anti-radiation and heat-insulating coating is coated on the surface of the box body 1.

[0032] In this embodiment, the storage and transportation box of the aircraft also includes a front sealing cover 4 and a rear sealing cover 5, and the front sealing cover 4 and the rear sealing cover 5 are arranged at both ends of the box body 1. The box body 1 can be made of steel, such as steel sections and steel plates. The steel sections and steel plates have high strength and low cost, which can effectively reduce the cost of the box body 1 and ensure the economy of the storage and transportation box of the aircraft. The storage room can be used to store aircraft. Multiple insulating cavities are filled with air. Since the thermal conductivity of air is low, the thermal conductivity of air at 20°C is 0.023W / (m·°C), and multiple insulating cavities can reduce the conduction of solar heat radiation into the box body 1. The anti-radiation heat insulation coating is coated on the outer surface of the box body 1. The anti-radiation heat insulation coating can highly reflect solar heat radiation and is not easy to accumulate heat on the surface of the box body 1, so that the temperature rise in the box body 1 is controlled within the storage temperature range of the aircraft under solar heat radiation.

[0033] In this embodiment, a plurality of heat-insulating cavities are provided in the top plate 11 of the box 1, and the plurality of heat-insulating cavities are filled with air. Since the thermal conductivity of air is low, the plurality of heat-insulating cavities can reduce the conduction of solar thermal radiation into the box 1, so that the solar thermal radiation is blocked. By coating the anti-radiation heat-insulating coating on the surface of the box 1, the solar thermal radiation is reflected and it is not easy to accumulate heat on the surface of the box 1, so that the temperature rise in the box 1 is controlled within the storage temperature range of the aircraft under solar thermal radiation, thereby solving the technical problem in the related art that the heat dissipation of steel storage and transportation boxes is poor, and the temperature rise in the box is likely to be serious under direct sunlight, and the temperature in the box may exceed the specified aircraft storage temperature.

[0034] Further, see Figure 2 and Figure 6 As shown, in some embodiments, a plurality of the heat-insulating cavities are interconnected, and the heat-insulating cavities are connected to the outside. In this embodiment, a plurality of the heat-insulating cavities are interconnected, so that the hot air in the top plate 11 can circulate with each other, and the heat-insulating cavities are connected to the outside, so that the hot air in the top plate 11 can be exchanged with the cold air outside, so that the plurality of the heat-insulating cavities can reduce the conduction of solar heat radiation into the box body 1, and can also exchange the hot air of the top plate 11 out.

[0035] Further, see Figure 2 , Figure 3 and Figure 6 As shown, in some embodiments, in some embodiments, the top plate 11 of the box body 1 includes an upper skin 111 and a top skin 112, and the upper skin 111 and the top skin 112 are connected by a plurality of support tubes 113 arranged between the upper skin 111 and the top skin 112, and the plurality of support tubes 113 are staggered horizontally and vertically to separate the upper skin 111 and the top skin 112 into a plurality of the thermal insulation cavities; the plurality of support tubes 113 and the upper skin 111 are intermittently welded to form intermittent welds 114 between the plurality of support tubes 113 and the upper skin 111, and the plurality of the thermal insulation cavities are interconnected through the intermittent welds 114, and the thermal insulation cavities are connected to the outside through the intermittent welds 114.

[0036] In this embodiment, the top skin 112 can ensure that the top appearance of the box body 1 is smooth and prevent rainwater from entering the insulation cavity. The multiple support tubes 113 are staggered horizontally and vertically to separate the upper skin 111 and the top skin 112 into multiple insulation cavities. The multiple support tubes 113 are intermittently welded to the upper skin 111, so that the multiple insulation cavities can be interconnected through the intermittent welds 114, and can also be connected to the outside through the intermittent welds 114, so that the multiple insulation cavities can reduce the conduction of solar heat radiation into the box body 1, and can also exchange the hot air of the top plate 11 through the intermittent welds 114, thereby ensuring air convection and exchange in the top plate 11.

[0037] Further, see Figure 1 As shown, in some embodiments, the anti-radiation thermal insulation coating main components include super weather resistant resin, high-reflection low-thermal conductivity filler, sintered filler and reinforced filler, wherein the high-reflection low-thermal conductivity filler main components include flaky aluminum foil and hollow microspheres, and the thickness of the anti-radiation thermal insulation coating is set to 400-600 μm.

[0038] In this embodiment, the flaky aluminum foil can be set to account for 1% to 2% of the total weight of the material of the radiation protection and heat insulation coating. Preferably, the flaky aluminum foil accounts for 1.5% of the total weight of the material of the radiation protection and heat insulation coating. The flaky aluminum foil can reflect more than 60% to 90% of thermal radiation. The hollow microspheres can be set to account for 10% to 20% of the total weight of the material of the radiation protection and heat insulation coating. Preferably, the hollow microspheres account for 15% of the total weight of the material of the radiation protection and heat insulation coating. The thermal conductivity of the hollow microspheres is low, so that the radiation protection and heat insulation coating has a good heat insulation effect. The thickness of the radiation protection and heat insulation coating can be set to 400 to 600 μm. The radiation protection and heat insulation coating is a main reflective and heat-insulating coating, which highly reflects solar radiation, so that solar thermal radiation is not easy to accumulate heat on the surface of the box 1, and at the same time, the heat accumulated in the box 1 can be scattered to the outside of the box 1 in the form of far infrared rays.

[0039] Further, see Figure 1 As shown, in some embodiments, the radiation-proof heat-insulating coating contains hollow microspheres. In this embodiment, the hollow microspheres are the main heat-insulating material, and the hollow microspheres contain rarefied gas. The thermal conductivity of the hollow microspheres is low, and the thermal conductivity of the hollow microspheres is 0.03-0.09 W / (m·℃), so that the radiation-proof heat-insulating coating has a good heat-insulating effect, which can reduce the conduction of solar heat radiation into the box 1.

[0040] Further, see Figure 1 As shown, in some embodiments, a heat-reflecting heat-insulating and anti-rust coating is coated between the box body 1 and the anti-radiation heat-insulating coating, and a protective layer is coated on the outside of the anti-radiation heat-insulating coating. In this embodiment, the heat-reflecting heat-insulating and anti-rust coating is coated between the box body 1 and the anti-radiation heat-insulating coating, so that the surface of the box body 1 can be rust-proof and have a certain heat-insulating function, so that the infrared rays transmitted by the anti-radiation heat-insulating coating are reflected away, and the protective layer is coated on the outside of the anti-radiation heat-insulating coating. The protective layer can be set as a green organic silicone heat-resistant coating, so that the surface of the box body 1 has a camouflage concealment function, and the thickness of the protective layer can be set to 25 to 50 μm.

[0041] Further, see Figure 1As shown, in some embodiments, the main components of the heat-reflective heat-insulating anti-rust coating include resin, high-floating aluminum powder and anti-rust pigment, and the thickness of the heat-reflective heat-insulating anti-rust coating is set to 25-35 μm. In this embodiment, the anti-rust pigment enables the heat-reflective heat-insulating anti-rust coating to have an anti-rust function, and the high-floating aluminum powder is arranged neatly, orderly and tightly in the heat-reflective heat-insulating anti-rust coating, reducing the gaps and defects on the surface of the heat-reflective heat-insulating anti-rust coating. The heat-reflective heat-insulating anti-rust coating can reflect sunlight and infrared rays transmitted by the anti-radiation heat-insulating coating, so that the heat-reflective heat-insulating anti-rust coating has a certain heat-insulating function, wherein the reflectivity of the heat-reflective heat-insulating anti-rust coating to light can reach 75% to 80%.

[0042] Further, see Figure 4 As shown, in some embodiments, the bottom plate 12 of the box body 1 includes a lower skin 121 and a plurality of longitudinal tubes 122, a plurality of the longitudinal tubes 122 are installed on the lower skin 121, the plurality of longitudinal tubes 122 are connected by a plurality of transverse lining tubes 123, at least two positioning and locking seats 124 are arranged between the plurality of longitudinal tubes 122, and an electrical connector mounting seat 125 is installed between two longitudinal tubes 122. In this embodiment, the box body 1 also includes a left side plate 13 and a right side plate 14, the left side plate 13 and the right side plate 14 are arranged on opposite sides between the top plate 11 and the bottom plate 12, so that the box body 1 forms a whole, the positioning and locking seats 124 are used to position the storage and transportation box of the aircraft on the transport vehicle and lock and fix it with the transport vehicle, and the electrical connector mounting seat 125 is used to install an electrical connector so that the electrical components in the storage room can communicate with external devices.

[0043] Further, see Figure 1 and Figure 4 As shown, in some embodiments, a plurality of stacking blocks 2 are symmetrically arranged on the bottom surface of the lower skin 121 corresponding to the position of the positioning locking seat 124. In this embodiment, a plurality of stacking blocks 2 are symmetrically arranged on the bottom surface of the lower skin 121 corresponding to the position of the positioning locking seat 124, so that the box body 1 can be temporarily or long-term stacked and stored at a set position, thereby improving the adaptability of the aircraft in storage, transportation and dispatching.

[0044] Further, see Figure 5As shown, in some embodiments, the bottom plate 12 is installed with a guide rail mechanism 3, and the guide rail mechanism 3 includes a front guide rail 31 and a rear guide rail 32. The front guide rail 31 is installed at one end of the bottom plate 12, and the rear guide rail 32 is installed at the other end of the bottom plate 12. The rear guide rail 32 includes a rear guide rail body 321, and the rear guide rail body 321 is installed with symmetrically arranged guide rails 322. In this embodiment, the front guide rail 31 and the rear guide rail 32 cooperate to make the box 1 adaptable to different types of aircraft, increase the flexibility of the storage, transportation and dispatch box of the aircraft, and at the same time, the interior of the storage, transportation and dispatch box of the aircraft can be adaptively modified to store, transport and launch various types of aircraft, so that the storage, transportation and dispatch box of the aircraft can be widely promoted.

[0045] In the description of the present application, it should be noted that the terms "upper", "lower", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0046] It should be noted that, in this application, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the presence of other identical elements in the process, method, article or device including the elements.

[0047] The above description is only a specific implementation of the present application, so that those skilled in the art can understand or implement the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features applied for herein.

Claims

1. A storage and transportation box for aircraft, characterized in that: It includes: A box (1), wherein the box (1) has a storage chamber, and a plurality of heat-insulating cavities are arranged in a top plate (11) of the box (1), wherein the plurality of heat-insulating cavities are interconnected and are connected to the outside; A radiation-proof heat-insulating coating, wherein the radiation-proof heat-insulating coating is coated on the surface of the box (1).

2. The storage and transportation box according to claim 1, characterized in that: The top plate (11) of the box body (1) comprises an upper skin (111) and a top skin (112); the upper skin (111) and the top skin (112) are connected via a plurality of support tubes (113) arranged between the upper skin (111) and the top skin (112); the plurality of support tubes (113) are staggered horizontally and vertically to separate the space between the upper skin (111) and the top skin (112) into a plurality of the heat-insulating cavities; The plurality of support tubes (113) are intermittently welded to the upper skin (111), so that intermittent welds (114) are formed between the plurality of support tubes (113) and the upper skin (111); the plurality of heat-insulating cavities are interconnected through the intermittent welds (114), and the heat-insulating cavities are connected to the outside through the intermittent welds (114).

3. The storage and transportation box according to claim 1, characterized in that: The main components of the radiation-proof thermal insulation coating include super-weather-resistant resin, high-reflection low-thermal conductivity filler, sintered filler and reinforced filler, wherein the main components of the high-reflection low-thermal conductivity filler include flaky aluminum foil and hollow microspheres, and the thickness of the radiation-proof thermal insulation coating is set to 400-600 μm.

4. The storage and transportation box according to claim 1, characterized in that: The radiation-proof and heat-insulating coating contains hollow microspheres.

5. The storage and transportation box according to claim 1, characterized in that: A heat-reflecting, heat-insulating and rust-proof coating is coated between the box body (1) and the anti-radiation and heat-insulating coating, and a protective layer is coated outside the anti-radiation and heat-insulating coating.

6. The storage and transportation box according to claim 5, characterized in that: The heat-reflective, heat-insulating and anti-rust coating mainly comprises resin, high-floating aluminum powder and anti-rust pigment, and the thickness of the heat-reflective, heat-insulating and anti-rust coating is set to 25-35 μm.

7. The storage and transportation box according to claim 1, characterized in that: The bottom plate (12) of the box body (1) comprises a lower skin (121) and a plurality of longitudinal tubes (122), the plurality of longitudinal tubes (122) being mounted on the lower skin (121), the plurality of longitudinal tubes (122) being connected via a plurality of transverse lining tubes (123), at least two positioning locking seats (124) being arranged between the plurality of longitudinal tubes (122), and an electrical connector mounting seat (125) being mounted between two of the longitudinal tubes (122).

8. The storage and shipping box according to claim 7, characterized in that: A plurality of stacking blocks (2) are symmetrically arranged on the bottom surface of the lower skin (121) at positions corresponding to the positioning locking seat (124).

9. The storage and shipping box according to claim 7, characterized in that: The base plate (12) is installed with a guide rail mechanism (3), the guide rail mechanism (3) comprising a front guide rail (31) and a rear guide rail (32), the front guide rail (31) being installed at one end of the base plate (12), the rear guide rail (32) being installed at the other end of the base plate (12), the rear guide rail (32) comprising a rear guide rail body (321), and the rear guide rail body (321) being installed with symmetrically arranged guide rails (322).

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