阅读说明：本技术 一种长航时高超声速飞行器的热防护结构 (Thermal protection structure of hypersonic aircraft during long voyage ) 是由 谭友德 王辉 刘庆 胡善刚 王巧云 王博哲 范开春 于 2021-10-19 设计创作，主要内容包括：本申请涉及飞行器技术领域,特别涉及一种长航时高超声速飞行器的热防护结构。本申请提供的热防护结构包括：防热层,所述防热层包括第一蒙皮和第一支撑骨架,所述第一支撑骨架固定连接在第一蒙皮的内部,所述第一蒙皮和第一支撑骨架的材料为纤维复合材料；隔热层,所述隔热层设置在第一支撑骨架的内部,所述隔热层的材料为气凝胶或石英棉；反射层,所述反射层设置在隔热层和第一支撑骨架之间,所述反射层的材料为镍、银、钛或石英纤维；金属层,所述金属层连接在防热层的下方,其包括第二蒙皮和第二支撑骨架,所述第二支撑骨架固定连接在第二蒙皮的内部,所述第二蒙皮和第二支撑骨架的材料为合金材料。(The application relates to the technical field of aircrafts, in particular to a thermal protection structure of a hypersonic aircraft during long-endurance. The application provides a thermal protection structure includes: the heat-proof layer comprises a first skin and a first support framework, the first support framework is fixedly connected inside the first skin, and the first skin and the first support framework are made of fiber composite materials; the heat insulation layer is arranged inside the first support framework and is made of aerogel or quartz wool; the reflecting layer is arranged between the heat insulation layer and the first supporting framework and is made of nickel, silver, titanium or quartz fibers; the metal layer is connected below the heat-proof layer and comprises a second skin and a second supporting framework, the second supporting framework is fixedly connected inside the second skin, and the second skin and the second supporting framework are made of alloy materials.)

1. A thermal protection structure for a hypersonic aircraft during long endurance, comprising:

the heat-proof layer (1) comprises a first skin (11) and a first support framework (12), wherein the first support framework (12) is fixedly connected inside the first skin (11), and the first skin (11) and the first support framework (12) are made of fiber composite materials;

the heat insulation layer (2) is arranged inside the first support framework (12), and the heat insulation layer (2) is made of aerogel or quartz wool;

the reflecting layer (3) is arranged between the heat insulation layer (2) and the first supporting framework (12), and the reflecting layer (3) is made of nickel, silver, titanium or quartz fibers;

the metal layer (4) is connected below the heat-proof layer (1) and comprises a second skin (41) and a second supporting framework (42), the second supporting framework (42) is fixedly connected inside the second skin (41), and the second skin (41) and the second supporting framework (42) are made of alloy materials.

2. The thermal protection structure for hypersonic aerial vehicles during long voyage according to claim 1, characterized in that the thickness of said first skin (11) is comprised between 6mm and 30mm and the thickness of said first supporting skeleton (12) is comprised between 13mm and 50 mm.

3. The thermal protection structure for hypersonic aerial vehicles during long voyage according to claim 1, characterized in that the lateral surface of said first skin (11) is provided with a plurality of through holes (111), the diameter of said through holes (111) being 0.5mm-3 mm.

4. The thermal protection structure for hypersonic aircraft during long endurance as claimed in claim 1, wherein said fiber composite is carbon fiber composite or quartz fiber composite.

5. The thermal protection structure for hypersonic aerial vehicles during long voyage according to claim 1, characterized in that the thickness of said thermal insulation layer (2) is 6-44 mm.

6. The thermal protection structure for hypersonic aerial vehicles during long voyage according to claim 1, characterized in that said reflecting layer (3) has a thickness of 0.2mm-2 mm.

7. The thermal protection structure for hypersonic aerial vehicles during long voyage according to claim 1, characterized in that said second skin (41) has a thickness of 1mm-5 mm.

8. The thermal protection structure for the hypersonic flight vehicle during long voyage of claim 1, characterized in that the alloy material is titanium alloy, aluminum alloy or alloy steel.

9. The thermal protection structure for hypersonic aircraft during long voyage according to claim 1, characterized in that the inside of said second supporting skeleton (42) is provided with a flow channel (421) and a cooling duct (422) communicating with the flow channel (421).

10. The thermal protection structure for hypersonic aircraft during long voyage according to claim 9, characterized in that the medium in said flow channel (421) and cooling duct (422) is water or fuel oil.

Technical Field

The application relates to the technical field of aircrafts, in particular to a thermal protection structure of a hypersonic aircraft during long-endurance.

Background

The hypersonic aircraft is an aircraft with the flight speed of more than 5 times of sound speed, has the advantages of high-speed maneuverability, quick striking capability, long-distance accurate striking and the like, but the flight speed of the hypersonic aircraft is high, and the temperature of the outer surface of the hypersonic aircraft is increased due to pneumatic heating generated by friction with the atmosphere in the process of flying in the atmosphere, so that the strength and the rigidity of the structure of the hypersonic aircraft are reduced. For a long-endurance high supersonic aircraft with the flight time of 30-90 minutes, the outer surface of the aircraft is in a high-temperature environment for a long time, the heat flow is large, and the requirement on thermal protection is very high.

The currently used thermal protection techniques are mainly of three types: passive cooling thermal protection technology, semi-passive thermal protection technology and active cooling thermal protection technology. For a long-endurance high supersonic aircraft, the passive cooling mode has a thicker heat-proof layer and a large thermal protection structure; the ablation heat protection of the semi-passive heat is easy to change the appearance structure of the aircraft, and the appearance of the aircraft is uncontrollable in the long-time flying process; active cooling mainly adopts a cooling medium (water and fuel oil) for convection cooling, and although effective cooling of the outer surface of the aircraft can be well realized, the cooling method needs to additionally carry water and fuel oil as a heat sink to reduce heat flow inside the aircraft, and the mass of the aircraft is also increased.

Based on the above analysis, it is necessary to provide a thermal protection structure with high heat insulation efficiency and light weight.

Disclosure of Invention

The embodiment of the application provides a thermal protection structure of a hypersonic aircraft during long voyage, and the thermal protection structure is high in heat insulation efficiency and light in weight.

The application provides a hot protective structure of hypersonic aircraft during long voyage, include:

the heat-proof layer comprises a first skin and a first support framework, the first support framework is fixedly connected inside the first skin, and the first skin and the first support framework are made of fiber composite materials;

the heat insulation layer is arranged inside the first support framework and is made of aerogel or quartz wool;

the reflecting layer is arranged between the heat insulation layer and the first supporting framework and is made of nickel, silver, titanium or quartz fibers;

the metal layer is connected below the heat-proof layer and comprises a second skin and a second supporting framework, the second supporting framework is fixedly connected inside the second skin, and the second skin and the second supporting framework are made of alloy materials.

In some embodiments, the first skin has a thickness of 6mm to 30mm and the first support armature has a thickness of 13mm to 50 mm.

In some embodiments, the side surface of the first skin is provided with a plurality of through holes, the diameter of each through hole is 0.5mm-3mm, and the through holes are arranged in an S shape on the side surface of the first skin.

In some embodiments, the fiber composite is a carbon fiber composite or a quartz fiber composite.

In some embodiments, the thermal insulation layer has a thickness of 6mm to 44 mm.

In some embodiments, the reflective layer has a thickness of 0.2mm to 2 mm.

In some embodiments, the second skin has a thickness of 1mm to 5 mm.

In some embodiments, the alloy material is a titanium alloy, an aluminum alloy, or an alloy steel.

In some embodiments, the second supporting framework is internally provided with a flow channel and a cooling pipeline communicated with the flow channel, and the flow channel and the cooling pipeline are arranged in a shape like a Chinese character 'mi'.

In some embodiments, the medium in the flow passage and the cooling pipe is water or fuel oil.

In some embodiments, the flow passages and cooling conduits have an inner diameter of 1mm to 6 mm.

The beneficial effect that technical scheme that this application provided brought includes: the application provides a hot protective structure adopts fibre combined material preparation heat protection layer, sets up insulating layer and reflection stratum simultaneously in the heat protection layer, adopts alloy material preparation metal level, and the whole quality is light, and bearing structure is strong, and specific strength and rigidity are big, have higher thermal-insulated efficiency of preventing, are applicable to long-endurance high supersonic aircraft.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, 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 view of a thermal protection structure of a hypersonic aircraft during long endurance provided in embodiment 1 of the present application;

fig. 2 is a schematic view of an arrangement structure of through holes on a side of a heat protection layer provided in embodiment 1 of the present application;

fig. 3 is a schematic structural diagram of a thermal insulation layer provided in embodiment 1 of the present application;

fig. 4 is a schematic structural view of a flow channel and a cooling pipe provided in embodiment 1 of the present application.

In the figure: 1. a heat shield layer; 11. a first skin; 111. a through hole; 12. a first support frame; 2. a thermal insulation layer; 3. a reflective layer; 4. a metal layer; 41. a second skin; 42. a second support armature; 421. a flow channel; 422. and (6) cooling the pipeline.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all 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 application.

Example 1:

the embodiment 1 of the application provides a thermal protection structure of a hypersonic aircraft during long voyage, and the thermal protection structure is high in heat insulation efficiency and light in weight.

Fig. 1 is a schematic view of a thermal protection structure provided in example 1 of the present application, and referring to fig. 1, the thermal protection structure includes a thermal protection layer 1, a thermal insulation layer 2, a reflective layer 3, and a metal layer 4.

Referring to fig. 1 and 2, the heat-proof layer 1 includes a first skin 11 and a first supporting framework 12, the first supporting framework 12 is bonded inside the first skin 11 through a binder, a plurality of through holes 111 with a diameter of 2mm are formed in the side surface of the first skin 11, the through holes 111 are arranged in an S shape, the thickness of the first skin 11 is 8mm, the thickness of the first supporting framework 12 is 20mm, the first skin 11 and the first supporting framework 12 are made of a quartz fiber reinforced phenolic resin composite material, and the quartz fiber reinforced phenolic resin composite material has the functions of heat resistance, load bearing, ablation resistance and erosion resistance, and also has certain heat-insulating performance.

Referring to fig. 3, insulating layer 2 sets up in the inside of first support skeleton 12, and the thickness of insulating layer 2 is 11mm, and the material of insulating layer 2 is quartz cotton, and quartz cotton is honeycomb arrangement in first support skeleton 12, and the quality is light, specific strength is high, not only has excellent heat-proof quality, still has certain bearing function.

The reflecting layer 3 is arranged between the heat insulation layer 2 and the first supporting framework 12, the thickness of the reflecting layer 3 is 1mm, the reflecting layer 3 is flexible quartz fiber cloth, the flexible quartz fiber cloth is sewn on the first supporting framework 12, the reflecting layer 3 can reflect radiant heat of the heat insulation layer 1 and also has certain bearing capacity.

Referring to fig. 4, the metal layer 4 includes a second skin 41 and a second supporting skeleton 42, the second skin 41 is bonded below the first skin 11 by an adhesive, the second supporting skeleton 42 is bonded inside the second skin 41 by an adhesive, the thickness of the second skin 41 is 3mm, the second skin 41 and the second supporting skeleton 42 are made of titanium alloy, a flow passage 421 and a cooling pipe 422 communicated with the flow passage 421 are arranged inside the second supporting skeleton 42, the cooling pipe 422 is bonded to the second skin 41, the cooling pipe 422 and the flow passage 421 form a structure shaped like a Chinese character 'mi', the inner diameters of the cooling pipe 422 and the flow passage 421 are both 3mm, and fuel oil is injected inside as a cooling medium. The structure that forms "rice" style of calligraphy with runner 421 of cooling tube 422 can not only improve the intensity and the rigidity of second covering 41, can also increase substantially the heat exchange area on fuel and second covering 41 surface, reduces local heat, and then improves thermal protection efficiency, selects the fuel not only can reach the cooling effect for the cooling medium, can also cyclic utilization provide the fuel for the aircraft.

Example 2:

the embodiment 2 of the application provides a thermal protection structure of a hypersonic aircraft during long voyage, and the thermal protection structure is high in heat insulation efficiency and light in weight.

Embodiment 2 provides a schematic diagram of a thermal protection structure similar to that of embodiment 1, and referring to fig. 1 to 4, the thermal protection structure provided in embodiment 2 of the present application includes a thermal protection layer 1, a thermal insulation layer 2, a reflective layer 3, and a metal layer 4.

The heat-proof layer 1 comprises a first skin 11 and a first supporting framework 12, the first supporting framework 12 is fixedly connected inside the first skin 11 through screws, a plurality of through holes 111 with the diameter of 1.5mm are formed in the side face of the first skin 11, the through holes 111 are arranged in an S shape, the thickness of the first skin 11 is 10mm, the thickness of the first supporting framework 12 is 18mm, and the first skin 11 and the first supporting framework 12 are made of carbon fiber composite materials.

Insulating layer 2 sets up in the inside of first support skeleton 12, and the thickness of insulating layer 2 is 10mm, and the material of insulating layer 2 is quartz cotton, and quartz cotton is honeycomb-like arranges in first support skeleton 12, and the quality is light, specific strength is high, not only has excellent heat-proof quality, still has certain bearing function.

Reflecting layer 3 sets up between insulating layer 2 and first support skeleton 12, and the thickness of reflecting layer 3 is 0.5mm, and reflecting layer 3 is the nickel piece, and the nickel piece bonds on first support skeleton 12, and reflecting layer 3 not only can reflect the radiant heat of heat-proof layer 1, still possesses certain bearing capacity.

The metal layer 4 comprises a second skin 41 and a second supporting framework 42, the second skin 41 is bonded below the first skin 11 through a bonding agent, the second supporting framework 42 is fixedly connected inside the second skin 41 through screws, the thickness of the second skin 41 is 2mm, the second skin 41 and the second supporting framework 42 are made of aluminum alloy, a flow channel 421 and a cooling pipeline 422 communicated with the flow channel 421 are arranged inside the second supporting framework 42, the cooling pipeline 422 is bonded with the second skin 41, the cooling pipeline 422 and the flow channel 421 form a structure shaped like a Chinese character 'mi', the inner diameters of the cooling pipeline 422 and the flow channel 421 are both 4mm, and fuel oil is injected inside to serve as a cooling medium. The structure that forms "rice" style of calligraphy with runner 421 of cooling tube 422 can not only improve the intensity and the rigidity of second covering 41, can also increase substantially the heat exchange area on fuel and second covering 41 surface, reduces local heat, and then improves thermal protection efficiency, selects the fuel not only can reach the cooling effect for the cooling medium, can also cyclic utilization provide the fuel for the aircraft.

Example 3:

the embodiment 3 of the application provides a thermal protection structure of a hypersonic aircraft during long voyage, and the thermal protection structure is high in heat insulation efficiency and light in weight.

Embodiment 3 provides a schematic diagram of a thermal protection structure similar to that of embodiment 1, and referring to fig. 1 to 4, the thermal protection structure provided in embodiment 3 of the present application includes a thermal protection layer 1, a thermal insulation layer 2, a reflective layer 3, and a metal layer 4.

The heat-proof layer 1 comprises a first skin 11 and a first supporting framework 12, the first supporting framework 12 is fixedly connected inside the first skin 11 through screws, a plurality of through holes 111 with the diameter of 1.5mm are formed in the side face of the first skin 11, the through holes 111 are arranged in an S shape, the thickness of the first skin 11 is 7mm, the thickness of the first supporting framework 12 is 15mm, the first skin 11 and the first supporting framework 12 are made of quartz fiber reinforced phenolic resin composite materials, and the quartz fiber reinforced phenolic resin composite materials have the functions of heat resistance, bearing, ablation resistance and scouring resistance and also have certain heat insulation performance.

Insulating layer 2 sets up in the inside of first support skeleton 12, and the thickness of insulating layer 2 is 15mm, and the material of insulating layer 2 is the aerogel, and the aerogel is honeycomb-like arranges in first support skeleton 12, and the quality is light, specific strength is high, not only has excellent heat-proof quality, certain bearing function in addition.

The reflecting layer 3 is arranged between the heat insulation layer 2 and the first supporting framework 12, the thickness of the reflecting layer 3 is 1.5mm, the reflecting layer 3 is a titanium sheet, the titanium sheet is bonded on the first supporting framework 12, and the reflecting layer 3 not only can reflect radiant heat of the heat-proof layer 1, but also has certain bearing capacity.

The metal layer 4 comprises a second skin 41 and a second supporting framework 42, the second skin 41 is fixedly connected below the first skin 11 through screws, the second supporting framework 42 is fixedly connected inside the second skin 41 through an adhesive, the thickness of the second skin 41 is 4mm, the second skin 41 and the second supporting framework 42 are made of titanium alloy, a flow channel 421 and a cooling pipeline 422 communicated with the flow channel 421 are arranged inside the second supporting framework 42, the cooling pipeline 422 is attached to the second skin 41, the cooling pipeline 422 and the flow channel 421 form a structure shaped like a Chinese character 'mi', the inner diameters of the cooling pipeline 422 and the flow channel 421 are both 2mm, and water is injected into the inside to serve as a cooling medium. The structure of the shape like a Chinese character 'mi' formed by the cooling pipe 422 and the flow channel 421 can not only improve the strength and rigidity of the second skin 41, but also greatly improve the heat exchange area between water and the surface of the second skin 41, reduce local heat, and further improve the thermal protection efficiency.

Example 4:

the embodiment 4 of the application provides a thermal protection structure of a hypersonic aircraft during long voyage, and the thermal protection structure is high in heat insulation efficiency and light in weight.

Embodiment 4 provides a schematic diagram of a thermal protection structure similar to that of embodiment 1, and referring to fig. 1 to 4, the thermal protection structure provided in embodiment 4 of the present application includes a thermal protection layer 1, a thermal insulation layer 2, a reflective layer 3, and a metal layer 4.

The heat-proof layer 1 comprises a first skin 11 and a first supporting framework 12, the first supporting framework 12 is fixedly connected inside the first skin 11 through a binder, a plurality of through holes 111 with the diameter of 2.5mm are formed in the side face of the first skin 11, the through holes 111 are arranged in an S shape, the thickness of the first skin 11 is 18mm, the thickness of the first supporting framework 12 is 25mm, and the first skin 11 and the first supporting framework 12 are made of carbon fiber composite materials.

Insulating layer 2 sets up in the inside of first support skeleton 12, and the thickness of insulating layer 2 is 20mm, and the material of insulating layer 2 is quartz cotton, and quartz cotton is honeycomb-like arranges in first support skeleton 12, and the quality is light, specific strength is high, not only has excellent heat-proof quality, still has certain bearing function.

The reflecting layer 3 is arranged between the heat insulation layer 2 and the first supporting framework 12, the thickness of the reflecting layer 3 is 0.8mm, the reflecting layer 3 is flexible quartz fiber cloth, the flexible quartz fiber cloth is sewn on the first supporting framework 12, and the reflecting layer 3 not only can reflect radiant heat of the heat-proof layer 1, but also has certain bearing capacity.

The metal layer 4 comprises a second skin 41 and a second supporting framework 42, the second skin 41 is bonded below the first skin 11 through an adhesive, the second supporting framework 42 is fixedly connected inside the second skin 41 through screws, the thickness of the second skin 41 is 2mm, the second skin 41 and the second supporting framework 42 are made of alloy steel, a flow channel 421 and a cooling pipeline 422 communicated with the flow channel 421 are arranged inside the second supporting framework 42, the cooling pipeline 422 is bonded with the second skin 41, the cooling pipeline 422 and the flow channel 421 form a structure shaped like a Chinese character 'mi', the inner diameters of the cooling pipeline 422 and the flow channel 421 are both 4mm, and water is injected into the inside to serve as a cooling medium. The structure of the shape like a Chinese character 'mi' formed by the cooling pipe 422 and the flow channel 421 can not only improve the strength and rigidity of the second skin 41, but also greatly improve the heat exchange area between water and the surface of the second skin 41, reduce local heat, and further improve the thermal protection efficiency.

In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.