CN211893639U - Ultrahigh-temperature end heat sealing structure of hypersonic aircraft - Google Patents
Ultrahigh-temperature end heat sealing structure of hypersonic aircraft Download PDFInfo
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- CN211893639U CN211893639U CN201922053742.1U CN201922053742U CN211893639U CN 211893639 U CN211893639 U CN 211893639U CN 201922053742 U CN201922053742 U CN 201922053742U CN 211893639 U CN211893639 U CN 211893639U
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Abstract
The utility model relates to the technical field of thermal protection of hypersonic aircraft, and discloses a hypersonic aircraft ultrahigh-temperature end head thermal sealing structure, which comprises a thermal resistance adapter plate I fixed at the near end of an aircraft end head cap and a thermal resistance adapter plate II fixed at the front end of an aluminum alloy shell of the aircraft; the first thermal resistance adapter plate is fixedly connected with the second thermal resistance adapter plate through a connecting screw; the end cap edge is lapped with the aluminum alloy shell edge butt joint part through a labyrinth groove; the outer wall of the aluminum alloy shell is sequentially provided with an aerogel heat-insulating layer and an outer cabin heat-proof layer from inside to outside. The utility model discloses an end cap and cabin body aluminum alloy shell adopt the keysets to be connected, and aluminum alloy shell and end cap are connected the face and are overlap joint labyrinth groove structure, and surface connection staggers with internal surface faying face position, reduces the influence that the outer thermal protection layer of cabin is thermal expansion to reduce the outer thermal protection layer thermal strain of cabin, and reduce the hot gas flow and to transmit heat to the internal portion of cabin, effectively realized the heat-seal, guaranteed the safe and reliable of structure.
Description
Technical Field
The utility model relates to a hot protection technical field of hypersonic aircraft, concretely relates to hypersonic aircraft super high temperature end heat seal structure.
Background
In the process of returning to the atmosphere and then entering the atmosphere, the hypersonic aircraft faces a very severe pneumatic heating environment, as shown in fig. 3, the highest temperature of the surface of the aircraft reaches about 2500K, the pneumatic heating time of the aircraft end, the windward side and other parts facing the pneumatic heating environment is long, and the total heating amount is large; meanwhile, in order to adapt to long-time safe flight, airborne electronic equipment on the aircraft has extremely strict requirements on the internal working temperature environment of the aircraft. Under the severe thermal environment conditions inside and outside the cabin, how to ensure the local and overall thermal safety of the hypersonic aircraft has become one of the key technologies which are urgently needed to be solved by aircraft development.
Under the general condition, according to the characteristics of pneumatic heating on the surface of a hypersonic aircraft, the thermal protection requirements of different aircraft positions are different, the selected materials are different, the aircraft end is in a heat-proof design by adopting refractory metals, and the aircraft cabin body is in a heat-proof design of C/SiC heat-proof layer + aerogel thermal insulation layer + aluminum alloy load-bearing framework, so that the safety of the aircraft structure can be better ensured by the heat-proof designs, but the problem of heat sealing of the ultrahigh-temperature metal end, the outer wall and the inner wall of the cabin body is difficult to effectively solve.
SUMMERY OF THE UTILITY MODEL
Based on above problem, the utility model provides a hypersonic aircraft ultra-high temperature end heat seal structure, the end cap adopts the keysets to be connected with cabin body aluminum alloy shell, aluminum alloy shell is connected the face with the end cap and is the overlap joint labyrinth groove structure, surface connection staggers with internal surface faying face position, reduce the influence that external thermal protection layer of cabin is heated inflation, thereby reduce external thermal protection layer thermal strain of cabin, and reduce the heat flow and to the internal portion heat transfer in cabin, heat seal has effectively been realized, the safe and reliable of structure has been guaranteed.
For solving the above technical problem, the utility model discloses a technical scheme is:
a hypersonic aircraft ultrahigh-temperature end head heat sealing structure comprises a first heat resistance adapter plate fixed at the near end of an aircraft end head cap and a second heat resistance adapter plate fixed at the front end of an aluminum alloy shell of an aircraft; the end head cap and the first thermal resistance adapter plate, the aluminum alloy shell and the second thermal resistance adapter plate, and the first thermal resistance adapter plate and the second thermal resistance adapter plate are fixedly connected through connecting screws; the end cap edge is lapped with the aluminum alloy shell edge butt joint part through a labyrinth groove; the outer wall of the aluminum alloy shell is sequentially provided with an aerogel heat-insulating layer and an outer cabin heat-proof layer from inside to outside.
Further, an outer sealing groove is arranged at the butt joint part of the end cap and the outer heat-proof layer of the cabin body, and quartz cotton filled type quartz fiber casing materials are adopted for outer sealing; the end cap and the bearing shell of the cabin body are provided with inner sealing grooves, and silicon rubber plates are used for sealing.
Furthermore, the end cap is made of a tungsten copper-infiltrated material, the length of the end cap structure is 100mm, the thickness of the stagnation point position is 30mm, and the thickness of the large-area is 10 mm.
Further, the heat-proof layer outside the cabin body is made of C/SiC material with the thickness of 6 mm; the thickness of the aerogel heat insulation layer is 10 mm.
Furthermore, two end heads of the aluminum alloy shell are provided with annular silicon rubber strain isolation layers which are attached along the outer walls of the edges of the end heads; the silicon rubber strain isolation layer is positioned between the outer heat-proof layer of the cabin body and the aluminum alloy shell, and the aerogel heat-proof layer is positioned in a sealed cavity formed by the aluminum alloy shell, the two silicon rubber strain isolation layers and the outer heat-proof layer of the cabin body in a combined mode.
Compared with the prior art, the beneficial effects of the utility model are that:
1) the utility model discloses an end cap and cabin body aluminum alloy shell adopt the keysets to be connected, and aluminum alloy shell and end cap are connected the face and are overlap joint labyrinth groove structure, and surface connection staggers with internal surface faying face position, reduces the influence that the outer thermal protection layer of cabin is thermal expansion to reduce the outer thermal protection layer thermal strain of cabin, and reduce the hot gas flow and to transmit heat to the internal portion of cabin, effectively realized the heat-seal, guaranteed the safe and reliable of structure.
2) An outer sealing groove is arranged at the butt joint part of the end cap and the outer heat-proof layer of the cabin body, and quartz cotton filled type quartz fiber sleeve materials are adopted for outer sealing; an inner sealing groove is designed at the position of the end cap and the bearing shell of the cabin body, and a silicon rubber plate is adopted for sealing; the outer labyrinth groove structure and the inner and outer sealing structures form a reliable end cap sealing structure.
3) The heat seal of the end cap and the aluminum alloy shell is optimized on the basis of the heat-proof and heat-insulating structure of C/SiC + aerogel + aluminum alloy shell, so that the safety of the hypersonic aircraft structure and the working performance requirements of airborne electronic equipment in the hypersonic aircraft structure are further guaranteed.
4) The silicon rubber strain isolation layers are arranged between the heat-proof layers at the two ends of the aluminum alloy shell of the cabin body and the metal shell, and can play a role in coordinating the heat matching performance between the C/SiC heat-proof layers and the aluminum alloy cabin body.
Drawings
FIG. 1 is a structural schematic diagram of an ultrahigh-temperature end heat sealing structure of a hypersonic aircraft in an embodiment;
FIG. 2 is a schematic diagram of the connection between the header cap and the first thermal resistance adapter plate and the second thermal resistance adapter plate in the embodiment;
FIG. 3 is a schematic diagram of the maximum heat flow distribution during reentry of a typical hypersonic vehicle.
Wherein: 1. an end cap; 2. a first thermal resistance adapter plate; 3. a second thermal resistance adapter plate; 4. an aluminum alloy housing; 5. A labyrinth groove; 6. an aerogel thermal insulation layer; 7. an outer heat-proof layer of the cabin; 8. an outer seal groove; 9. an inner seal groove; 10. A silicone rubber strain isolation layer.
Detailed Description
To make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to the following examples and drawings, and the exemplary embodiments and descriptions thereof of the present invention are only used for explaining the present invention, and are not intended as limitations of the present invention.
Example (b):
referring to fig. 1, 2 and 3, the hypersonic aircraft ultrahigh temperature end heat sealing structure comprises a first heat resistance adapter plate 2 fixed at the near end of an aircraft end cap 1 and a second heat resistance adapter plate 3 fixed at the front end of an aluminum alloy shell 4 of the aircraft; the head cap 1 and the first thermal resistance adapter plate 2, the aluminum alloy shell 4 and the second thermal resistance adapter plate 3, and the first thermal resistance adapter plate 2 and the second thermal resistance adapter plate 3 are fixedly connected through connecting screws; the edge of the end cap 1 is lapped with the edge butt joint part of the aluminum alloy shell 4 through a labyrinth groove 5; the outer wall of the aluminum alloy shell 4 is sequentially provided with an aerogel heat-insulating layer 6 and an outer cabin heat-proof layer 7 from inside to outside.
In this embodiment, the head cap 1 is fixed to the first thermal resistance adapter plate 2 by tightening the connecting screw, the second thermal resistance adapter plate 3 is fixed to the aluminum alloy housing 4 of the cabin by tightening the connecting screw, and the first thermal resistance adapter plate 2 is fixed to the second thermal resistance adapter plate 3 by tightening the connecting screw, so that the detachable connection between the head cap 1 and the aluminum alloy housing 4 of the cabin is realized. The aluminum alloy shell 4 and the end cap 1 are connected by the lap joint labyrinth groove 5 structure, so that the thermal strain of the heat-proof layer outside the cabin body can be reduced, the heat transfer of hot air flowing to the inside of the cabin body is reduced, the heat sealing is effectively realized, and the safety and reliability of the structure are ensured.
The end cap 1 in the embodiment is made of a tungsten copper infiltrated material and is used for heat protection; the length of the end cap 1 structure is 100mm, the thickness of the stagnation point position is 30mm, and the thickness of the large-area is 10 mm. In the flying process, the maximum temperature of the outer surface of the end cap 1 can reach 1000 ℃, and the maximum temperature of the inner wall is 740 ℃; the first thermal resistance adapter plate 2 and the second thermal resistance adapter plate 3 are made of stainless steel and are used for providing connection thermal resistance and preventing the internal temperature of the cabin from being high due to radiation heat transfer from the high-temperature end to the cabin.
An outer sealing groove 8 is arranged at the butt joint part of the end cap 1 and the outer heat-proof layer of the cabin body, and quartz cotton filled type quartz fiber sleeve materials are adopted for outer sealing; an inner sealing groove 9 is designed on the end cap 1 and the bearing shell of the cabin body, and a silicon rubber plate is used for sealing an outer labyrinth structure and an inner sealing structure and an outer sealing structure to form a reliable end sealing structure.
The aircraft cabin body adopts a heat-proof and heat-insulating structure of 'C/SiC + aerogel + aluminum alloy shell 4', the C/SiC is a heat-proof layer, and the thickness is 6 mm; the aerogel is a heat insulation layer with the thickness of 10 mm; the aluminum alloy is a force bearing part, and the thickness of the aluminum alloy is 3 mm; the highest temperature of the C/SiC heat-proof layer can reach 1700 ℃, the highest temperature of the aerogel heat-insulating layer 6 is 800 ℃, and the highest temperature of the aluminum alloy bearing framework is 150 ℃. The connecting part of the end cap 1 and the aircraft cabin body is designed into a lap joint labyrinth structure, the lap joint surface positions of the outer surface connection and the inner surface are staggered, and the influence of thermal expansion of the outer heat-proof layer 7 of the cabin body is reduced. The heat seal of the end cap 1 and the aluminum alloy shell 4 is optimized on the basis of the heat-proof and heat-insulating structure of C/SiC + aerogel + aluminum alloy shell 4, so that the safety of the hypersonic aircraft structure and the working performance requirements of airborne electronic equipment in the hypersonic aircraft structure are further guaranteed.
Two ends of the aluminum alloy shell 4 are provided with annular silicon rubber strain isolation layers 10 which are attached along the outer walls of the edges of the ends; the silicon rubber strain isolation layer 10 is positioned between the outer heat-proof layer 7 of the cabin and the aluminum alloy shell 4, and the aerogel heat-proof layer 6 is positioned in a sealed cavity surrounded by the aluminum alloy shell 4, the two silicon rubber strain isolation layers 10 and the outer heat-proof layer 7 of the cabin. The silicon rubber strain isolation layers 10 are arranged between the heat-proof layers at the two ends of the cabin aluminum alloy shell 4 and the metal shell, and can play a role in coordinating the heat matching performance between the C/SiC heat-proof layers and the aluminum alloy cabin.
The embodiment of the present invention is the above. The specific parameters in the above embodiments and examples are only for the purpose of clearly showing the verification process of the present invention, and are not used to limit the protection scope of the present invention, which is still subject to the claims, and all the equivalent structural changes made by using the contents of the specification and drawings of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. The utility model provides a hypersonic aircraft ultra-high temperature end heat seal structure which characterized in that: the heat resistance adapter plate comprises a first heat resistance adapter plate (2) fixed at the near end of an aircraft end cap (1) and a second heat resistance adapter plate (3) fixed at the front end of an aluminum alloy shell (4) of the aircraft; the end head cap (1) is fixedly connected with the first thermal resistance adapter plate (2), the aluminum alloy shell (4) is fixedly connected with the second thermal resistance adapter plate (3), and the first thermal resistance adapter plate (2) is fixedly connected with the second thermal resistance adapter plate (3) through connecting screws; the butt joint part of the edge of the end cap (1) and the edge of the aluminum alloy shell (4) is overlapped through a labyrinth groove (5); the outer wall of the aluminum alloy shell (4) is sequentially provided with an aerogel heat-insulating layer (6) and a cabin outer heat-proof layer (7) from inside to outside.
2. The hypersonic aircraft ultra-high temperature tip heat seal structure of claim 1, wherein: an outer sealing groove (8) is arranged at the butt joint part of the end cap (1) and the outer heat-proof layer (7) of the cabin body, and quartz cotton filled type quartz fiber sleeve materials are adopted for outer sealing; an inner sealing groove (9) is designed at the position of the end cap (1) and the bearing shell of the cabin body, and a silicon rubber plate is used for sealing.
3. The hypersonic aircraft ultra-high temperature tip heat seal structure of claim 1, wherein: the end cap (1) is made of a tungsten copper infiltrated material, the length of the end cap (1) is 100mm, the thickness of a stagnation point position is 30mm, and the thickness of a large-area is 10 mm.
4. The hypersonic aircraft ultra-high temperature tip heat seal structure of claim 1, wherein: the cabin outer heat-proof layer (7) is made of C/SiC material with the thickness of 6 mm; the thickness of the aerogel heat insulation layer (6) is 10 mm.
5. The hypersonic aircraft ultra-high temperature tip heat seal structure of any one of claims 1-4, wherein: two ends of the aluminum alloy shell (4) are provided with annular silicon rubber strain isolation layers (10) which are attached along the outer walls of the edges of the ends; the silicon rubber strain isolation layer (10) is located between the cabin body outer heat-proof layer (7) and the aluminum alloy shell (4), and the aerogel heat-proof layer (6) is located in a sealed cavity surrounded by the aluminum alloy shell (4), the two silicon rubber strain isolation layers (10) and the cabin body outer heat-proof layer (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922053742.1U CN211893639U (en) | 2019-11-25 | 2019-11-25 | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft |
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| CN201922053742.1U CN211893639U (en) | 2019-11-25 | 2019-11-25 | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114771A (en) * | 2019-11-25 | 2020-05-08 | 中国空气动力研究与发展中心 | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft |
| CN113955076A (en) * | 2021-11-11 | 2022-01-21 | 湖北航天技术研究院总体设计所 | Aircraft with wing and cabin section heat insulation structure |
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
-
2019
- 2019-11-25 CN CN201922053742.1U patent/CN211893639U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114771A (en) * | 2019-11-25 | 2020-05-08 | 中国空气动力研究与发展中心 | Ultrahigh-temperature end heat sealing structure of hypersonic aircraft |
| CN113978696A (en) * | 2021-11-08 | 2022-01-28 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
| CN113978696B (en) * | 2021-11-08 | 2024-04-09 | 湖北航天技术研究院总体设计所 | Spacecraft and thermal resistance type end cap mounting structure thereof |
| CN113955076A (en) * | 2021-11-11 | 2022-01-21 | 湖北航天技术研究院总体设计所 | Aircraft with wing and cabin section heat insulation structure |
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