Heat seal structure and aircraft against aerodynamic heating of separation surface

Abstract

The application provides a heat sealing structure for aerodynamic heating of a separation surface and an aircraft, comprising: a sealing structure, a piston exhaust structure and an internal heat insulation structure; the side of the heat protection layer of the aircraft facing away from the atmosphere outside the aircraft is the interior of the aircraft, one end of a separation device is installed in the heat protection layer of the aircraft, and the other end is installed in the interior of the aircraft; a sealing structure is arranged between the separation device and the heat protection layer of the aircraft, an internal heat insulation structure is arranged between the separation device and the interior of the aircraft, and a piston exhaust structure is arranged at the end of the separation device facing the atmosphere outside the aircraft. The sealing structure, the piston exhaust structure and the internal heat insulation structure can not only avoid the direct inflow of aerodynamic heat from the outside of the separation surface into the interior of the aircraft, but also gradually release the internal pressure to balance the aerodynamic heat, thereby solving the heat flow problem of the aircraft during long-time flight after the fairing is separated.

Description

Technical Field

[0001] This invention relates to the field of aerial separation technology for aircraft, and more specifically, to a heat-sealing structure for aerodynamic heating of the separation surface and an aircraft thereof. Background Technology

[0002] The fairing is a crucial structure for high-speed aircraft, responsible for providing a favorable aerodynamic shape and protecting the payload from environmental influences before cruise flight. Once the aircraft reaches a certain altitude, the fairing must be separated and jettisoned in a timely manner to ensure the payload functions properly.

[0003] After the fairing separates, the heat-resistant and insulating layers at the separation interface cannot be used to prevent aerodynamic heat from entering the aircraft. Heat will continuously flow into the interior from the separation interface. On the one hand, heat will further flow into the aircraft through the separation gap; on the other hand, when the heat accumulates to a certain level at the separation interface in direct contact with the atmosphere, it will generate enormous internal pressure, leading to structural damage to the aircraft.

[0004] Therefore, a heat-sealing structure for aerodynamic heating of the separation surface is needed. This structure should not only prevent aerodynamic heat from flowing directly into the aircraft from the outside of the separation surface, but also gradually release the internal pressure to reach aerodynamic thermal equilibrium, thus solving the heat flow problem of the aircraft continuing long-duration flight after fairing separation. Summary of the Invention

[0005] To address the shortcomings of existing technologies, the purpose of this invention is to provide a heat-sealing structure and aircraft for aerodynamic heating of the separation surface.

[0006] A heat-sealing structure for pneumatic heating of a separation surface provided by the present invention includes: a sealing structure, a piston-type exhaust structure, and an internal heat insulation structure;

[0007] The side of the aircraft's heat shield facing away from the external atmosphere is the interior of the aircraft. One end of the separation device is installed inside the heat shield, and the other end is installed inside the aircraft.

[0008] A sealing structure is provided between the separation device and the heat protection layer of the aircraft, an internal heat insulation structure is provided between the separation device and the interior of the aircraft, and a piston-type exhaust structure is provided at the end of the separation device facing the external atmosphere of the aircraft.

[0009] Preferably, the sealing structure comprises: asbestos rubber and fluorosilicone rubber;

[0010] There is a gap between the side of the separation device facing the external atmosphere of the aircraft and the heat shield of the aircraft. The side of the gap facing the interior of the aircraft is sealed by asbestos rubber and fluorosilicone rubber installed on the separation device. The asbestos rubber is located between the fluorosilicone rubber and the gap.

[0011] Preferably, the waist of the separation device extends outward in a circumferential direction to form a skirt. The skirt is located between the heat shield of the aircraft and the interior of the aircraft. A square sealing groove and a circular sealing groove are provided on the side of the skirt close to the heat shield of the aircraft. The asbestos rubber is installed in the square sealing groove, and the fluorosilicone rubber is installed in the circular sealing groove.

[0012] Preferably, the piston-type exhaust structure includes: a piston;

[0013] The separation device has a piston movement groove inside the end facing the external atmosphere of the aircraft. The piston movement groove is connected to the external atmosphere of the aircraft. The diameter of the end of the piston movement groove away from the external atmosphere of the aircraft is smaller than that of the end facing the external atmosphere of the aircraft. The piston is installed in the piston movement groove and slides along the axial direction of the piston movement groove.

[0014] Preferably, the internal hot airflow is located in the cavity between the end of the piston facing away from the external atmosphere of the aircraft and the piston movement groove.

[0015] Preferably, the internal thermal insulation structure includes: a thermal insulation soft structure and a thermal insulation rigid structure;

[0016] The separation device and the interior of the aircraft are separated by layers of heat-insulating soft structure and heat-insulating hard structure, with the heat-insulating soft structure located between the heat-insulating hard structure and the separation device.

[0017] Preferably, a gap is provided between the heat-insulating soft structure and the heat-insulating rigid structure.

[0018] Preferably, a separation surface is provided between the heat shield of the aircraft and the separation device and the external atmosphere of the aircraft.

[0019] Preferably, the piston movement groove is connected to the interior of the aircraft.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1. In terms of thermal protection, this invention uses a two-layer sealing structure to directly isolate the hot airflow, preventing the hot airflow from directly entering the aircraft and transferring heat through thermal convection;

[0022] 2. This invention solves the problem of internal hot airflow being transferred from the inside to the outside through a piston-type exhaust structure, avoiding excessive internal temperature and pressure that could damage the aircraft structure.

[0023] 3. This invention incorporates heat-resistant structures and materials within the aircraft through an internal heat insulation structure, preventing heat from further penetrating the aircraft's interior even if it is conducted through heat conduction. Attached Figure Description

[0024] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0025] Figure 1 This is a schematic diagram of the heat-sealed structure;

[0026] As shown in the figure:

[0027] Detailed Implementation

[0028] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0029] Example 1

[0030] like Figure 1 As shown, this embodiment includes: a sealing structure, a piston-type exhaust structure, and an internal heat insulation structure; the side of the aircraft heat shield 3 facing away from the external atmosphere 1 is the aircraft interior 2; one end of the separation device 12 is installed inside the aircraft heat shield 3, and the other end is installed inside the aircraft interior 2; a sealing structure is provided between the separation device 12 and the aircraft heat shield 3; an internal heat insulation structure is provided between the separation device 12 and the aircraft interior 2; and a piston-type exhaust structure is provided at the end of the separation device 12 facing the external atmosphere 1. A separation surface 4 is provided between the aircraft heat shield 3 and the separation device 12 and the external atmosphere 1.

[0031] The sealing structure includes asbestos rubber 6 and fluorosilicone rubber 7. A gap 5 exists between the periphery of the separation device 12 facing the external atmosphere 1 and the aircraft's heat shield 3. The gap 5 facing the aircraft's interior 2 is sealed by the asbestos rubber 6 and fluorosilicone rubber 7 installed on the separation device 12. The asbestos rubber 6 is located between the fluorosilicone rubber 7 and the gap 5. A skirt extends circumferentially outward from the waist of the separation device 12, located between the aircraft's heat shield 3 and the aircraft's interior 2. A square sealing groove and a circular sealing groove are provided on the side of the skirt closest to the aircraft's heat shield 3. The square sealing groove contains asbestos rubber 6, and the circular sealing groove contains fluorosilicone rubber 7.

[0032] The piston-type exhaust structure includes: a piston 8; a piston movement groove is provided inside the separation device 12 facing the external atmosphere 1 of the aircraft, the interior of the aircraft 2 is connected to the piston movement groove, and the piston movement groove is connected to the external atmosphere 1 of the aircraft. The diameter of the piston movement groove at the end away from the external atmosphere 1 is smaller than that at the end closer to the external atmosphere 1. The piston 8 is installed in the piston movement groove and slides axially along the piston movement groove. The internal hot airflow 9 is located in the cavity between the end of the piston 8 facing away from the external atmosphere 1 and the piston movement groove.

[0033] The internal heat insulation structure includes a flexible heat insulation structure 10 and a rigid heat insulation structure 11. The separation device 12 and the interior of the aircraft 2 are separated by layers of the flexible heat insulation structure 10 and the rigid heat insulation structure 11, with the flexible heat insulation structure 10 located between the rigid heat insulation structure 11 and the separation device 12. A gap is provided between the flexible heat insulation structure 10 and the rigid heat insulation structure 11.

[0034] Example 2

[0035] Example 2 is a preferred example of Example 1.

[0036] The technical problem to be solved in this embodiment is to avoid the risk of excessive heat and structural damage due to excessive pressure inside the aircraft after the fairing is separated, including the sealing structure, piston exhaust structure and internal heat insulation structure.

[0037] The sealing structure uses a double-layer seal of asbestos rubber 6 and fluorosilicone rubber 7 to prevent hot airflow from directly entering the aircraft interior 2 through the gap 5 of the separation surface 4. A piston-type exhaust structure removes excess gas from the heat directly transmitted through the separation surface 4, achieving internal and external thermal balance and preventing internal structural rupture. An internal heat insulation structure prevents the heat already transmitted to the separation surface 4 from further transferring to the aircraft interior 2, avoiding damage to components inside the aircraft interior 2 due to excessive temperature.

[0038] Asbestos rubber 6 consists of a square-section high-temperature resistant asbestos board and a corresponding sealing groove, serving as the primary barrier against hot airflow. Fluorosilicone rubber 7 consists of a circular-section high-temperature resistant asbestos board and a corresponding sealing groove, serving as the secondary barrier against hot airflow.

[0039] The piston-type exhaust structure features a variable-diameter design in the piston movement groove. By changing the compression ratio of the piston movement groove, the internal gas is discharged along the piston's sealing diameter difference gap after the product operates, ensuring the structural integrity and preventing damage at high temperatures after the product operates.

[0040] The internal insulation structure consists of insulation materials with low specific heat ratio and heat protection structure, which ensures that in addition to the direct convection of heat from the hot airflow, it further prevents heat conduction into the interior of the aircraft, thus eliminating potential heat hazards.

[0041] Specifically, such asFigure 1 As shown, in this embodiment, after the fairing separates, the space is divided into three parts: the external atmosphere 1, the interior of the aircraft 2, and the heat shield 3. Due to the presence of the separation surface 4, there is a certain gap 5 between the separation device 12 and the heat shield 3.

[0042] This embodiment consists of asbestos rubber 6, fluorosilicone rubber 7, piston 8, heat-insulating soft structure 10, and heat-insulating hard structure 11.

[0043] The double-layer seal of asbestos rubber 6 and fluorosilicone rubber 7 prevents hot air from flowing directly into the aircraft interior 2 through the gap 5 of the separation surface 4. The asbestos rubber 6 is in direct contact with the hot air, which first isolates most of the hot air from entering the interior. The temperature of the hot air passing through this layer drops significantly. Under the action of the fluorosilicone rubber 7, the gas is completely sealed, and the hot air is ultimately blocked to the outside of the structure.

[0044] The separation device 12 uses a piston 8 structure for separation, such as Figure 1 As shown by the dashed line at the position of piston 8, piston 8 moves outward after separation. A variable-diameter structure is used in the piston movement groove. By changing the compression ratio of the gap between the piston movement groove and piston 8, the internal hot airflow 9 is discharged along the sealed gap after the product operates. When the temperature rises, the internal pressure increases. The increased pressure discharges excess gas through the sealed gap, achieving dynamic equilibrium and ensuring the structural integrity and non-destruction of the product at high temperatures after operation.

[0045] The internal thermal insulation structure prevents heat already transferred to the separation surface from further penetrating into the aircraft. This internal thermal insulation structure comprises a flexible thermal insulation structure 10 and a rigid thermal insulation structure 11. The flexible thermal insulation structure 10 utilizes commercially available thermal insulation materials with extremely low specific heat ratios. When heat is conducted into the interior through the separation interface 4, the heat transferred there is insulated. The rigid thermal insulation structure 11 acts as a shape-maintaining element, preventing excessive deformation caused by thermal stress, and also provides further thermal insulation between itself and the flexible thermal insulation structure 10.

[0046] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0047] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A heat-sealing structure for pneumatic heating of a separation surface, characterized in that, include: Sealed structure, piston-type exhaust structure, and internal heat insulation structure; The side of the aircraft heat shield (3) facing away from the external atmosphere (1) is the aircraft interior (2). One end of the separation device (12) is installed inside the aircraft heat shield (3), and the other end is installed inside the aircraft interior (2). A sealing structure is provided between the separation device (12) and the heat shield layer (3) of the aircraft, and an internal heat insulation structure is provided between the separation device (12) and the interior (2) of the aircraft. A piston-type exhaust structure is provided at the end of the separation device (12) facing the external atmosphere (1) of the aircraft. The piston-type exhaust structure includes: piston (8); The separation device (12) has a piston movement groove inside the end facing the external atmosphere (1) of the aircraft. The piston movement groove is connected to the external atmosphere (1) of the aircraft. The diameter of the end of the piston movement groove away from the external atmosphere (1) of the aircraft is smaller than that of the end close to the external atmosphere (1) of the aircraft. The piston (8) is installed in the piston movement groove and slides along the axial direction of the piston movement groove. The internal hot airflow (9) is located in the cavity between the end of the piston (8) facing away from the external atmosphere (1) of the aircraft and the piston movement groove.

2. The heat-sealing structure for pneumatic heating of the separation surface according to claim 1, characterized in that, The sealing structure includes: asbestos rubber (6) and fluorosilicone rubber (7). There is a gap (5) between the side of the separation device (12) facing the external atmosphere (1) of the aircraft and the heat shield (3) of the aircraft. The gap (5) facing the interior (2) of the aircraft is sealed by asbestos rubber (6) and fluorosilicone rubber (7) installed on the separation device (12). The asbestos rubber (6) is located between the fluorosilicone rubber (7) and the gap (5).

3. The heat-sealing structure for pneumatic heating of the separation surface according to claim 2, characterized in that: The separation device (12) has a skirt extending outward in the circumferential direction at its waist. The skirt is located between the heat shield layer (3) of the aircraft and the interior (2) of the aircraft. A square sealing groove and a circular sealing groove are provided on the side of the skirt close to the heat shield layer (3) of the aircraft. The asbestos rubber (6) is installed in the square sealing groove, and the fluorosilicone rubber (7) is installed in the circular sealing groove.

4. The heat-sealing structure for pneumatic heating of the separation surface according to claim 1, characterized in that, The internal thermal insulation structure includes: a thermal insulation soft structure (10) and a thermal insulation rigid structure (11); The separation device (12) and the interior of the aircraft (2) are separated by layers of the heat-insulating soft structure (10) and the heat-insulating hard structure (11), with the heat-insulating soft structure (10) located between the heat-insulating hard structure (11) and the separation device (12).

5. The heat-sealing structure for pneumatic heating of the separation surface according to claim 4, characterized in that: A gap is provided between the thermal insulation soft structure (10) and the thermal insulation hard structure (11).

6. The heat-sealing structure for pneumatic heating of the separation surface according to claim 1, characterized in that: A separation surface (4) is provided between the heat shield (3) of the aircraft and the separation device (12) and the external atmosphere (1) of the aircraft.

7. The heat-sealing structure for pneumatic heating of the separation surface according to claim 1, characterized in that: The interior of the aircraft (2) is connected to the piston movement groove.

8. An aircraft, characterized in that: The aircraft employs the heat-sealing structure for aerodynamic heating of the separation surface as described in any one of claims 1-7.

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