Sealing structure for cabin door of airplane

Abstract

A sealing structure for a cabin door of an airplane can realize an airtight function and a liquid-tight function in the cabin. The sealing device is arranged between a cabin door (1) and a door frame (2) of the cabin and comprises a main sealing cavity (31) which is communicated with the cabin interior (5) through a ventilation hole (314), a root (311), facing the door frame (2), of the main sealing cavity (31) is connected to the door frame (2) in a sealing mode through a fixing base (34), and a sealing tongue piece (33) which is connected to the main sealing cavity (31), is in a hook shape and extends towards the inner side of the cabin. A concave first matching supporting part (11) corresponding to the sealing tongue piece in shape is formed in the position, corresponding to the sealing tongue piece, of the cabin door, a sealing groove (36) sunken towards the door frame side is formed in the connecting position of the sealing tongue piece and the main sealing cavity, and a second matching supporting part (12) protruding towards the door frame side is formed in the position, corresponding to the sealing groove, of the cabin door.

Description

Technical Field

[0001] The invention relates to a sealing structure for a cabin door of an aircraft, in particular to a sealing structure with airtightness and liquid-tightness functions. Background Art

[0002] In the prior art, a sealing structure is provided between the cabin door and the door frame of the aircraft, and the sealing structure generally adopts a tongue-shaped or single-cavity structure. However, as a tongue-shaped sealing structure, the sealing effect on the fitting surface is formed mainly by the rebound deformation of the cantilever end of the sealing structure. When the cabin door is closed, the tongue-shaped sealing structure is squeezed. When pressurized, the sealing structure needs to withstand the pressurization load, but because the sealing structure itself has limited resilience, the air pressure or hydraulic pressure should not be too large. If the tongue-shaped sealing structure is required to meet the airtight and liquid-tight functions at the same time, the design difficulty of the sealing structure becomes greater. Moreover, the tongue-shaped sealing structure has high requirements on the position and posture of the cabin door and the manufacturing process of the sealing structure. Once the position of the cabin door deviates, gas or liquid leakage is likely to occur.

[0003] In addition, as a sealing structure with a single cavity structure, although its airtight function design has a good effect when subjected to gas pressurization load, due to the insufficient resilience of the sealing structure itself, when the liquid pressure load in the cabin acts, it is easy to cause leakage at the contact point of the cabin door and the liquid-tight function cannot be guaranteed.

[0004] Therefore, there is an urgent need for a sealing structure that can achieve airtightness and liquid-tightness at the hatch. Summary of the invention

[0005] The present invention is completed in view of the above-mentioned technical problems, and its purpose is to provide a sealing structure for a cabin door of an aircraft, which has the function of ensuring airtightness and liquid-tightness in the cabin.

[0006] In order to achieve the above-mentioned purpose, a first aspect of the present invention provides a sealing structure for a cabin door of an aircraft, which is clamped between the cabin door and a door frame of the cabin, and the sealing structure for the cabin door of the aircraft includes a main sealing cavity, which is connected to the cabin via a vent, and the root of the main sealing cavity facing the door frame is sealed and connected to the door frame via a fixed base, including a sealing tongue, which is connected to the main sealing cavity, is hook-shaped, and extends toward the inside of the cabin, and a concave first mating support portion corresponding to the shape of the sealing tongue is formed at a portion of the cabin door corresponding to the sealing tongue, a sealing groove recessed toward the door frame side is formed at the connection between the sealing tongue and the main sealing cavity, and a second mating support portion protruding toward the door frame side is formed at a portion of the cabin door corresponding to the sealing groove.

[0007] According to the above structure, by combining the sealing tongue and the concave first mating support part and the sealing groove and the second mating support part, the air-tight function and liquid-tight function between the cabin door and the door frame can be achieved through the contact between the sealing tongue and the first mating support part, and the engagement of the sealing groove and the second mating support part can effectively prevent liquid leakage on the X2 side, so that the above-mentioned air-tight function and liquid-tight function can be further consolidated on the outside of the cabin.

[0008] The sealing structure for an aircraft cabin door according to the second aspect of the present invention is based on the sealing structure for an aircraft cabin door according to the first aspect of the present invention, wherein a main sealing synapse composed of a plurality of circular peaks with vertices is formed on the cabin outer side of the sealing groove on the surface of the main sealing cavity facing the cabin door, and a third inclined mating support portion is formed at a portion of the cabin door corresponding to the main sealing synapse.

[0009] According to the above structure, since the main sealing contact composed of a plurality of circular peaks with vertices is formed on the surface of the main sealing cavity facing the cabin door and on the cabin outer side of the sealing groove, when the cabin door closes the door frame, the main sealing contact contacts the inclined third matching support portion, thereby forming a plurality of sealing paths for preventing gas or liquid leakage on the path flowing from the cabin inner side to the cabin outer side. Thus, the airtight function and the liquidtight function can be further ensured.

[0010] The sealing structure for an aircraft cabin door according to the third aspect of the present invention is based on the sealing structure for an aircraft cabin door according to the second aspect of the present invention, and the third mating support portion is formed as an inclined surface which inclines toward the door frame side as it moves from the inside of the cabin to the outside of the cabin.

[0011] According to the above structure, since the third matching support portion is formed as an inclined surface that is inclined toward the door frame side as it moves from the cabin inner side to the cabin outer side, the inclination of the inclined surface increases the amount of extrusion between the main sealing cavity and the third matching support portion. In this case, if the load of the pressurized gas or liquid in the cabin acts on the sealing structure and applies a thrust toward the cabin outer side to the sealing structure, a large friction force will be generated between the main sealing cavity and the third matching support portion to prevent the sealing structure from being squeezed out of the cabin.

[0012] The sealing structure for an aircraft cabin door of the fourth aspect of the present invention is based on the sealing structure for an aircraft cabin door of any one of the first to third aspects of the present invention, and also includes a secondary sealing cavity, which is connected to the main sealing cavity and extends to the outside of the cabin, and a secondary sealing synapse composed of a plurality of circular peaks with vertices is formed on the surface of the secondary sealing cavity facing the cabin door, and a fourth inclined mating support portion is formed at a portion of the cabin door corresponding to the secondary sealing synapse.

[0013] According to the above structure, a secondary sealing synapse of a secondary sealing cavity is formed on the cabin outer side of the main sealing cavity, which is continuously composed of multiple circular peaks with vertices, and a fourth inclined matching supporting portion is formed at the position of the cabin door corresponding to the secondary sealing synapse. Therefore, a primary sealing structure is also formed on the cabin outer side of the main sealing cavity, which can better realize the airtight function and liquid-tight function between the cabin door and the door frame.

[0014] The sealing structure for an aircraft cabin door of the fifth aspect of the present invention is based on the sealing structure for an aircraft cabin door of the fourth aspect of the present invention, and the fourth mating support portion is connected to the third mating support portion on the outside of the cabin, and is formed as an inclined surface that inclines toward the door frame side as it moves from the inside of the cabin to the outside of the cabin.

[0015] According to the above structure, since the fourth matching support part is connected to the third matching support part on the outside of the cabin, it is formed as an inclined surface that is inclined toward the door frame side as it moves from the inside of the cabin to the outside of the cabin. Therefore, when the cabin door closes the door frame, the secondary sealing synapse is pressed and fitted with the inclined fourth matching support part, thereby forming multiple sealing paths that prevent gas or liquid leakage on the path flowing from the inside of the cabin to the outside of the cabin. In this way, the airtight function and liquid-tight function can be further ensured on the basis of the sealing structure formed by the main sealing synapse and the third matching support part.

[0016] The sealing structure for an aircraft cabin door of the sixth aspect of the present invention is based on the sealing structure for an aircraft cabin door of the fourth aspect of the present invention, wherein the main sealing cavity and the secondary sealing cavity are both hollow, and the root of the door frame side of the main sealing cavity is fixed to the door frame via fasteners, and a main cavity support is extended from the root to the cabin door side.

[0017] According to the above structure, since the main cavity support is connected to the root of the main sealing cavity connected to the door frame and extends toward the door side in the main sealing cavity, when the door closes the door frame and squeezes the main sealing cavity between the two, the main cavity support can limit the maximum compression of the main sealing cavity and provide auxiliary support. In this way, the main sealing cavity can be prevented from being over-extruded and cracked or plastically deformed, thereby extending the life of the main sealing cavity and improving its durability.

[0018] The sealing structure for an aircraft cabin door of the seventh aspect of the present invention is based on the sealing structure for an aircraft cabin door of the fourth aspect of the present invention, and also includes a sealing stopper, which is fastened to the door frame and is formed to abut against the secondary sealing cavity when the cabin door closes the door frame.

[0019] According to the above structure, since it also includes a sealing stopper, the sealing stopper is fastened to the door frame and is formed to abut against the secondary sealing cavity when the cabin door closes the door frame. Therefore, on the basis of sealing achieved by the main sealing cavity, the sealing function can be further enhanced by the abutment between the sealing stopper and the secondary sealing cavity to ensure the reliability of the sealing.

[0020] The sealing structure for an aircraft cabin door of the eighth aspect of the present invention is based on the sealing structure for an aircraft cabin door of the seventh aspect of the present invention, and the sealing baffle is L-shaped, with its transverse portion fixed to the door frame via fasteners, and its longitudinal portion extending to the secondary sealing cavity side.

[0021] According to the above structure, since the sealing baffle is L-shaped, its transverse part is fixed to the door frame via fasteners, and the longitudinal part extends to the secondary sealing cavity side. Therefore, it is convenient for the sealing baffle to be fixed to the door frame and to abut against the secondary sealing cavity.

[0022] The sealing structure for an aircraft door according to a ninth aspect of the present invention is based on the sealing structure for an aircraft door according to any one of the first to third aspects of the present invention, wherein the sealing tongue is made of a material having a resilient deformation property.

[0023] According to the above structure, since the sealing tongue is made of a material with a resilient deformation property, when the door closes the door frame, the sealing tongue can be pressed and fitted with the first matching support portion by utilizing the resilient deformation property of the sealing tongue to form a sealing surface. In this way, the airtight function and the liquidtight function can be fully realized.

[0024] The sealing structure for an aircraft door of the tenth aspect of the present invention is based on the sealing structure for an aircraft door of any one of the first to third aspects of the present invention, and the main sealing cavity is made of a material with rebound deformation properties.

[0025] According to the above structure, since the main sealing cavity is made of a material with rebound deformation performance, when the door closes the door frame, the rebound deformation of the main sealing cavity can be used to squeeze and fit the main sealing cavity and the third matching support portion to form a sealing surface. In this way, the airtight function and the liquid-tight function can be fully realized.

[0026] The sealing structure for an aircraft door according to the eleventh aspect of the present invention is based on the sealing structure for an aircraft door according to the fourth aspect of the present invention, and the secondary sealing cavity is made of a material having a rebound deformation property.

[0027] According to the above structure, since the secondary sealing cavity is made of a material with a resilient deformation property, when the door closes the door frame, the secondary sealing cavity can be compressed and fitted with the fourth matching support portion by utilizing the resilient deformation of the secondary sealing cavity to form a sealing surface. In this way, the airtight function and the liquidtight function can be reliably achieved.

[0028] The twelfth aspect of the present invention provides a cabin door, which is installed on a door frame via a sealing structure for an aircraft cabin door according to any one of the first to eleventh aspects, the sealing structure comprising a sealing tongue, a main sealing cavity and a secondary sealing cavity in sequence from the cabin inner side to the cabin outer side, in the cabin door, a first mating support portion for accommodating the sealing tongue, a third mating support portion corresponding to a main sealing contact formed in the main sealing cavity and a fourth mating support portion corresponding to a secondary sealing contact formed in the secondary sealing cavity are formed in sequence from the cabin inner side to the cabin outer side, a sealing groove recessed toward the door frame side is formed at the connection between the sealing tongue and the main sealing cavity, and a second mating support portion protruding toward the door frame side is formed at a portion of the cabin door corresponding to the sealing groove.

[0029] According to the above structure, the hatch door and the door frame can be sealed at multiple levels by sequentially forming a sealing structure composed of a sealing tongue and a first matching support portion of the hatch door, a sealing structure composed of a sealing groove and a second matching support portion of the hatch door, a sealing structure composed of a main sealing contact of the main sealing cavity and a third matching support portion, and a sealing structure composed of a secondary sealing contact of the secondary sealing cavity and a fourth matching support portion from the inside of the cabin to the outside of the cabin. In this way, the airtight function and the liquidtight function can be reliably ensured. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some preferred embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0031] Figure 1 The diagram is a schematic diagram showing a sealing structure for an aircraft door according to an embodiment of the present invention.

[0032] Figure 2 The present invention is a sealing structure for a cabin door of an aircraft according to an embodiment of the present invention. Figure 1 Schematic diagram of the shape when the hatch is open, obtained by cutting along the AA line.

[0033] Figure 3 The present invention is a sealing structure for a cabin door of an aircraft according to an embodiment of the present invention. Figure 1Schematic diagram of the shape when the hatch is closed, obtained by cutting along the AA line.

[0034] (Explanation of symbols)

[0035] 1 hatch;

[0036] 10. Door body;

[0037] 11 first matching support portion;

[0038] 12 second matching support portion;

[0039] 13 a third matching support portion;

[0040] 14 fourth matching support portion;

[0041] 2 door frames;

[0042] 3. Seals;

[0043] 31 main sealing chamber;

[0044] 310 hollow cavity of the main sealing cavity;

[0045] 311 roots;

[0046] 3111 Avoidance slot;

[0047] 312 main cavity support;

[0048] 313 Primary sealed synapse;

[0049] 314 vents;

[0050] 32 secondary sealing chamber;

[0051] 320 A hollow cavity of the sealing cavity;

[0052] 321 paraseal synapse;

[0053] 33 Sealing tongue;

[0054] 34 fixed base;

[0055] 35 sealing stopper;

[0056] 351 lateral section;

[0057] 352 longitudinal section;

[0058] 36 sealing groove;

[0059] 4 Fasten the screws;

[0060] 5. In the cabin;

[0061] 6 Outside the cabin. DETAILED DESCRIPTION

[0062] Below, refer to Figures 1 to 3 Various embodiments of the sealing structure for an aircraft cabin door of the present invention are described, wherein: Figure 1 The diagram is a schematic diagram showing a sealing structure for an aircraft door according to an embodiment of the present invention. Figure 2 The present invention is a sealing structure for a cabin door of an aircraft according to an embodiment of the present invention. Figure 1 Schematic diagram of the shape when the hatch is open, obtained by cutting along the AA line. Figure 3 The present invention is a sealing structure for a cabin door of an aircraft according to an embodiment of the present invention. Figure 1 Schematic diagram of the shape when the hatch is closed, obtained by cutting along the AA line.

[0063] The sealing structure for the cabin door of an aircraft of the present invention, i.e. the sealing member 3 is as follows Figure 1 It is installed between the cabin door 1 and the door frame 2 as shown by the cross-sectional line AA, and more specifically, between the end of the cabin door 1 close to the cabin interior 5 and the door frame 2.

[0064] In the following, for the sake of convenience, Figure 2 , 3 The direction of the door frame 2 shown in the figure is set as the X direction, one side of the X direction is set as the X1 side, and the other side is set as the X2 side. The direction perpendicular to the X direction is set as the Y direction, one side of the Y direction is set as the Y1 side, and the other side is set as the Y2 side.

[0065] (Sealing structure for aircraft door according to the present embodiment)

[0066] The surface of the cabin door 1 of the aircraft facing the door frame 2 is formed with a cabin door body 10, a first matching support portion 11 located on the X2 side of the cabin door body 10 and in the shape of a groove, a protrusion located on the X2 side of the first matching support portion 11 and adjacent to the first matching support portion 11, namely, a second matching support portion 12, an inclined curved surface located on the X2 side of the second matching support portion 12 and inclined toward the Y1 side as it moves from the X1 side toward the X2 side, namely, a third matching support portion 13, and an inclined curved surface that tilts toward the Y1 side as it moves from the X1 side toward the X2 side from the part of the third matching support portion 13 closer to the Y2 side, namely, a fourth matching support portion 14, and these matching support portions are smoothly connected to each other.

[0067] In this embodiment, if Figure 1 As shown, the door frame 2 as a whole is an annular frame surrounding the cabin door 1, and a seal 3 is sandwiched between the entire circumference of the door frame 2 and the cabin door 1. The seal 3 is composed of a main sealing cavity 31, a secondary sealing cavity 32 and a sealing tongue 33, and its root 311 is fastened to the door frame 2 by a fastening screw 4 via a C-shaped fixed base 34.

[0068] The main sealing cavity 31 is formed into a hollow shape including a hollow cavity 310 inside, including: a root 311 nested in the fixed base 34, a cylindrical main cavity support 312 extending from the root 311 into the hollow cavity 310, a main sealing synapse 313 formed on the peripheral wall of the main sealing cavity 31 facing the cabin door 1 and composed of four continuous circular peaks with vertices, and a vent hole 314 formed on the peripheral wall of the main sealing cavity 31 facing the cabin interior 5.

[0069] The secondary sealing cavity 32 is formed into a substantially elliptical hollow shape including a hollow cavity 320 therein, and a secondary sealing protrusion 321 consisting of four continuous round peaks with apexes is formed on its surface facing the fourth mating support portion 14 .

[0070] The sealing tongue 33 extends from the main sealing cavity 31 to the cabin 5 side, and extends in the opposite direction of the secondary sealing cavity 32 relative to the main sealing cavity 31. Its outer surface material is rubber material, and there is a reinforced fabric layer in the middle, which has excellent tear resistance and rebound deformation performance. In addition, a sealing groove 36 is formed at the connection between the sealing tongue 33 and the main sealing synapse 313, which is concave toward the door frame 2 side.

[0071] As described above, the fastening screw 4 is fixed to the door frame 2 via the fastening hole (not shown) formed at the corresponding position of the door frame 2 and the fastening hole (not shown) formed at the corresponding position of the fixed base 34, so that the root 311 of the main sealing cavity 31 is nested in the C-shaped groove of the fixed base 34. Correspondingly, the root 311 of the main sealing cavity 31 is formed with an escape groove 3111 for escaping the fastening screw 4. In this way, it is possible to avoid interference between the fastening screw 4 and the root 311 of the main sealing cavity 31 when the fastening screw 4 passes through the door frame 2 and is screwed into the fixed base 34, resulting in failure to fully tighten.

[0072] In addition to the above-mentioned components, a sealing stopper 35 is also formed. The sealing stopper 35 is formed of metal material into a roughly L-shape, and its transverse portion 351 is fixedly connected to the door frame 2 via a fastening screw 4, and the longitudinal portion 352 extends from the X2 side end of the transverse portion 351 to the Y2 side. When the cabin door 1 closes the door frame 2, the Y2 side end of the longitudinal portion 352 will abut against the secondary sealing cavity 32. At the same time, the Y2 side surface of the secondary sealing cavity 32 is tightly attached to and squeezed and deformed against the fourth matching support portion 14 of the cabin door 1. In this way, the sealing function between the cabin door 1 and the door frame 2 can be ensured by the rebound deformation of the secondary sealing cavity 32.

[0073] According to the door frame 2, the seal 3 and the hatch 1 as described above, the following sealing structure is formed between the door frame 2 and the hatch 1:

[0074] The sealing structure is formed by the sealing tongue 33 being embedded in the concave first matching support part 11 of the hatch 1; the sealing structure is formed by the second matching support part 12 of the hatch 1 being embedded in the sealing groove 36 between the sealing tongue 33 and the main sealing cavity 31; the sealing structure is formed by the main sealing cavity 31 and the third matching support part 13 of the hatch 1 being pressed and fitted; the sealing structure is formed by the secondary sealing cavity 32 and the fourth matching support part 14 of the hatch 1 being pressed and fitted. Through this four-level sealing structure, the sealing performance can be fully ensured when the hatch 1 closes the door frame 2.

[0075] In the sealing structure as described above, Figure 2 , Figure 3 As shown, the third matching support portion 13 and the fourth matching support portion 14 are both inclined curved surfaces, and the two are transitionally connected by a smooth step, and they form an angle of 20° to 30° with the hatch body 10. This angle can increase the amount of extrusion between the hatch 1 and the seal 3 in the Y direction, thereby increasing the friction between the hatch 1 and the seal 3 in the X direction. In this way, when the pressurized gas or liquid in the cabin 5 pushes the seal 3 toward the outside of the cabin 6, under the action of the above-mentioned friction force, the seal 3 can be effectively prevented from being squeezed out of the cabin 6 by the load generated by the above-mentioned pressurized gas or liquid.

[0076] In addition, if Figure 2 , 3 As shown, the second mating support portion 12 is formed into a round peak shape with an apex protruding from the Y2 side surface of the hatch 1 to the Y1 side. Figure 3 As shown, when the second mating support portion 12 is embedded in the sealing groove 36, the sealing area between the second mating support portion 12 and the sealing groove 36 can be increased by embedding in the Y direction, thereby increasing the airtightness and liquid-tightness between the cabin door 1 and the door frame 2.

[0077] In addition, the first matching support portion 11 and the second matching support portion 12 are formed adjacent to each other in the X direction, and are recessed toward the Y2 side to form an angle of 145° with the door body 10. In this way, the engagement of the hook-shaped sealing tongue 33 with the recessed first matching support portion 11 increases the sealing area between the two, thereby improving the airtightness and liquid-tightness between the door 1 and the door frame 2.

[0078] Each part of the seal 3 is made of materials with rebound deformation performance such as rubber and internal reinforced fabric, for example, silicone rubber or EPDM rubber with excellent environmental medium resistance. On this basis, the seal 3 adopts a composite structure of a double-cavity structure and a sealing tongue, so the seal 3 has excellent rebound deformation performance. In this way, when the cabin 5 is filled with pressurized gas or liquid, the rebound deformation performance of the seal 3 forms a good sealing surface by forming an extrusion fit between the cabin door 1 and the door frame 2, thereby being able to withstand the load generated by the pressurized gas or liquid in the cabin and making the cabin door 1 and the door frame 2 well sealed.

[0079] According to the hatch door 1, the seal 3 and the door frame 2 as described above, when Figure 2 When the hatch door 1 is opened from the door frame 2, the primary sealing cavity 31, the secondary sealing cavity 32 and the sealing tongue 33 are separated from the hatch door 1. Figure 3 When the hatch 1 shown in the figure closes the door frame 2, the main sealing cavity 31, the secondary sealing cavity 32 and the sealing tongue 33 are respectively squeezed and tightly attached to the third matching support part 13, the fourth matching support part 14 and the first matching support part 11 of the hatch 1 and deformed, thereby, the sealing between the hatch 1 and the door frame 2 can be achieved through simple operation.

[0080] In addition, if Figure 2 , 3 As shown in FIG. 1 , the cylindrical main cavity support member 312 extends from the root 311 of the sealing member 3 toward the Y2 side. Figure 3 As shown, when the door frame 2 is closed, the main sealing cavity 31 will be squeezed and deformed until the Y2 side end of the main cavity support 312 abuts against the third matching support portion 13 of the door 1. In this way, the maximum compression amount of the main sealing cavity 31 can be limited by the main cavity support 312, avoiding excessive squeezing of the sealing member 3, thereby improving the life and durability of the sealing member 3.

[0081] (Four-stage sealing structure of the sealing structure for aircraft door of the present embodiment)

[0082] When Figure 3 When the door frame 2 of the hatch door 1 is closed, the sealing tongue 33 is pressed against and deformed by the first matching support portion 11 to form a sealing surface, thereby realizing a first-level sealing structure.

[0083] The apex of the second mating support portion 12 is embedded in the sealing groove 36 to form a sealing contact surface, thereby realizing a second-level sealing structure.

[0084] The main sealing synapse 313 of the main sealing cavity 31 is pressed, adhered and deformed with the third matching support portion 13 of the cabin door 1 to form a plurality of sealing lines, thereby realizing a third-level sealing structure.

[0085] The secondary sealing synapse 321 of the secondary sealing cavity 32 is pressed, adhered and deformed with the fourth matching support portion 14 of the cabin door 1 to form a plurality of sealing lines, thereby realizing a fourth-level sealing structure.

[0086] Through the above-mentioned four-stage sealing structure, the sealing between the cabin door 1 and the door frame 2 can be reliably achieved.

[0087] (Positioning Structure of Sealing Structure for Aircraft Door of the Present Embodiment)

[0088] When Figure 3 When the door frame 2 of the hatch door 1 is closed, the second matching support portion 12 is embedded in the sealing groove 36, so that the sealing member 3 can be positioned in both the X direction and the Y direction.

[0089] The sealing contact surface of the first matching support portion 11 with the sealing tongue piece 33 is in a groove shape, so the main sealing cavity 31 can be positioned in both the X direction and the Y direction.

[0090] Since the third mating support portion 13 and the fourth mating support portion 14 are both formed as inclined surfaces extending toward the Y1 side as they extend from the X1 side toward the X2 side, when the pressurized gas or liquid in the cabin 5 generates a load force on the main sealing cavity 31 toward the outside of the cabin, the inclination of the inclined surface will increase the amount of extrusion between the first mating support portion 11 and the main sealing synapse 313, and between the second mating support portion 12 and the secondary sealing synapse 321, thereby increasing the friction force to prevent the main sealing cavity 31 and the secondary sealing cavity 32 from being pushed outside the cabin 6.

[0091] The main sealing cavity 31 can be connected to the door frame 2 by fixing the main sealing cavity 31 to the door frame 2 via the fixing base 34 and the fastening screws 4. The L-shaped sealing stopper 35 is fixedly connected to the door frame 2 via the fastening screws 4. When the cabin door 1 closes the door frame 2, the sealing stopper 35 will be in close contact with the secondary sealing cavity 32 and squeeze it onto the fourth matching support portion 14 of the cabin door 1. In this way, the movement of the sealing member 3 can be restricted from the X2 side, thereby preventing the sealing member 3 from being squeezed out of the cabin 6 under the action of the pressurized gas or liquid in the cabin 5.

[0092] (Technical Effects of the Sealing Structure for Aircraft Doors of the Embodiment)

[0093] According to the four-stage sealing structure formed as described above, when the cabin 5 is filled with pressurized gas or liquid, under the load generated by it, the compression fitting surface formed by the sealing tongue 33 and the first matching support portion 11 is a concave curved surface, which can not only achieve accurate positioning of the two, but also increase the compression fitting area between the seal 3 and the cabin door 1, reducing the potential risk of leakage. The vertex of the second matching support portion 12 is also fully embedded in the sealing groove 36, forming a positioning and sealing structure facing the Y1 side, thereby achieving the positioning function and the sealing function.

[0094] The main sealing synapse 313 and the secondary sealing synapse 321 are respectively squeezed and fitted with the third mating support part 13 and the fourth mating support part 14 to form a sealing structure with multiple sealing lines. Compared with the sealing structure with a single sealing line, the sealing stability is higher and even if the surface of the seal is damaged, it can maintain a high airtightness and liquid-tightness function.

[0095] On this basis, the four-stage sealing structure as described above can increase the sealing area between the seal 3 and the hatch 1 compared with a single cavity sealing structure or a tongue-shaped sealing structure, thereby avoiding the leakage of gas or liquid due to failure of one of the sealing structures. In this way, the stability and redundancy of the sealing at the hatch can be improved.

[0096] In addition, through Figure 3 The positioning structure shown can firmly position the sealing member 3 between the cabin door 1 and the door frame 2 .

[0097] Above, combined Figures 1 to 3 All technical solutions of the embodiments of the present invention have been clearly and completely described. However, the described embodiments are only part of the embodiments of the present invention. As long as they do not deviate from the scope of the purpose of the present invention, all other embodiments obtained by those skilled in the art without making any creative work belong to the scope to be protected by the present invention.

[0098] In the above embodiment, an angle of 20° to 30° is formed between the third mating support portion and the fourth mating support portion and the door body, and an angle of 145° is formed between the first mating support portion and the door body, but the present invention is not limited to this and may also be an angle of other degrees.

[0099] In the above embodiment, the main sealing synapse and the auxiliary sealing synapse are both formed by four continuous round peaks with vertices, but the present invention is not limited thereto, and the number of the round peaks with vertices may also be other numbers.

[0100] In the above embodiment, the third matching support portion and the fourth matching support portion of the hatch are both formed as inclined surfaces, but the present invention is not limited thereto, and they may also be formed as flat surfaces.

Claims

1. A sealing structure for a cabin door of an aircraft, sandwiched between the cabin door and the door frame of the cabin, characterized in that: The sealing structure for the cabin door of an aircraft comprises a main sealing cavity, which is communicated with the cabin via a vent hole, and the root of the main sealing cavity facing the door frame is sealed and connected to the door frame via a fixed base. It is characterized in that It includes a sealing tongue, which is connected to the main sealing cavity, is hook-shaped, and extends toward the inside of the cabin. A concave first matching support portion corresponding to the shape of the sealing tongue piece is formed at a portion of the hatch corresponding to the sealing tongue piece. A sealing groove is formed at the connection between the sealing tongue and the main sealing cavity and is recessed toward the door frame. A second matching support portion protruding toward the door frame is formed at a portion of the door corresponding to the sealing groove.

2. The sealing structure for an aircraft door according to claim 1, characterized in that: A main sealing contact composed of a plurality of circular peaks with vertices is formed on the surface of the main sealing cavity facing the hatch and on the cabin outer side of the sealing groove. A third matching support portion having an inclined surface is formed at a portion of the door corresponding to the main sealing synapse.

3. The sealing structure for an aircraft door according to claim 2, characterized in that: The third engaging support portion is formed as an inclined surface that is inclined toward the door frame side as it moves from the cabin inner side to the cabin outer side.

4. The sealing structure for an aircraft door according to any one of claims 1 to 3, characterized in that: It also includes a secondary sealing cavity, which is connected to the primary sealing cavity and extends to the outside of the cabin. A secondary sealing synapse composed of a plurality of circular peaks with vertices is formed on the surface of the secondary sealing cavity facing the hatch. A fourth matching support portion having an inclined surface is formed at a portion of the door corresponding to the secondary sealing synapse.

5. The sealing structure for a cabin door of an aircraft according to claim 4, characterized in that: The fourth matching support portion is connected to the third matching support portion on the outside of the cabin, and is formed as an inclined surface that is inclined toward the door frame side as it moves from the inside of the cabin to the outside of the cabin.

6. The sealing structure for a cabin door of an aircraft according to claim 4, characterized in that: The main sealing cavity and the secondary sealing cavity are both hollow. The root of the door frame side of the main sealing cavity is fixed to the door frame via a fastener. A main cavity support is extended from the root toward the door side.

7. The sealing structure for a cabin door of an aircraft according to claim 4, characterized in that: It also includes a sealing stopper, which is fastened to the door frame and is formed to abut against the secondary sealing cavity when the cabin door closes the door frame.

8. The sealing structure for a cabin door of an aircraft according to claim 7, characterized in that: The sealing stopper is L-shaped, with a transverse portion fixed to the door frame via a fastener, and a longitudinal portion extending toward the secondary sealing cavity.

9. The sealing structure for a cabin door of an aircraft according to any one of claims 1 to 3, characterized in that: The sealing tongue is made of a material with rebound deformation performance.

10. The sealing structure for a cabin door of an aircraft according to any one of claims 1 to 3, characterized in that: The main sealing cavity is made of a material with rebound deformation performance.

11. The sealing structure for a cabin door of an aircraft according to claim 4, characterized in that: The secondary sealing cavity is made of a material with rebound deformation performance.

12. A cabin door, mounted on a door frame via the sealing structure for a cabin door of an aircraft according to any one of claims 1 to 11, It is characterized in that The sealing structure includes a sealing tongue, a main sealing cavity and a secondary sealing cavity in sequence from the inside to the outside of the cabin. In the cabin door, a first matching support portion for accommodating the sealing tongue, a third matching support portion corresponding to the main sealing synapse formed in the main sealing cavity, and a fourth matching support portion corresponding to the secondary sealing synapse formed in the secondary sealing cavity are sequentially formed from the cabin inner side to the cabin outer side. A sealing groove is formed at the connection between the sealing tongue and the main sealing cavity and is recessed toward the door frame. A second matching support portion protruding toward the door frame is formed at a portion of the door corresponding to the sealing groove.

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