CN113586719B - Sealing structure for oil cover of auxiliary oil tank of airplane - Google Patents
Sealing structure for oil cover of auxiliary oil tank of airplane Download PDFInfo
- Publication number
- CN113586719B CN113586719B CN202110869519.3A CN202110869519A CN113586719B CN 113586719 B CN113586719 B CN 113586719B CN 202110869519 A CN202110869519 A CN 202110869519A CN 113586719 B CN113586719 B CN 113586719B
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- Prior art keywords
- oil
- sealing
- annular
- auxiliary
- mounting hole
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/062—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces characterised by the geometry of the seat
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/10—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/10—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing
- F16J15/104—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing characterised by structure
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The application provides an aircraft auxiliary fuel tank oil cover sealing structure, which comprises an auxiliary fuel tank shell, a metal oil cover and a fastener, wherein the metal oil cover is arranged on the auxiliary fuel tank shell; the auxiliary oil tank shell is made of a composite material; an oil port is arranged on the side surface of the auxiliary oil tank shell; a first mounting hole is formed in the side surface of the oil port on the auxiliary oil tank shell; the metal oil cover is connected with the oil port; the metal oil cover is provided with an annular sealing seat which is used for sealing a gap between the oil port and the metal oil cover; the annular sealing seat is provided with a second mounting hole, and the fastener penetrates through the first mounting hole and is connected in the second mounting hole. The auxiliary oil tank shell is made of a composite material, so that the overall weight is reduced, and the impact resistance is strong; the annular sealing seat of the metal oil cover is fixedly attached to the shell, so that good sealing performance of the oil port is ensured.
Description
Technical Field
The application belongs to the technical field of aircraft auxiliary fuel tank sealing elements, and particularly relates to an aircraft auxiliary fuel tank oil cover sealing structure.
Background
The auxiliary fuel tank of the aircraft is a fuel tank which is hung under the fuselage or wings of the aircraft and has thick middle and streamline two tips. The auxiliary oil tank can be hung to increase the voyage and the endurance time of the aircraft, and when the aircraft performs air combat, the auxiliary oil tank can be thrown away when necessary, so that the aircraft can be thrown into combat with better maneuverability.
In the prior art, the auxiliary oil tank shell is made of metal materials so as to improve the strength of the whole shell, and the impact resistance of the shell is high. The oil port of the auxiliary oil tank shell is connected with a metal oil cover so as to avoid the leakage of oil at the oil port. And set up first screw thread through-hole on the metal oil lid, set up the second screw thread through-hole on the casing, adopt the bolt to pass first screw thread through-hole, second screw thread through-hole in proper order, adopt the terminal nut to fix, the terminal setting of bolt is in the inside of casing to consolidate the oil lid.
However, the auxiliary fuel tank housing is made of a metal material, and the whole housing is heavy and has poor impact resistance. All set up the screw thread through-hole on the casing and the oil lid, bolt lug connection is in two screw thread through-holes departments, and the position that two screw thread through-holes are connected with the bolt can appear the phenomenon of oil leak easily, leads to the sealed effect of metal oil lid poor.
Disclosure of Invention
In view of the above, the application aims to provide an oil cover sealing structure of an auxiliary oil tank of an aircraft, which solves the problems in the prior art that the auxiliary oil tank shell is made of metal materials, so that the weight is heavy and the shock resistance is poor; the shell and the metal oil cover are provided with threaded through holes, and after the threaded through holes are connected through bolts, oil leakage easily occurs at the threaded through holes, so that the technical problem of poor sealing effect of the metal oil cover is caused.
In order to achieve the above purpose, the technical scheme of the application is realized as follows:
an aircraft auxiliary fuel tank oil cover sealing structure comprises an auxiliary fuel tank shell, a metal oil cover and a fastener;
the auxiliary oil tank shell is made of a composite material;
an oil port is arranged on the side surface of the auxiliary oil tank shell; a first mounting hole is formed in the side surface of the oil port on the auxiliary oil tank shell;
the metal oil cover is connected with the oil port; the metal oil cover is provided with an annular sealing seat which is used for sealing a gap between the oil port and the metal oil cover;
the annular sealing seat is provided with a second mounting hole, and the fastener penetrates through the first mounting hole and is connected in the second mounting hole.
Further, a sealing column is arranged on the annular sealing seat along the inner direction of the auxiliary oil tank shell;
the second mounting hole is disposed in the sealing post, and a distal end of the second mounting hole terminates in the sealing post.
Further, the end of the sealing post is arc-shaped.
Further, the surface of the annular sealing seat is an arc-shaped surface which is matched with the inner surface of the auxiliary oil tank shell.
Further, an annular sealing gasket is connected between the annular sealing seat and the inner surface of the auxiliary oil tank shell.
Further, the annular sealing gasket is provided with a third mounting hole for the fastener to penetrate.
Further, on the annular sealing gasket, a reinforcing layer is arranged on the inner surface which is attached to the annular sealing seat.
Further, a sealing groove is arranged on the inner surface of the annular sealing seat, which is attached to the annular sealing gasket;
and a sealing ring is connected in the sealing groove.
Further, the depth of the sealing groove is smaller than the thickness of the sealing ring.
Further, the cross section of the sealing groove is any one of square, trapezoid with inner narrow and outer wide and triangle with inner narrow and outer wide;
the cross section of the sealing ring is any one of square, trapezoid with inner narrow and outer wide, and triangle with inner narrow and outer wide.
Compared with the prior art, the sealing structure of the oil cover of the auxiliary oil tank of the aircraft has the following advantages:
the auxiliary oil tank shell is made of composite materials, and the whole auxiliary oil tank shell is light in weight, high in strength and good in impact resistance; when the metal oil cover is connected with the oil port, the sealing performance of the oil port is good. An annular sealing seat is arranged on the metal oil cover so as to seal and strengthen a gap between the oil port and the metal oil cover, and good sealing performance of the oil port is ensured; the fastener passes through the first mounting hole and is fixed in the second mounting hole to fix the metal oil cover on the auxiliary oil tank shell, ensure the leakproofness between metal oil cover and the auxiliary oil tank shell.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic view of a sealing structure of an aircraft auxiliary fuel tank oil cover in a use state according to an embodiment of the application;
fig. 2 is an enlarged view of a portion a in fig. 1;
FIG. 3 is a schematic view of a metal oil cap according to an embodiment of the present application;
FIG. 4 is a schematic view of an annular gasket according to an embodiment of the present application;
fig. 5 is a schematic structural diagram of a seal ring according to an embodiment of the present application.
Reference numerals illustrate:
100-a secondary oil tank shell; 200-a metal oil cover;
300-fasteners; 101-an oil port;
102-a first mounting hole; 201-an annular seal seat;
202-a second mounting hole; 203-sealing the column;
204-an annular gasket; 205-a third mounting hole;
206-sealing the groove; 207-sealing ring.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other.
In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication 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 in a specific case.
The application will be described in detail below with reference to the drawings in connection with embodiments.
As shown in fig. 1 to 5, the present application provides an aircraft auxiliary fuel tank oil cap sealing structure, comprising an auxiliary fuel tank housing 100, a metal oil cap 200 and a fastener 300;
the auxiliary fuel tank shell 100 is made of composite materials;
an oil port 101 is formed in the side face of the auxiliary oil tank shell 100; a first mounting hole 102 is provided in the side surface of the oil port 101 in the auxiliary oil tank case 100;
the metal oil cover 200 is connected with the oil port 101; the metal oil cover 200 is provided with an annular sealing seat 201, and the annular sealing seat 201 is used for sealing a gap between the oil port 101 and the metal oil cover 200;
the annular seal seat 201 is provided with a second mounting hole 202, and the fastener 300 passes through the first mounting hole 102 and is connected in the second mounting hole 202.
Specifically, referring to fig. 1, the auxiliary fuel tank housing 100 is made of a composite material, the weight of the entire auxiliary fuel tank housing 100 is reduced by the composite material, and the auxiliary fuel tank housing 100 has high strength and good impact resistance; because the auxiliary oil tank shell 100 is made of composite materials, the metal oil cover 200 is made of metal materials, and when the metal oil cover 200 is connected with the oil port 101, the metal and the composite materials are more firmly attached, and the sealing performance is better. And when mass production is carried out, compared with the prior art that the auxiliary oil tank shell 100 is made of a metal material, the auxiliary oil tank shell 100 is made of a composite material, and has the advantages of simple production process, low cost, short production period and the like.
Referring to fig. 2, the annular seal holder 201 and the metal oil cap 200 are integrally formed, and are made of metal materials. The fastener 300 employs a screw. The first mounting hole 102 is a screw hole formed in the side surface of the tank case 100 at the side surface of the oil port 101. When the metal oil cover 200 is connected with the oil port 101, the upper end surface of the annular sealing seat 201 is just attached to the inner surface of the auxiliary oil tank shell 100, and the oil port 101 is sealed by the upper surface of the annular sealing seat 201. The second mounting hole 202 is a threaded blind hole formed in the annular seal seat 201. When in use, the screw passes through the threaded through hole and is fixed in the threaded blind hole, so as to fix the annular sealing seat 201 on the auxiliary oil tank shell 100, and seal and fix the metal oil cover 200 and the oil port 101.
In another embodiment of the present application, a plurality of threaded through holes are uniformly distributed on the auxiliary oil tank housing 100 along the annular direction of the oil port 101; a plurality of threaded blind holes are correspondingly arranged on the annular sealing seat 201 along the annular direction; the screws are correspondingly multiple; a screw is inserted through a threaded through hole and is fixed in a threaded blind hole. In this embodiment, the structure of a plurality of pairs of uniformly distributed threaded through holes, threaded blind holes and screws is adopted, so that the connection position between the annular sealing seat 201 and the auxiliary fuel tank housing 100 is fixed in the annular direction, and the stability and the tightness of the connection position between the annular sealing seat 201 and the auxiliary fuel tank housing 100 are ensured.
In one embodiment of the present application, as shown in fig. 2 and 3, a seal post 203 is provided on an annular seal seat 201 along the inner direction of the auxiliary tank case 100;
a second mounting hole 202 is provided in the sealing post 203, the end of the second mounting hole 202 terminating in the sealing post 203.
Specifically, the sealing post 203 is a protruding post formed on the lower end surface of the annular sealing seat 201, the sealing post 203 is disposed on the outer surface of the lower end surface of the annular sealing seat 201, and the sealing post 203 is disposed inside the auxiliary fuel tank housing 100, and at the side position of the metal fuel cap 200, the inner space of the auxiliary fuel tank housing 100 is not occupied, and meanwhile, the installation of the annular sealing seat 201 by an operator is facilitated.
A sealing post 203 is provided at the outer surface of the lower end surface of the annular sealing seat 201, and the starting point of the second mounting hole 202 is communicated with the upper surface of the sealing post 203, the end of the second mounting hole 202 is terminated inside the sealing post 203, the end of the screw is terminated inside the sealing post 203, and the tightness of the annular sealing seat 201 is ensured.
In one embodiment of the present application, as shown in fig. 2 and 3, the end of the sealing post 203 is curved.
Specifically, the distal end of the sealing post 203 is provided in an outwardly convex arc shape so as not to be scratched when the operator installs the metal oil cap 200.
In one embodiment of the present application, as shown in fig. 2 and 3, the surface of the annular seal seat 201 is an arcuate surface corresponding to the inner surface of the auxiliary tank case 100.
Specifically, when the metal oil cover 200 is installed, the inner surface of the upper end surface of the annular sealing seat 201 needs to be attached to the inner surface of the auxiliary oil tank housing 100 at the oil port 101, and the inner surface of the auxiliary oil tank housing 100 is an arc surface, so that the inner surface of the annular sealing seat 201 is also set to be an arc surface corresponding to the inner surface of the auxiliary oil tank housing 100, and good tightness of connection between the inner surface of the annular sealing seat 201 and the inner surface of the auxiliary oil tank housing 100 is ensured.
In one embodiment of the present application, as shown in fig. 2 and 4, an annular gasket 204 is connected between the annular seal seat 201 and the inner surface of the auxiliary tank case 100.
Specifically, the annular sealing gasket 204 is made of a silicone rubber material, and the friction between the annular sealing seat 201 and the inner surface of the auxiliary oil tank shell 100 can be increased due to the arrangement of the annular sealing gasket 204, so that the metal oil cover 200 is firmly connected to the oil port 101.
In one embodiment of the present application, as shown in fig. 2 and 4, the annular gasket 204 is provided with a third mounting hole 205 for the fastener 300 to pass through.
Specifically, the third mounting hole 205 is a threaded through hole formed in the annular gasket 204. In use, the fastener 300 sequentially penetrates through the first mounting hole 102 and the third mounting hole 205 and is locked in the second mounting hole 202, so that the annular sealing seat 201 and the annular sealing gasket 204 are connected to the oil port 101 of the auxiliary oil tank shell 100.
In another embodiment of the present application, a plurality of third mounting holes 205 are uniformly distributed on the annular gasket 204 along the annular direction, and the number of the third mounting holes 205 corresponds to the number of the plurality of screws in the above embodiment; in this embodiment, a plurality of third mounting holes 205 are uniformly provided on the annular gasket 204, and the annular gasket 204 is fixed in the annular direction.
In one embodiment of the present application, a reinforcing layer is provided on the inner surface of the annular gasket 204, which is bonded to the annular seal 201.
Specifically, in the first embodiment, the reinforcing layer is provided on the upper surface of the annular gasket 204, and in use, the friction between the upper surface of the annular gasket 204 and the inner surface of the auxiliary fuel tank housing 100 is increased.
In the second embodiment, a reinforcing layer is provided on the lower surface of the annular gasket 204, and when in use, the friction between the lower surface of the annular gasket 204 and the inner surface of the annular seal seat 201 is increased.
In the third embodiment, the reinforcing layers are provided on both the upper surface and the lower surface of the annular gasket 204, and when in use, the friction between the upper surface of the annular gasket 204 and the inner surface of the auxiliary tank case 100, and between the lower surface of the annular gasket 204 and the inner surface of the annular seal seat 201 are increased.
In the above embodiment, the reinforcing layer is an anti-slip ridge, or anti-slip particle, formed on the surface of the annular gasket 204.
In one embodiment of the present application, as shown in fig. 3 and 5, a seal groove 206 is provided on the inner surface of the annular seal seat 201, which is attached to the annular seal 204;
a seal 207 is connected to the seal groove 206.
Specifically, in the first embodiment, the seal groove 206 is an annular groove formed on the inner surface of the upper end surface of the annular seal seat 201; the sealing ring 207 is an annular silicone rubber ring; when the annular silicon rubber ring is used, the annular silicon rubber ring is clamped in the annular groove, friction force between the inner surface of the annular sealing seat 201 and the annular sealing gasket 204 is increased, and stability of a connection position between the annular sealing seat 201 and the annular sealing gasket 204 is ensured.
In the second embodiment, the seal groove 206 is an arc-shaped groove formed on the inner surface of the upper end surface of the annular seal seat 201; the sealing ring 207 is an arc-shaped silicon rubber ring; when the sealing device is used, the arc-shaped silicon rubber ring is clamped in the arc-shaped groove, so that the friction force between the inner surface of the annular sealing seat 201 and the annular sealing gasket 204 is increased, and the stability of the connection position between the annular sealing seat 201 and the annular sealing gasket 204 is ensured. In this embodiment, the seal groove 206 and the seal ring 207 are both arc-shaped, and materials are saved on the premise of not affecting the tightness.
In the third embodiment, the seal groove 206 is a plurality of cylindrical grooves formed on the inner surface of the upper end surface of the annular seal seat 201, and the seal ring 207 may also be a plurality of silicone rubber bosses; when the sealing device is used, a silicon rubber convex column is clamped in one cylindrical groove, so that the friction force between the inner surface of the annular sealing seat 201 and the annular sealing gasket 204 is increased, and the stability of the connection position between the annular sealing seat 201 and the annular sealing gasket 204 is ensured. In this embodiment, the seal groove 206 and the seal ring 207 are both cylindrical, and once a certain silicone rubber boss is damaged, replacement is facilitated.
In one embodiment of the present application, as shown in fig. 2, 3, and 5, the depth of seal groove 206 is less than the thickness of seal ring 207.
Specifically, during the use, the lower terminal surface joint of sealing washer 207 is fixed in the interior bottom surface department of seal groove 206, and the up end of sealing washer 207 slightly projects in the up end of seal groove 206, and the bellied position just laminating chucking is in the lower terminal surface department of annular seal pad 204, increases the leakproofness of the hookup location between annular seal seat 201 and the annular seal pad 204.
In one embodiment of the present application, the cross section of the seal groove 206 is any one of square, trapezoid with inner narrow and outer wide, triangle with inner narrow and outer wide;
the cross section of the seal ring 207 is any one of a square shape, a trapezoid shape with a narrow inside and a wide outside, and a triangle shape with a narrow inside and a wide outside.
Specifically, when both the cross section of the seal groove 206 and the cross section of the seal ring 207 are square, the seal ring 207 can be securely engaged with the seal groove 206.
When both the cross section of the seal groove 206 and the cross section of the seal ring 207 are trapezoidal with the inner narrow and the outer wide, the bonding firmness between the upper end surface of the seal ring 207 and the annular gasket 204 and the supporting firmness of the lower end surface of the seal ring 207 can be ensured.
When the cross section of the seal groove 206 and the cross section of the seal ring 207 are both triangular with a narrow inner portion and a wide outer portion, the adhesion between the upper end surface of the seal ring 207 and the annular gasket 204 can be ensured.
The foregoing description of the preferred embodiments of the application is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the application.
Claims (3)
1. An aircraft bellytank hydraulic fluid port seal structure, its characterized in that: comprises a secondary oil tank shell (100), a metal oil cover (200) and a fastener (300);
the auxiliary oil tank shell (100) is made of a composite material;
an oil port (101) is arranged on the side surface of the auxiliary oil tank shell (100); a first mounting hole (102) is formed in the side surface of the oil port (101) on the auxiliary oil tank shell (100);
the metal oil cover (200) is connected with the oil port (101); the metal oil cover (200) is provided with an annular sealing seat (201), and the annular sealing seat (201) is used for sealing a gap between the oil port (101) and the metal oil cover (200);
the annular sealing seat (201) is provided with a second mounting hole (202), and the fastener (300) penetrates through the first mounting hole (102) to be connected in the second mounting hole (202);
the annular sealing seat (201) is provided with a sealing column (203) along the inner direction of the auxiliary oil tank shell (100);
the second mounting hole (202) is arranged in the sealing post (203), and the tail end of the second mounting hole (202) is terminated in the sealing post (203);
the tail end of the sealing column (203) is arc-shaped;
the surface of the annular sealing seat (201) is an arc-shaped surface which is matched with the inner surface of the auxiliary oil tank shell (100);
an annular sealing gasket (204) is connected between the annular sealing seat (201) and the inner surface of the auxiliary oil tank shell (100);
a third mounting hole (205) for the fastener (300) to penetrate is formed in the annular sealing gasket (204);
a reinforcing layer is arranged on the inner surface of the annular sealing gasket (204) which is attached to the annular sealing seat (201);
a sealing groove (206) is arranged on the inner surface of the annular sealing seat (201) which is attached to the annular sealing gasket (204);
and a sealing ring (207) is connected in the sealing groove (206).
2. The aircraft auxiliary fuel tank port seal structure of claim 1, wherein: the depth of the sealing groove (206) is smaller than the thickness of the sealing ring (207).
3. The aircraft auxiliary fuel tank port seal structure according to claim 2, wherein: the section of the sealing groove (206) is any one of square, trapezoid with inner narrow and outer wide and triangle with inner narrow and outer wide;
the cross section of the sealing ring (207) is any one of square, trapezoid with inner narrow and outer wide and triangle with inner narrow and outer wide.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110869519.3A CN113586719B (en) | 2021-07-30 | 2021-07-30 | Sealing structure for oil cover of auxiliary oil tank of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110869519.3A CN113586719B (en) | 2021-07-30 | 2021-07-30 | Sealing structure for oil cover of auxiliary oil tank of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113586719A CN113586719A (en) | 2021-11-02 |
| CN113586719B true CN113586719B (en) | 2023-10-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110869519.3A Active CN113586719B (en) | 2021-07-30 | 2021-07-30 | Sealing structure for oil cover of auxiliary oil tank of airplane |
Country Status (1)
| Country | Link |
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| CN (1) | CN113586719B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104676008A (en) * | 2015-03-03 | 2015-06-03 | 深圳市长江机械设备有限公司 | Sealing mechanism |
| CN207496947U (en) * | 2017-11-30 | 2018-06-15 | 江西洪都航空工业集团有限责任公司 | A kind of small-sized composite material integral tank filler cap |
| CN209410349U (en) * | 2018-12-11 | 2019-09-20 | 四川航空工业川西机器有限责任公司 | A kind of auxiliary tank of aircraft bleeder plug |
| CN111216875A (en) * | 2018-11-26 | 2020-06-02 | 空中客车营运有限公司 | Aircraft fuel tank port seal |
| CN210830456U (en) * | 2019-11-02 | 2020-06-23 | 浙江吉鑫祥叉车制造有限公司 | Fuel tank cover plate pad and fuel tank cover sealing structure |
| CN111520473A (en) * | 2020-05-06 | 2020-08-11 | 航天特种材料及工艺技术研究所 | Composite material aircraft fuel tank port cover sealing structure and sealing method |
-
2021
- 2021-07-30 CN CN202110869519.3A patent/CN113586719B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104676008A (en) * | 2015-03-03 | 2015-06-03 | 深圳市长江机械设备有限公司 | Sealing mechanism |
| CN207496947U (en) * | 2017-11-30 | 2018-06-15 | 江西洪都航空工业集团有限责任公司 | A kind of small-sized composite material integral tank filler cap |
| CN111216875A (en) * | 2018-11-26 | 2020-06-02 | 空中客车营运有限公司 | Aircraft fuel tank port seal |
| CN209410349U (en) * | 2018-12-11 | 2019-09-20 | 四川航空工业川西机器有限责任公司 | A kind of auxiliary tank of aircraft bleeder plug |
| CN210830456U (en) * | 2019-11-02 | 2020-06-23 | 浙江吉鑫祥叉车制造有限公司 | Fuel tank cover plate pad and fuel tank cover sealing structure |
| CN111520473A (en) * | 2020-05-06 | 2020-08-11 | 航天特种材料及工艺技术研究所 | Composite material aircraft fuel tank port cover sealing structure and sealing method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113586719A (en) | 2021-11-02 |
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