CN113415430A - Lug beam structure of auxiliary fuel tank of airplane - Google Patents
Lug beam structure of auxiliary fuel tank of airplane Download PDFInfo
- Publication number
- CN113415430A CN113415430A CN202110869486.2A CN202110869486A CN113415430A CN 113415430 A CN113415430 A CN 113415430A CN 202110869486 A CN202110869486 A CN 202110869486A CN 113415430 A CN113415430 A CN 113415430A
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- Prior art keywords
- hanging
- arc
- hanging beam
- hole
- beam structure
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- 239000002828 fuel tank Substances 0.000 title claims abstract description 35
- 239000007769 metal material Substances 0.000 claims abstract description 11
- 239000002131 composite material Substances 0.000 claims abstract description 9
- 230000003014 reinforcing effect Effects 0.000 claims description 9
- 239000000725 suspension Substances 0.000 description 12
- 239000000463 material Substances 0.000 description 4
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000010030 laminating Methods 0.000 description 1
- 238000011031 large-scale manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/04—Arrangement thereof in or on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention provides a lifting lug beam structure of an aircraft auxiliary fuel tank, which comprises an auxiliary fuel tank shell, a lifting beam and a lifting ring piece, wherein the lifting lug beam structure comprises a lifting lug and a lifting lug; the auxiliary oil tank shell is made of composite materials; a first mounting hole is formed in the side face of the auxiliary oil tank shell, and the first mounting hole is in a stepped shape with a wide inner part and a narrow outer part; the hanging beam is made of metal materials and is clamped at the first mounting hole; the hanging beam is provided with a connecting hole, one end of the hanging ring piece is connected in the connecting hole, and the other end of the hanging ring piece is used for being connected with the lower part of the machine body. The auxiliary oil tank shell is made of composite materials, so that the overall weight is reduced, and the impact resistance is strong; the side surface of the auxiliary oil tank shell is connected with the hanging beam through the first mounting hole, so that one end of the hanging ring piece is fixed at the hanging beam, and the other end of the hanging ring piece is fixed at the lower part of the machine body, thereby ensuring the stability of the connection position between the auxiliary oil tank and the machine body.
Description
Technical Field
The invention belongs to the technical field of aircraft auxiliary fuel tank connecting pieces, and particularly relates to a lifting lug beam structure of an aircraft auxiliary fuel tank.
Background
The airplane auxiliary fuel tank is a fuel tank which is hung below the fuselage or wing of an airplane, has a thick middle part and two sharp ends and is in a streamline shape. The auxiliary fuel tank can be hung to increase the voyage and endurance time of the airplane, and when the airplane is in air battle, the auxiliary fuel tank can be thrown away if necessary, so that the airplane can be put into battle 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 shell has strong impact resistance. A hook is generally welded on the side surface of the auxiliary fuel tank shell, and the hook is connected with the lower part of the fuselage or the lower part of the wing of the airplane so as to fixedly connect the auxiliary fuel tank and the fuselage of the airplane.
However, the secondary fuel tank shell is made of metal materials, so that the whole shell is heavy in weight and poor in impact resistance. The auxiliary fuel tank is fixedly connected with the lower part of the machine body in a hook mode, so that the installation position of the auxiliary fuel tank is unstable easily, and potential safety hazards exist.
Disclosure of Invention
In view of the above, the present invention provides a fuel tank, which solves the problems in the prior art that the weight is heavy and the impact resistance is poor due to the fact that the casing of the auxiliary fuel tank is made of a metal material; the auxiliary fuel tank is connected with the lower part of the machine body in a hook mode, and the mounting position of the auxiliary fuel tank is unstable, so that the technical problem of potential safety hazards exists.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
a lifting lug beam structure of an aircraft auxiliary fuel tank comprises an auxiliary fuel tank shell, a lifting beam and a lifting ring piece;
the auxiliary oil tank shell is made of composite materials;
a first mounting hole is formed in the side face of the auxiliary oil tank shell, and the first mounting hole is in a stepped shape with a wide inner part and a narrow outer part; the hanging beam is made of metal materials and is clamped at the first mounting hole;
the hanging beam is provided with a connecting hole, one end of the hanging ring piece is connected in the connecting hole, and the other end of the hanging ring piece is used for being connected with the lower part of the machine body.
Further, the connection hole terminates inside the suspension beam.
Furthermore, the top surface of the hanging beam is an arc-shaped structural surface which is convex outwards and is matched with the inner wall of the auxiliary oil tank shell.
Furthermore, an arc-shaped mounting surface is arranged on the arc-shaped structural surface.
Furthermore, a connecting column is arranged on the arc-shaped mounting surface and protrudes out of the arc-shaped mounting surface, and the connecting column is clamped in the first mounting hole;
the connecting hole is arranged in the connecting column.
Furthermore, be equipped with the second mounting hole on the arc mounting surface, the quantity of second mounting hole is a plurality of that the equipartition set up.
Furthermore, the side of hanging beam is equipped with the lightening hole, and the quantity of lightening hole is a plurality of that the equipartition set up.
Furthermore, the bottom surface of the hanging beam is of a plane structure.
Furthermore, planar structure is equipped with the reinforcement piece, and the planar structure is connected through the retaining member to the reinforcement piece.
Furthermore, the interior of the hanging beam is of a hollow structure.
Compared with the prior art, the aircraft auxiliary fuel tank lifting lug beam structure 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; a first mounting hole is formed in the side face of the auxiliary oil tank shell, and the first mounting hole is in a stepped shape with a wide inner part and a narrow outer part, so that the hanging beam is clamped and fixed; the hanging beam is made of metal materials, so that the manufacturability of the whole structure is improved; the connecting holes are formed in the hanging beam, one end of the hanging ring piece is fixed, the other end of the hanging ring piece is connected with the lower portion of the machine body, stability of the connecting position between the auxiliary oil tank and the machine body is guaranteed, and the problems that in the prior art, the installation position of the auxiliary oil tank is unstable and potential safety hazards exist due to the fact that the whole auxiliary oil tank is made of metal materials and the machine body is connected in a welded hook mode are solved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic diagram illustrating a usage state of an aircraft drop tank lug structure in an embodiment of the invention;
FIG. 2 is an enlarged view of portion A of FIG. 1;
FIG. 3 is a schematic structural view of a suspension beam in an embodiment of the present invention;
FIG. 4 is a partially cut-away schematic view of a suspension beam in an embodiment of the invention;
FIG. 5 is a front view of a suspension beam in an embodiment of the invention;
FIG. 6 is a top view of a suspension beam in an embodiment of the present invention;
fig. 7 is a bottom view of a suspension beam in an embodiment of the invention.
Description of reference numerals:
100-a secondary tank housing; 200-a hanging beam;
300-a suspension ring member; 101-a first mounting hole;
201-connecting hole; 202-arc structural surface;
203-arc mounting surface; 204-connecting column;
205-a second mounting hole; 206-lightening holes;
207-planar structure; 208-reinforcing blocks.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 to 7, the invention provides an aircraft drop tank lifting lug beam structure, which comprises a drop tank shell 100, a lifting beam 200 and a lifting ring piece 300;
the secondary fuel tank housing 100 is made of a composite material;
a first mounting hole 101 is formed in the side surface of the auxiliary oil tank shell 100, and the first mounting hole 101 is in a ladder shape with a wide inner part and a narrow outer part; the hanging beam 200 is made of metal materials, and the hanging beam 200 is clamped at the first mounting hole 101;
the hanging beam 200 is provided with a connecting hole 201, one end of the hanging ring piece 300 is connected in the connecting hole 201, and the other end of the hanging ring piece 300 is used for connecting the lower position of the machine body.
Specifically, referring to fig. 1 and 2, the secondary fuel tank shell 100 is made of a composite material, the composite material reduces the weight of the whole secondary fuel tank shell 100, and the secondary fuel tank shell 100 has high strength and good impact resistance; because the bellytank casing 100 adopts combined material to make, hanging beam 200 adopts the material of metal to make, when being connected between hanging beam 200 and first mounting hole 101, laminate between the inner wall of hanging beam 200 and bellytank casing 100 mutually, and the laminating is more firm between metal and the combined material, and the leakproofness is better. And when carrying out large-scale production, compare in the prior art, bellytank casing 100 adopts the metal material to make, the bellytank casing 100 of this application adopts combined material to make, has advantages such as production simple process, with low costs, production cycle are short.
Referring to fig. 1 and 2, a first mounting hole 101 is formed in a side surface of the drop tank case 100, and the first mounting hole 101 is a stepped shape having a wide inner side and a narrow outer side, so that a top surface of the hanging beam 200 can be engaged with the stepped hole to fix a mounting position of the hanging beam 200. First mounting hole 101 is the structure of notch cuttype through-hole, and in order to ensure the steadiness of hanging beam 200 when this notch cuttype through-hole department connects, set up the ring channel at the inner wall of this notch cuttype through-hole, joint rubber pad in the ring channel to increase the frictional force between hanging beam 200 and this notch cuttype through-hole, ensure the steadiness of hanging beam 200 in this notch cuttype through-hole department connection.
The middle position of the upper end face of the hanging beam 200 is provided with a connecting hole 201, the connecting hole 201 is a threaded hole, the lower end of the hanging ring piece 300 is provided with a threaded shaft, and the threaded shaft is in threaded connection with the threaded hole so as to fix the lower end position of the hanging ring piece 300. The upper end of the hanging ring piece 300 is provided with a connecting shaft hole, so that a connecting shaft at the lower part of the machine body can be clamped and fixed at the shaft hole, and the upper end of the hanging ring piece 300 is fixed at the lower part of the machine body.
In one embodiment of the present invention, as shown in fig. 2 and 4, the connection hole 201 is terminated inside the hanging beam 200.
Specifically, the connecting hole 201 is a blind threaded hole, so that the blind threaded hole is terminated inside the hanging beam 200, and the end of the threaded shaft at the lower end of the hanging ring piece 300 is terminated inside the hanging beam 200, thereby preventing the lower end of the hanging ring piece 300 from extending out of the hanging beam 200 and damaging other internal structural members of the drop tank housing 100.
In one embodiment of the present invention, as shown in fig. 3 and 5, the top surface of the hanging beam 200 is an outwardly convex arc-shaped structural surface 202 adapted to the inner wall of the secondary fuel tank housing 100.
Specifically, the drop tank case 100 is a cylinder having a thick middle position and thin two end positions, the first mounting hole 101 is formed in the middle position, and the arc-shaped structural surface 202 is formed on the top surface of the hanging beam 200, so that the arc-shaped structural surface 202 can be attached and fixed to the inner wall of the drop tank case 100, and the stability of the connection position between the hanging beam 200 and the drop tank case 100 is ensured.
In other embodiments of the present invention, since the hanging beam 200 is made of a metal material, a layer of rubber pad may be bonded to the top surface of the hanging beam 200, so that the rubber pad is directly attached to the inner wall of the auxiliary fuel tank case 100 made of a composite material, thereby increasing the friction between the hanging beam 200 and the inner wall of the auxiliary fuel tank case 100 and ensuring the firmness between the arc-shaped structural surface 202 at the top of the hanging beam 200 and the inner wall of the auxiliary fuel tank case 100.
In one embodiment of the present invention, as shown in fig. 3 and 5, the arc-shaped structure surface 202 is provided with an arc-shaped mounting surface 203.
Specifically, the arc mounting surface 203 is disposed at a middle position of the arc structure surface 202, and the thickness of the arc mounting surface 203 is greater than that of the arc structure surface 202. During practical use, an arc-shaped groove is formed in the inner wall of the auxiliary fuel tank shell 100, so that the arc-shaped mounting surface 203 is just clamped in the arc-shaped groove, and the top surface of the hanging beam 200 is clamped and fixed.
In other embodiments of the present invention, since the width of the arc-shaped mounting surface 203 is smaller than the width of the arc-shaped structure surface 202, a rubber pad is bonded to the positions adjacent to the left and right side surfaces of the arc-shaped mounting surface 203 at the left and right sides of the top surface of the arc-shaped structure surface 202, so that when the arc-shaped mounting surface 203 is clamped in the arc-shaped groove, the two rubber pads can be attached to the side surfaces of the secondary fuel tank housing 100.
In an embodiment of the present invention, as shown in fig. 3 and 5, a connection column 204 is disposed on the arc-shaped mounting surface 203, the connection column 204 protrudes from the arc-shaped mounting surface 203, and the connection column 204 is clamped to the first mounting hole 101;
the connection hole 201 is provided in the connection post 204.
Specifically, a connecting column 204 is arranged in the middle of the arc-shaped mounting surface 203, and the connecting column 204 protrudes out of the arc-shaped mounting surface 203, so that the protruding position can be clamped in the first mounting hole 101.
The connecting column 204 is a hollow column, and the connecting hole 201 is a threaded blind hole arranged at the hollow part of the connecting column 204, so that a threaded shaft at the lower end of the hanging ring piece 300 can be in threaded connection in the threaded blind hole.
In an embodiment of the present invention, as shown in fig. 3 and 6, the arc-shaped mounting surface 203 is provided with a plurality of second mounting holes 205, and the number of the second mounting holes 205 is a plurality of second mounting holes 205 that are uniformly distributed.
Specifically, the second mounting hole 205 is a blind threaded hole formed in the arc-shaped mounting surface 203, the blind threaded hole terminating inside the suspension beam 200, and a through threaded hole is formed in the side surface of the drop tank case 100 in the circumferential direction of the first mounting hole 101, and a screw is inserted through the through threaded hole and connected in the blind threaded hole to fix the suspension beam 200 and the drop tank case 100.
During actual use, the number of the threaded blind holes is a plurality of uniformly distributed blind holes, the number of the threaded through holes is a plurality of blind holes corresponding to the number of the threaded blind holes, and a plurality of screws are adopted to fix the hanging beam 200 and the auxiliary oil tank shell 100.
In an embodiment of the present invention, as shown in fig. 3 and 6, the side surface of the hanging beam 200 is provided with a plurality of lightening holes 206, and the number of the lightening holes 206 is a plurality of holes arranged in a uniform manner.
Specifically, a plurality of weight-reducing holes 206 are uniformly distributed on the left side and the right side of the hanging beam 200, and the weight-reducing holes 206 are blind holes formed in the side surface of the hanging beam, so that the weight of the whole hanging beam 200 is reduced, and the whole weight of the auxiliary fuel tank shell 100 is reduced.
In one embodiment of the present invention, as shown in fig. 5 and 7, the bottom surface of the hanging beam 200 is a planar structure 207.
Specifically, the bottom surface of the hanging beam 200 is configured to be a plane structure 207 to avoid other connectors inside the drop tank case 100 and protect the other connectors inside the drop tank case 100.
In one embodiment of the invention, as shown in fig. 7, the planar structure 207 is provided with reinforcing blocks 208, and the reinforcing blocks 208 are connected to the planar structure 207 by means of locking members.
Specifically, the number of the reinforcing blocks 208 is four, and the inner ends of the four reinforcing blocks 208 enclose a circular through hole structure to reinforce the four corners of the hanging beam 200. And the four reinforcing blocks 208 are all provided with threaded through holes, the plane structure 207 of the hanging beam 200 is provided with threaded blind holes, the locking members adopt screws, and the screws are used for connecting the reinforcing blocks 208 to the plane structure 207 so as to connect the reinforcing blocks 208 to the bottom of the hanging beam 200.
In one embodiment of the present invention, the suspension beam 200 has a hollow structure inside.
Specifically, the suspension beam 200 has a hollow structure, which greatly reduces the weight of the entire suspension beam 200, thereby reducing the weight of the secondary fuel tank case 100.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. The utility model provides an aircraft bellytank lug beam structure which characterized in that: the auxiliary oil tank comprises an auxiliary oil tank shell (100), a hanging beam (200) and a hanging ring piece (300);
the auxiliary oil tank shell (100) is made of composite materials;
a first mounting hole (101) is formed in the side face of the auxiliary oil tank shell (100), and the first mounting hole (101) is in a stepped shape with the wide inner part and the narrow outer part; the hanging beam (200) is made of metal materials, and the hanging beam (200) is clamped at the first mounting hole (101);
the hanging beam (200) is provided with a connecting hole (201), one end of the hanging ring piece (300) is connected into the connecting hole (201), and the other end of the hanging ring piece (300) is used for being connected with the lower position of the machine body.
2. An aircraft drop tank shackle beam structure as defined in claim 1, wherein: the connecting hole (201) is terminated inside the hanging beam (200).
3. An aircraft drop tank shackle beam structure as defined in claim 2, wherein: the top surface of the hanging beam (200) is an arc-shaped structural surface (202) which is convex outwards and is matched with the inner wall of the auxiliary fuel tank shell (100).
4. An aircraft drop tank shackle beam structure as defined in claim 3, wherein: and an arc-shaped mounting surface (203) is arranged on the arc-shaped structure surface (202).
5. An aircraft drop tank shackle beam structure as defined in claim 4, wherein: a connecting column (204) is arranged on the arc-shaped mounting surface (203), the connecting column (204) protrudes out of the arc-shaped mounting surface (203), and the connecting column (204) is clamped at the first mounting hole (101);
the connecting hole (201) is arranged in the connecting column (204).
6. An aircraft drop tank shackle beam structure as defined in claim 5, wherein: the arc-shaped mounting surface (203) is provided with a plurality of second mounting holes (205), and the number of the second mounting holes (205) is a plurality of uniformly distributed mounting holes.
7. An aircraft drop tank shackle beam structure as defined in claim 6, wherein: the side surface of the hanging beam (200) is provided with a plurality of lightening holes (206), and the number of the lightening holes (206) is a plurality of that are uniformly distributed.
8. An aircraft drop tank shackle beam structure as defined in claim 7, wherein: the bottom surface of the hanging beam (200) is of a plane structure (207).
9. An aircraft drop tank shackle beam structure as defined in claim 8, wherein: the planar structure (207) is provided with a reinforcing block (208), and the reinforcing block (208) is connected with the planar structure (207) through a locking piece.
10. An aircraft drop tank shackle beam structure as defined in claim 9, wherein: the interior of the hanging beam (200) is of a hollow structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110869486.2A CN113415430A (en) | 2021-07-30 | 2021-07-30 | Lug beam structure of auxiliary fuel tank of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110869486.2A CN113415430A (en) | 2021-07-30 | 2021-07-30 | Lug beam structure of auxiliary fuel tank of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113415430A true CN113415430A (en) | 2021-09-21 |
Family
ID=77718549
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110869486.2A Pending CN113415430A (en) | 2021-07-30 | 2021-07-30 | Lug beam structure of auxiliary fuel tank of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113415430A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB788235A (en) * | 1955-05-13 | 1957-12-23 | Gloster Aircraft Company Ltd | Improvements in aircraft fuel tanks |
| US20160052638A1 (en) * | 2013-03-26 | 2016-02-25 | Mitsubishi Heavy Industries, Ltd. | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body |
| CN207045760U (en) * | 2017-03-30 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of anti-bird hits auxiliary fuel tank |
| CN209410348U (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 pedestal |
| CN111731493A (en) * | 2020-06-18 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Light diffusion structure of aircraft fuel tank hoisting position |
| CN212386707U (en) * | 2020-04-28 | 2021-01-22 | 成都凯天电子股份有限公司 | Aviation bellytank cable suspension device |
| CN112478182A (en) * | 2020-11-10 | 2021-03-12 | 合肥江航飞机装备股份有限公司 | All-composite light fuel tank shell for aircraft |
-
2021
- 2021-07-30 CN CN202110869486.2A patent/CN113415430A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB788235A (en) * | 1955-05-13 | 1957-12-23 | Gloster Aircraft Company Ltd | Improvements in aircraft fuel tanks |
| US20160052638A1 (en) * | 2013-03-26 | 2016-02-25 | Mitsubishi Heavy Industries, Ltd. | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body |
| CN207045760U (en) * | 2017-03-30 | 2018-02-27 | 中国航空工业集团公司西安飞机设计研究所 | A kind of anti-bird hits auxiliary fuel tank |
| CN209410348U (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 pedestal |
| CN212386707U (en) * | 2020-04-28 | 2021-01-22 | 成都凯天电子股份有限公司 | Aviation bellytank cable suspension device |
| CN111731493A (en) * | 2020-06-18 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Light diffusion structure of aircraft fuel tank hoisting position |
| CN112478182A (en) * | 2020-11-10 | 2021-03-12 | 合肥江航飞机装备股份有限公司 | All-composite light fuel tank shell for aircraft |
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Application publication date: 20210921 |
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