CN113415432A - Plane auxiliary fuel tank stabilizing surface structure - Google Patents
Plane auxiliary fuel tank stabilizing surface structure Download PDFInfo
- Publication number
- CN113415432A CN113415432A CN202110869488.1A CN202110869488A CN113415432A CN 113415432 A CN113415432 A CN 113415432A CN 202110869488 A CN202110869488 A CN 202110869488A CN 113415432 A CN113415432 A CN 113415432A
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- Prior art keywords
- support
- stabilizing
- shell
- piece
- clamping plate
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- 230000000087 stabilizing effect Effects 0.000 title claims abstract description 74
- 239000002828 fuel tank Substances 0.000 title abstract description 25
- 239000007769 metal material Substances 0.000 claims abstract description 11
- 239000002131 composite material Substances 0.000 claims abstract description 10
- 239000003381 stabilizer Substances 0.000 claims description 26
- 239000010410 layer Substances 0.000 claims description 4
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 239000012945 sealing adhesive Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 description 7
- 239000002184 metal Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 238000004519 manufacturing process Methods 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
- 238000002360 preparation method Methods 0.000 description 1
- 239000000565 sealant Substances 0.000 description 1
- 238000005728 strengthening Methods 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
- B64D37/06—Constructional adaptations thereof
-
- 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
Landscapes
- 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 stabilizing surface structure of an aircraft auxiliary fuel tank, which comprises an auxiliary fuel tank shell, a stabilizing surface and a fastener, wherein the stabilizing surface is arranged on the shell; the auxiliary oil tank shell and the stabilizing surface are both made of composite materials; the fastener is made of metal materials, one end of the fastener penetrates through the inner side of the tail shell of the auxiliary oil tank shell and is connected with the inner side of the auxiliary oil tank shell, and the other end of the fastener is connected with the inner side of the stabilizing surface. The number of the stabilizing surfaces is two, and the two stabilizing surfaces are respectively connected to two opposite sides of the tail shell. The auxiliary oil tank shell is made of composite materials, so that the overall weight is reduced, and the impact resistance is strong; the stabilizing surface is made of composite materials, and the fastening piece is made of metal materials, so that the stabilizing surface can be firmly connected to the tail shell of the auxiliary oil tank shell, and the connecting position is firm.
Description
Technical Field
The invention belongs to the technical field of tail structures of aircraft auxiliary fuel tanks, and particularly relates to a stabilizing surface 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. The left side and the right side of the tail shell of the auxiliary oil tank shell are respectively welded with a stabilizing surface, and the stabilizing surfaces are made of metal materials, so that the auxiliary oil tank shell and the stabilizing surfaces are made of the same materials, and the stability of the tail position of the auxiliary oil tank shell after welding is ensured.
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 two stabilizing surfaces are connected at the tail position of the auxiliary oil tank shell in a welding mode, and the connecting position of the stabilizing surfaces is easy to cause instability during use.
Disclosure of Invention
In view of the above, the invention aims to provide a stabilizing surface structure of an aircraft auxiliary fuel tank, so as to solve the problems that in the prior art, the weight is heavy and the impact resistance is poor because an auxiliary fuel tank shell is made of a metal material; the tail stabilizing surface of the auxiliary oil tank shell is fixed in a welding mode, and the technical problem of instability is easily caused during use.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
an aircraft auxiliary fuel tank stabilizing surface structure comprises an auxiliary fuel tank shell, a stabilizing surface and a fastener;
the auxiliary oil tank shell and the stabilizing surface are both made of composite materials;
the fastener is made of metal materials, one end of the fastener penetrates through the inner side of the tail shell of the auxiliary oil tank shell and is connected with the inner side of the auxiliary oil tank shell, and the other end of the fastener is connected with the inner side of the stabilizing surface.
The number of the stabilizing surfaces is two, and the two stabilizing surfaces are respectively connected to two opposite sides of the tail shell.
Furthermore, the connection surface of the fixing surface and the tail shell which are attached to each other is coated with a sealing adhesive layer.
Furthermore, the thickness of the supporting surface at the middle position of the stabilizing surface is greater than that of the slope surface at the outer side position of the stabilizing surface.
Further, the slope surface is an inclined slope surface with the inner side thickness larger than the outer side thickness.
Furthermore, the front end surface of the stabilizing surface is provided with an inclined surface structure with a narrow inner part and a wide outer part;
the outer side surface of the stabilizing surface is parallel to the outer side surface of the auxiliary oil tank shell.
Furthermore, the stabilizing surface is of a hollow shell structure.
Further, the fastener comprises a first supporting piece, a second supporting piece and a clamping piece;
the first supporting piece, the tail shell and one side of the clamping piece are connected through a first connecting piece;
the structure of the second support is the same as that of the first support; the second supporting piece, the tail shell and the other side of the clamping piece are connected through a second connecting piece; the second supporting piece is connected with the first supporting piece through a third connecting piece; (ii) a
The outer side surface of the clamping piece is connected with the inner side of the stabilizing surface through a fourth connecting piece.
Furthermore, the outer side of the first supporting piece is provided with an arc-shaped surface structure matched with the inner side surface of the tail shell;
the inner side surface of the first supporting piece is provided with a triangular supporting structure arranged transversely.
Further, the clamping piece comprises an arc-shaped supporting plate, a first clamping and connecting plate and a second clamping and connecting plate;
the inner side surface of the arc-shaped supporting plate is connected with the first supporting piece and the second supporting piece; the upper part of the outer side of the arc-shaped supporting plate is connected with a first clamping and connecting plate, the lower part of the outer side of the arc-shaped supporting plate is connected with a second clamping and connecting plate, and the first clamping and connecting plate and the second clamping and connecting plate have the same structure;
the inner side of the stabilizing surface is embedded into the accommodating cavity between the first clamping plate and the second clamping plate and is connected with the first clamping plate and the second clamping plate through a fifth connecting piece.
Furthermore, the outside of first joint board is equipped with the strengthening rib.
Compared with the prior art, the stabilizing surface structure of the aircraft auxiliary fuel tank 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; the stabilizing surface is also made of composite materials, so that the overall weight is reduced; the fastener is made of metal materials, so that the firmness of connection between the tail shell of the auxiliary oil tank shell and the stabilizing surface is ensured; one end of the fastener penetrates through the tail shell and is connected to the inner side of the tail shell, and the other end of the fastener is connected to the inner side of the stabilizing surface, so that the connection stability between the tail shell and the stabilizing surface is ensured; the number of the stabilizing surfaces is two, and the balance of the tail shell is good.
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 view of a landing surface structure of an aircraft drop tank in an embodiment of the invention;
FIG. 2 is a schematic structural diagram of a stabilizer in an embodiment of the present invention;
FIG. 3 is a top view of a stabilizer in an embodiment of the present invention;
FIG. 4 is a left side view of a stabilizer in an embodiment of the present invention;
FIG. 5 is a schematic view of the outer side of a stabilizer fastener in an embodiment of the invention;
FIG. 6 is a schematic view of the inner side of a fastener of the stabilizer in an embodiment of the invention.
Description of reference numerals:
100-a secondary tank housing; 200-a stabilizer;
300-a fastener; 101-a tail housing;
201-connecting surface; 202-a support surface;
203-slope surface; 204-bevel structure;
301-a first support; 302-a second support;
303-a clip; 304-an arcuate face structure;
305-a triangular support structure; 306-an arc-shaped support plate;
307-a first clamping plate; 308-a second clamping plate;
309-an accommodating cavity; 310-reinforcing ribs.
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 6, the invention provides an aircraft drop tank stabilizing surface structure, which comprises a drop tank shell 100, a stabilizing surface 200 and a fastener 300;
the auxiliary oil tank shell 100 and the stabilizing surface 200 are both made of composite materials;
the fastener 300 is made of metal material, one end of the fastener 300 penetrates through the inside of the tail shell 101 of the auxiliary fuel tank shell 100 and is connected with the auxiliary fuel tank shell 100, and the other end of the fastener 300 is connected with the inside of the stabilizing surface 200.
The number of the stabilizing surfaces 200 is two, and the two stabilizing surfaces 200 are respectively connected to two opposite sides of the tail housing 101.
Specifically, referring to fig. 1, the secondary fuel tank shell 100 and the stabilizing surface 200 are both made of composite materials, the composite materials reduce 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, the stabilizing surface 200 all adopt combined material to make, fastener 300 adopts the material preparation of metal, when being connected through fastener 300 between bellytank casing 100 and the stabilizing surface 200, 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.
After the inner end of the fastener 300 is inserted into the drop tank case 100, the inner end of the tail case 101 is connected by a bolt, and the outer end of the fastener 300 is connected by a bolt to the inner side of the stabilizing surface 200, so that the stabilizing surface 200 is attached to the outer side of the tail case 101, and the tail case 101 and the stabilizing surface 200 are fixed by the fastener 300. And the inner end of the fastener 300 is disposed at an inner position of the tail housing 101 without affecting the outer structure of the secondary fuel tank housing 100. The outside end of fastener 300 is direct connection the inboard of stabilizer 200, combines together fixedly between metal and the combined material, and the hookup location is firm, and the hookup location leakproofness is good.
In one embodiment of the present invention, as shown in fig. 1, 2 and 3, a connection surface 201 of the stabilizing surface 200 and the tail housing 101 is coated with a sealant layer.
Specifically, the connecting surface 201 on the inner side of the stabilizing surface 200 is coated with a sealing adhesive layer, so that the attaching position between the inner side of the stabilizing surface 200 and the outer side surface of the tail shell 101 is firm, the pneumatic stress load is optimized, and the structural strength of the stabilizing surface 200 is enhanced.
In one embodiment of the present invention, as shown in fig. 1, 2 and 3, the thickness of the support surface 202 at the middle position of the stabilizer 200 is greater than the thickness of the slope surface 203 at the outer position of the stabilizer 200.
In the prior art, the structure of the stabilizer is as follows: the thickness of each position of the plate-shaped structure is uniform. When the aircraft is used, although the stress of each position of the plate-shaped structure is balanced, the stress balance of the middle position is not ensured, and the stability during flight is influenced.
In the embodiment of the present invention, the thickness of the middle position of the stabilizing surface 200 is thicker, and the thickness of the outer position is thinner, so as to ensure the stress load of the middle position of the whole stabilizing surface 200.
In one embodiment of the present invention, as shown in fig. 1, 2 and 3, the slope 203 is an inclined slope having a greater inside thickness than outside thickness.
Specifically, by adopting the slope structure, the stress on the outer side of the slope surface 203 is smaller than the stress on the inner side, and the stress load on the inner side of the slope surface 203 is ensured.
In one embodiment of the present invention, as shown in fig. 1, 2 and 3, the front end surface of the stabilizer 200 has a bevel structure 204 with a narrow inside and a wide outside;
the outer side surface of the stabilizing surface 200 is arranged in parallel with the outer side surface of the secondary fuel tank case 100.
Specifically, the front end surface of the stabilizer 200 is provided with the inclined surface structure 204, so that the front end of the stabilizer 200 is narrower, and the rear end of the stabilizer is wider, thereby facilitating to maintain the balance of the whole stabilizer 200.
The outer side surface of the stabilizing surface 200 is parallel to the outer side surface of the auxiliary fuel tank casing 100, so that the whole auxiliary fuel tank casing 100 can stably operate
In one embodiment of the present invention, as shown in fig. 3 and 4, the stabilizer 200 is a hollow shell structure.
Specifically, the stabilizing surface 200 is a hollow structure, which reduces the weight.
In one embodiment of the present invention, as shown in fig. 1, 5, 6, the fastener 300 comprises a first support member 301, a second support member 302, and a clamping member 303;
one sides of the first supporting piece 301, the tail shell 101 and the clamping piece 303 are connected through a first connecting piece;
the structure of the second support 302 is the same as that of the first support 301; the other sides of the second supporting piece 302, the tail shell 101 and the clamping piece 303 are connected through a second connecting piece; the second support member 302 is connected with the first support member 301 through a third connecting member; (ii) a
The outer side of the clamping member 303 is connected to the inner side of the stabilizing surface 200 by a fourth connecting member.
Specifically, the first support member 301, the second support member 302 are the same in structure, and are arranged relatively along the inner side of the clamping member 303, and the first support member 301 comprises an outer arc support plate, an inner arc connecting plate, and after the arc support plate is connected with the arc connecting plate, three triangular plates transversely arranged from top to bottom are connected and fixed. The first connecting piece, the second connecting piece, the third connecting piece and the fourth connecting piece are all of bolt and nut structures.
The side of afterbody casing 101 sets up first screw hole, sets up the second screw hole in first support piece 301's the arc backup pad, and chucking spare 303 left side sets up the third screw hole, adopts the bolt to wear to establish third screw hole, first screw hole in proper order, connects in the second screw hole, makes first support piece 301 connect at chucking spare 303's inboard left side position, fixes first support piece 301 at the lateral surface of afterbody casing 101. Similarly, the side of the tail housing 101 is provided with a first threaded hole, the arc-shaped support plate of the second support member 302 is provided with a fourth threaded hole, the right side of the clamping member 303 is provided with a third threaded hole, the bolt is adopted to sequentially penetrate through the third threaded hole and the first threaded hole, and the second support member 302 is connected in the fourth threaded hole, so that the second support member 302 is connected at the right side of the inner side of the clamping member 303, and the second support member 302 is fixed on the outer side surface of the tail housing 101.
The arc-shaped connecting plate on the inner side of the second support 302 and the arc-shaped connecting plate on the inner side of the first support 301 are fixed through bolts and nuts.
The outer side surface of the clamping piece 303 and the inner side of the stabilizing surface 200 are fixed by bolts.
In one embodiment of the present invention, as shown in fig. 1, 5 and 6, the outer side of the first support 301 has an arc-shaped surface structure 304 adapted to the inner side surface of the tail casing 101;
the inner side of the first support 301 has a laterally arranged triangular support structure 305.
Specifically, since the tail housing 101 is an arc-shaped structure, the arc-shaped surface structure 304 is the arc-shaped support plate, and the radian of the arc-shaped surface structure 304 is consistent with that of the tail housing 101, so that the stability of the attachment between the first support member 301 and the tail housing 101 can be ensured.
The triangular support structure 305 is the triangular plate, and three triangular plates transversely arranged are sequentially connected between the arc support plate and the arc connecting plate along the vertical direction, so as to support and fix the arc support plate and the arc connecting plate, thereby ensuring the support force when the first support member 301 is connected. Similarly, the second support 302 has the same structure as the first support 301.
In one embodiment of the present invention, as shown in fig. 1, 5, and 6, the clamping member 303 includes an arc-shaped support plate 306, a first clamping plate 307, and a second clamping plate 308;
the inner side surface of the arc-shaped support plate 306 is connected with the first support piece 301 and the second support piece 302; the upper part of the outer side of the arc-shaped supporting plate 306 is connected with a first clamping and connecting plate 307, the lower part of the outer side of the arc-shaped supporting plate 306 is connected with a second clamping and connecting plate 308, and the first clamping and connecting plate 307 and the second clamping and connecting plate 308 have the same structure;
the inner side of the fixing surface 200 is embedded in the accommodating cavity 309 between the first clamping plate 307 and the second clamping plate 308, and is connected with the first clamping plate 307 and the second clamping plate 308 through a fifth connecting piece.
Specifically, the arc support plate 306 of the chucking member 303 has the same structure as that of the above-described first support member 301, so that the tail housing 101 is accommodated between the two arc support plates. A plurality of threaded holes are provided in the arc support plate 306 of the retainer 303 so that bolts can pass through the threaded holes in the arc support plate 306 of the retainer 303, the threaded holes in the tail housing 101, and the threaded holes in the arc support plate of the first support 301 to fix the tail housing 101 between the two arc support plates.
The first clamping plate 307 and the second clamping plate 308 are both transversely arranged trapezoidal plates with wide inside and narrow outside, and the two trapezoidal plates are transversely arranged to connect the outer sides of the arc-shaped support plates 306. And all set up the screw hole on two trapezoidal boards, the fifth connecting piece adopts bolt and nut, forms between two trapezoidal boards and holds chamber 309 to the inboard embedding of ann's level 200 is in should holding chamber 309, then adopts the screw hole on two joint boards of bolted connection, fixes the position of ann's level 200.
The first clamping plate 307 and the second clamping plate 308 are both trapezoidal plates with wide inner parts and narrow outer parts, so that the supporting force of the inner side positions of the two clamping plates is increased, the width of the outer side positions is narrow, and the material is saved.
In one embodiment of the present invention, as shown in fig. 1, 5 and 6, a reinforcing rib 310 is provided on the outer side of the first engaging plate 307.
Specifically, the reinforcing rib 310 is a triangular plate in the vertical direction provided on the upper end surface of the first engaging plate 307, and the supporting force of the first engaging plate 307 can be increased by the triangular plate. Similarly, a triangular plate is also provided on the lower end surface of the second engaging plate 308 in the vertical direction, and the supporting force of the second engaging plate 308 can be increased by using the triangular plate.
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 stabilizer structure which characterized in that: comprises a secondary oil tank shell (100), a stabilizing surface (200) and a fastener (300);
the auxiliary oil tank shell (100) and the stabilizing surface (200) are both made of composite materials;
the auxiliary oil tank is characterized in that the fastening piece (300) is made of a metal material, one end of the fastening piece (300) penetrates through the auxiliary oil tank shell (100) to be connected with the inner side of the tail shell (101) of the auxiliary oil tank shell (100), and the other end of the fastening piece (300) is connected with the inner side of the stabilizing surface (200).
The number of the stabilizing surfaces (200) is two, and the two stabilizing surfaces (200) are respectively connected to two opposite sides of the tail shell (101).
2. An aircraft drop tank stabilizer structure according to claim 1, characterized in that: the connection surface (201) of the stabilizing surface (200) and the tail shell (101) is coated with a sealing adhesive layer.
3. An aircraft drop tank stabilizer structure according to claim 2, characterized in that: the thickness of the supporting surface (202) in the middle of the stabilizing surface (200) is larger than that of the slope surface (203) in the outer side of the stabilizing surface (200).
4. An aircraft drop tank stabilizer structure according to claim 3, characterized in that: the slope surface (203) is an inclined slope surface with the inner side thickness larger than the outer side thickness.
5. An aircraft drop tank stabilizer structure according to claim 4, wherein: the front end face of the stabilizing face (200) is provided with a bevel structure (204) with a narrow inner part and a wide outer part;
the outer side surface of the stabilizing surface (200) is parallel to the outer side surface of the auxiliary oil tank shell (100).
6. An aircraft drop tank stabilizer structure according to claim 5, wherein: the stabilizing surface (200) is of a hollow shell structure.
7. An aircraft drop tank stabilizer structure according to claim 6, wherein: the fastener (300) comprises a first support (301), a second support (302) and a clasp (303);
one sides of the first supporting piece (301), the tail shell (101) and the clamping piece (303) are connected through a first connecting piece;
the structure of the second support (302) is the same as the structure of the first support (301); the second supporting piece (302), the tail shell (101) and the other side of the clamping piece (303) are connected through a second connecting piece; the second support (302) is connected with the first support (301) through a third connector;
the outer side face of the clamping piece (303) is connected with the inner side of the stabilizing face (200) through a fourth connecting piece.
8. An aircraft drop tank stabilizer structure according to claim 7, wherein: the outer side of the first support piece (301) is provided with an arc-shaped surface structure (304) matched with the inner side surface of the tail shell (101);
the inner side of the first support (301) has a laterally arranged triangular support structure (305).
9. An aircraft drop tank stabilizer structure according to claim 8, wherein: the clamping piece (303) comprises an arc-shaped supporting plate (306), a first clamping plate (307) and a second clamping plate (308);
the inner side surface of the arc-shaped support plate (306) is connected with the first support (301) and the second support (302); the upper part of the outer side of the arc-shaped supporting plate (306) is connected with the first clamping plate (307), the lower part of the outer side of the arc-shaped supporting plate (306) is connected with the second clamping plate (308), and the first clamping plate (307) and the second clamping plate (308) have the same structure;
the inner side of the stabilizing surface (200) is embedded in a containing cavity (309) between the first clamping plate (307) and the second clamping plate (308), and is connected with the first clamping plate (307) and the second clamping plate (308) through a fifth connecting piece.
10. An aircraft drop tank stabilizer structure according to claim 9, wherein: and a reinforcing rib (310) is arranged on the outer side of the first clamping plate (307).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110869488.1A CN113415432A (en) | 2021-07-30 | 2021-07-30 | Plane auxiliary fuel tank stabilizing surface structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110869488.1A CN113415432A (en) | 2021-07-30 | 2021-07-30 | Plane auxiliary fuel tank stabilizing surface structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113415432A true CN113415432A (en) | 2021-09-21 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110869488.1A Pending CN113415432A (en) | 2021-07-30 | 2021-07-30 | Plane auxiliary fuel tank stabilizing surface structure |
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| CN (1) | CN113415432A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113970277A (en) * | 2021-11-16 | 2022-01-25 | 天津爱思达新材料科技有限公司 | Front end rear flange reinforcing structure |
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| CN212866340U (en) * | 2020-07-06 | 2021-04-02 | 山东中预建筑科技有限公司 | Corner connecting steel part for assembly type office building |
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2021
- 2021-07-30 CN CN202110869488.1A patent/CN113415432A/en active Pending
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| WO2015170090A1 (en) * | 2014-05-07 | 2015-11-12 | Bae Systems Plc | Aircraft fuel tank |
| CN104913901A (en) * | 2015-06-23 | 2015-09-16 | 中国航空工业集团公司西安飞机设计研究所 | Airplane auxiliary fuel tank flutter model |
| CN205010864U (en) * | 2015-10-14 | 2016-02-03 | 中国人民解放军93469部队 | Foldable bellytank bracket |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113970277A (en) * | 2021-11-16 | 2022-01-25 | 天津爱思达新材料科技有限公司 | Front end rear flange reinforcing structure |
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Application publication date: 20210921 |
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| RJ01 | Rejection of invention patent application after publication |