CN112478182A - All-composite light fuel tank shell for aircraft - Google Patents
All-composite light fuel tank shell for aircraft Download PDFInfo
- Publication number
- CN112478182A CN112478182A CN202011246639.XA CN202011246639A CN112478182A CN 112478182 A CN112478182 A CN 112478182A CN 202011246639 A CN202011246639 A CN 202011246639A CN 112478182 A CN112478182 A CN 112478182A
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- ring frame
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- shaped ring
- shell
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- 239000002828 fuel tank Substances 0.000 title claims abstract description 45
- 239000002131 composite material Substances 0.000 title claims abstract description 40
- 210000001503 joint Anatomy 0.000 claims abstract description 29
- 238000000354 decomposition reaction Methods 0.000 claims abstract description 18
- 238000007789 sealing Methods 0.000 claims abstract description 6
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 21
- 239000004917 carbon fiber Substances 0.000 claims description 21
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 21
- 230000008719 thickening Effects 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 8
- 239000000725 suspension Substances 0.000 claims description 7
- 229910052751 metal Inorganic materials 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 239000000853 adhesive Substances 0.000 claims description 4
- 230000001070 adhesive effect Effects 0.000 claims description 4
- 241000237942 Conidae Species 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims description 3
- 230000007704 transition Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 150000003839 salts Chemical class 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 229910000838 Al alloy Inorganic materials 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 238000003466 welding Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000006185 dispersion Substances 0.000 description 2
- 239000000835 fiber Substances 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000003032 molecular docking Methods 0.000 description 2
- 239000000123 paper Substances 0.000 description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 241001330002 Bambuseae Species 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 210000001015 abdomen Anatomy 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000002023 wood Substances 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; 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
-
- 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
- B64D37/04—Arrangement thereof in or on aircraft
Abstract
The invention relates to the technical field of parts of aviation and aerospace aircrafts, in particular to a light fuel tank shell made of full composite materials for an aircraft; the integral structure is divided into three large sections, which comprise a front conical section (100), a middle column section (200) and a rear conical section (300), and the concrete structure comprises a conical section shell (1), a column section shell (2), a conical section shell (3), an L-shaped ring frame a (4), an L-shaped butt joint ring frame (5), an L-shaped ring frame b (6), a small omega-shaped ring frame (7), a large omega-shaped ring frame (8), an L-shaped ring frame c (9), an L-shaped butt joint ring frame b (10), an omega-shaped ring frame (11), a U-shaped ring frame (12), a main hoisting point joint (13), a stop block (14), a rear hoisting point joint (15), a concentrated force decomposition structure (16) and an I-shaped beam decomposition joint (17); the cabin section has the advantages of easy integrated design and manufacture, high integral rigidity, light weight, simple structure, easy guarantee of the sealing characteristic of the box body, strong adaptability to salt fog and other severe environments, and the like.
Description
Technical Field
The invention relates to the technical field of parts of aviation and aerospace aircrafts, in particular to a light fuel tank shell made of all-composite materials for an aircraft.
Background
The auxiliary fuel tank is a fuel tank which is hung below the fuselage or wing of the aerospace craft, is thick in the middle and has two sharp ends in a streamline shape. The auxiliary fuel tank is hung, so that the voyage and the endurance time of the airplane can be increased, and the auxiliary fuel tank can be thrown away when the airplane is in necessary air battle, so that the airplane can be put into battle with better maneuverability.
In addition to the non-disposable fuel reservoir designed to fit the fuselage shape in the early days, the fuel reservoir has a streamlined exterior design as the main design direction, so as to reduce the generated drag, reduce the negative influence on the mobility and stability of the aircraft, and reduce the impact on other carrying equipment or fuselage structures when the fuel reservoir is separated from the aircraft. Some auxiliary fuel tanks have small fixed wings for balancing at the tail, which is useful for achieving the above-mentioned purpose.
Although most fuel tanks take a streamlined shape, some are designed with a relatively flat curve in the central portion rather than a circular arc, especially in the case of a fuel tank with a large capacity, which requires a suitable safety distance from the ground for carrying under the belly.
The materials used for the secondary fuel tank at present comprise wood, bamboo, paper fiber and aluminum alloy, and the proportion of the paper fiber, the stainless steel and the aluminum alloy used is higher after the middle period of world war. After the jet age, aluminum alloys have become a widely considered target due to the speed and the forces generated on fuel tanks during flight.
The fuel tank of the traditional airplane adopts a metal light shell welding structure, the weight of the shell of the fuel tank is heavier, the rigidity of the fuel tank is problematic, the quality of a welding seam of the metal structure is difficult to guarantee, the performance after welding is lower, and the fuel tank is not beneficial to lifting the range of the aircraft.
Disclosure of Invention
The invention aims to provide a high-rigidity fuel tank for an aviation aircraft, wherein the whole structure of the fuel tank adopts a structural scheme of carbon fiber composite skin and a ring frame, and the problems that the fuel tank in the prior art is heavy in weight, low in rigidity and performance, and influences the range of the aircraft are solved. The method can occupy a place in a wide range of light structures by a unique structural design scheme, realized special functions and application in engineering.
The technical scheme adopted by the invention is as follows:
a high-rigidity composite fuel tank for an aircraft is characterized in that a main body is made of carbon fiber composite; the overall structure is divided into three large sections, including a front conical section 100, a middle column section 200 and a rear conical section 300, and the concrete structure includes a conical section shell 1, a column section shell 2, a conical section shell 3, an L-shaped ring frame a4, an L-shaped butt joint ring frame 5, an L-shaped ring frame b6, a small omega-shaped ring frame 7, a large omega-shaped ring frame 8, an L-shaped ring frame c9, an L-shaped butt joint ring frame b10, an omega-shaped ring frame 11, a U-shaped ring frame 12, a main hoisting point joint 13, a stop block 14, a rear hoisting point joint 15, a concentrated force decomposition structure 16 and an I-beam decomposition joint 17;
the front conical section 100 and the middle column section 200 are connected in an inserting mode through an L-shaped butt joint ring frame a5, the middle column section 200 and the rear conical section 300 are connected in an inserting mode through an L-shaped butt joint ring frame b10, the whole fuel tank only has two butt joint surfaces of the L-shaped butt joint ring frame a5 and the L-shaped butt joint ring frame b10, ring frames at other positions are all arranged in the corresponding shell, the whole fuel tank is provided with two lifting point structures connected with an airplane, a main lifting point joint 13 and a rear lifting point joint 15; one on the back of the middle column section 200 and the other on the back of the rear cone section 300. Moreover, ring frame structures are arranged on two sides of each lifting point corresponding to the interior of the shell, and the ring frame structures and the respective cabin sections are integrally manufactured; the stop block 14 is arranged at the back of the rear conical section 300, and ring frame structures are arranged at two sides in the shell at the corresponding position of the stop block 14, and the ring frame structures and the rear conical section 300 are integrally manufactured; the internal structure is specifically as follows: the L-shaped ring frame a4 and the L butt joint ring frame a5 are installed in the front conical section 100 in a co-curing mode; the L-shaped ring frame b6, the small omega-shaped ring frame 7, the large omega-shaped ring frame 8 and the L-shaped ring frame c9 are arranged inside the middle column section 200 in a co-curing manner; l butt joint ring frame b10, omega-shaped ring frame 11 and U-shaped ring frame 12 are installed inside rear conical section 300 in a co-curing mode.
The front conical section 100 and the middle column section 200, and the middle column section 200 and the rear conical section 300 are connected by self-sealing bolts in the radial direction after being spliced by high-strength adhesive glue.
The front conical section 100 is of a carbon fiber composite thin-wall structure with a light shell structure, an L-shaped annular frame a4 and an L-shaped butt joint annular frame a5 are added, the whole body is integrally manufactured, the thickness of a skin is 2mm, the annular co-curing annular frames are arranged, and the materials used in the structure are all carbon fiber composite materials.
The cross section of the L-shaped ring frame a4, the L-shaped ring frame b6 and the L-shaped ring frame c9 is L-shaped.
The middle column section 200 is of a light shell structure and a carbon fiber composite thin-wall structure with a ring frame, is integrally manufactured, has a skin thickness of 2.5mm, and is annularly co-cured with the ring frame; the main hoisting point joint 13 is arranged in the shell and is provided with a thickened area, and two sides of the thickened area are annularly provided with a small omega-shaped ring frame 7 and a large omega-shaped ring frame 8.
The small omega-shaped ring frame 7 and the large omega-shaped ring frame 8 have the shape characteristic that the cross section bears a shape like a Chinese character 'ji'.
The column section shell 2 is subjected to local thickening transition treatment and is divided into an M main hoisting point thickening area and an N main hoisting point ring frame thickening area.
The concentrated force decomposition structure 16 and the I-beam decomposition joint 17 are metal parts with I-shaped sections.
The rear conical section 300 is of a carbon fiber composite thin-wall structure of a light shell structure, an omega-shaped ring frame 11 and a U-shaped ring frame 12 are arranged in the rear conical section, the rear conical section is integrally manufactured, the thickness of a skin is 2mm, the rear conical section is a circumferential co-curing circumferential frame, and the carbon fiber composite is used as the structural material.
The conical section shell 3 is of a thin-wall composite material structure, and thickened regions are arranged at the mounting positions of the stop block 14 and the rear lifting point joint 15. The stop block 14 and the rear lifting point joint 15 are both arranged on the outer side of the conical section shell 3.
The invention has the beneficial effects that:
the cabin section has the advantages of easy integrated design and manufacture, high integral rigidity, light weight, simple structure, short production period, low cost, easy guarantee of the sealing characteristic of the box body, strong manufacturability, strong adaptability to salt fog and other severe environments, and the like.
Drawings
FIG. 1 is an overall structural view of a fuel tank case
FIG. 2 is a sectional view of the overall structure of the fuel tank case I
FIG. 3 shows a plug connection between the front cone section 100 and the middle column section 200 of the fuel tank housing
FIG. 4 is a block diagram of the front cone 100 of the fuel tank shell
FIG. 5 is a typical L-shaped ring frame (4, 6, 9) configuration
FIG. 6 is a cross-sectional view of the middle column section 200
FIG. 7 is a sectional view showing the structure of the column casing 2 in the middle column 200
FIG. 8 is a view of the small omega ring 7 within the middle column section 200
FIG. 9 is a view of the large omega ring frame 8 within the middle column section 200
FIG. 10 is a block diagram of the rear cone segment 300
FIG. 11 is a block diagram of the cone housing 3 in the rear cone 300
FIG. 12 is a block diagram of the omega-ring 11 in the rear cone segment 300
FIG. 13 is a block diagram of the L docking ring frame b10 in the rear cone section 300 with the middle column section 200
In the figure, 100-front cone section, 200-middle column section, 300-rear cone section, 1-cone section shell, 2-column section shell, 3-cone section shell, 4-L-shaped ring frame a, 5-L butt joint ring frame a, 6-L-shaped ring frame b, 7-small omega-shaped ring frame, 8-large omega-shaped ring frame, 9-L-shaped ring frame c, 10-L butt joint ring frame b, 11-omega-shaped ring frame, 12-U-shaped ring frame, 13-main hoisting point joint, 14-stop block, 15-rear hoisting point joint, 16-concentrated force decomposition structure, 17-I-beam decomposition joint, M-main hoisting point thickening area, N-main hoisting point ring frame thickening area
Detailed Description
A high-rigidity composite fuel tank for an aircraft is provided, the main body of which is made of carbon fiber composite. As shown in fig. 1 and 2, the overall structure is divided into three large sections, including a front conical section 100, a middle column section 200, and a rear conical section 300, and the specific structure includes a conical section housing 1, a column section housing 2, a conical section housing 3, an L-shaped ring frame a4, an L-shaped butt ring frame 5, an L-shaped ring frame b6, a small Ω -shaped ring frame 7, a large Ω -shaped ring frame 8, an L-shaped ring frame c9, an L-shaped butt ring frame b10, an Ω -shaped ring frame 11, a U-shaped ring frame 12, a main lifting point joint 13, a stopper 14, a rear lifting point joint 15, a concentrated force decomposition structure 16, an i-beam decomposition joint 17, and other detailed structures.
As shown in fig. 3, the front cone section 100 and the middle column section 200 are connected in an insertion manner through an L-shaped docking ring frame a5, and in particular, in use, after the insertion by coating high-strength adhesive glue, the front cone section and the middle column section are radially connected by using self-sealing bolts. The middle column section 200 and the rear cone section 300 are connected in an inserting mode through the L-shaped butt joint ring frame 10, and are connected in a radial mode through self-sealing bolts after high-strength adhesive is coated and inserted in specific use. The whole fuel tank only has two butt joint surfaces of an L butt joint ring frame a5 and an L butt joint ring frame b10, and ring frames at other positions are all installed in the corresponding shell, so that the effects of enhancing the annular rigidity and improving the strength of the whole fuel tank are achieved. The entire fuel tank has two hanger point configurations (main hanger point connector 13, rear hanger point connector 15) for connection to the aircraft, one on the back of the middle column section 200 and one reverse stop 14 configuration on the back of the rear cone section 300. Moreover, ring frame structures which ensure the rigidity and the strength of the shell and the concentrated force dispersion of the lifting points are arranged on two sides of the interior of the shell corresponding to each lifting point, and the ring frame structures and the respective cabin sections are integrally manufactured; the stopper 14 is arranged at the back of the rear conical section 300, and ring frame structures which ensure the rigidity and strength of the shell and the dispersion of concentrated lifting force of lifting points are arranged at two sides in the shell at the corresponding position of the stopper 14, and the ring frame structures and the rear conical section 300 are integrally manufactured. The internal structure is specifically as follows: the L-shaped ring frame a4 and the L butt joint ring frame a5 are installed in the front conical section 100 in a co-curing mode; the L-shaped ring frame b6, the small omega-shaped ring frame 7, the large omega-shaped ring frame 8 and the L-shaped ring frame c9 are arranged inside the middle column section 200 in a co-curing manner; l butt joint ring frame b10, omega-shaped ring frame 11 and U-shaped ring frame 12 are installed inside rear conical section 300 in a co-curing mode.
As shown in fig. 4, the front cone section 100 is of a thin-walled carbon fiber composite material structure with a light shell structure, an L-shaped ring frame a4 and an L-shaped butt-joint ring frame a5 are added, the whole body is integrally manufactured, the skin thickness is 2mm, the ring direction co-curing ring frames are arranged, and the materials used in the structure are all carbon fiber composite materials. The built-in ring frame can improve the annular rigidity of the whole structure, so that the bearing capacity of the shell is improved.
The typical L-shaped ring frames are shown in FIG. 5, the cross sections of the typical L-shaped ring frames are L-shaped, each ring frame is co-cured with the cone section shell 1, the column section shell 2 and the cone section shell 3 according to corresponding positions, and carbon fiber composite materials are selected as materials.
As shown in fig. 6 and 7, the middle column section 200 is of a light shell structure and a ring frame carbon fiber composite thin-wall structure, the whole body is integrally manufactured, the thickness of the skin is 2.5mm, and the ring frame is annularly co-cured. The thickening area is arranged in the shell and is arranged at the position of the main hoisting point joint 13, the small omega-shaped ring frame 7 and the large omega-shaped ring frame 8 are arranged on the two sides of the thickening area in the circumferential direction, and the ring frame arranged in the thickening area can improve the circumferential rigidity of the whole structure, so that the bearing capacity of the shell is improved.
As shown in fig. 8 and 9, 4 channels of omega-shaped ring frames are arranged inside the column section shell 2 corresponding to the main hoisting point joint 13 of the small omega-shaped ring frame 7 and the large omega-shaped ring frame 8, and the small omega-shaped ring frame 7 and the large omega-shaped ring frame 8 have the shape characteristic of a cross section bearing a Chinese character 'ji'. As shown in fig. 7, the column casing 2 is processed by local thickening and transition, and is divided into an M main hoisting point thickening area and an N main hoisting point ring frame thickening area. The main hoisting point joint 13 is made of box-shaped metal. The small omega-shaped ring frame 7 and the large omega-shaped ring frame 8 can effectively improve the annular rigidity of the whole fuel tank, and simultaneously, the super-large concentrated force generated by hanging the airplane is transmitted to the shell through the main hoisting point joint 13, the concentrated force decomposition structure 16 and the I-beam decomposition joint 17. The concentrated force decomposition structure 16 and the I-beam decomposition joint 17 are metal parts with I-shaped sections.
As shown in fig. 4, the rear cone section 300 is of a thin-walled carbon fiber composite material structure with a light shell structure, and is internally provided with an omega-shaped ring frame 11 and a U-shaped ring frame 12, the whole body is integrally manufactured, the skin thickness is 2mm, the ring direction is co-cured to form a ring direction frame, and the materials used in the structure are all carbon fiber composite materials. The built-in ring frame can improve the annular rigidity of the whole structure, so that the bearing capacity of the shell is improved.
Referring to fig. 11, the cone shell 3 is a thin-walled composite material structure, and thickened regions are arranged at the installation positions of the stop block 14 and the rear suspension point joint 15. The stop block 14 and the rear suspension point joint 15 are both mounted on the outer side 3 of the cone section housing, and the stop block 14 and the rear suspension point joint 15 are not important to the invention and will not be described in detail.
The structure of the omega-shaped ring frame 11 in the rear cone section 300 is shown in fig. 12, and the characteristic is that the section of the ring frame is in a shape of a Chinese character 'ji'. The U-shaped ring frame 12 is characterized in that the section of the ring frame is U-shaped, and the materials are all made of carbon fiber composite materials. The omega-shaped ring frame 11 and the U-shaped ring frame 12 can effectively improve the annular rigidity of the whole structure of the conical section shell 3, and meanwhile, concentrated force generated by hanging and throwing the rear end point of the airplane can be transmitted to the shell, so that reliable connection of the fuel tanks is guaranteed.
Claims (10)
1. A high-rigidity composite fuel tank for an aircraft is characterized in that a main body is made of carbon fiber composite; the integral structure is divided into three large sections, which comprise a front conical section (100), a middle column section (200) and a rear conical section (300), and the concrete structure comprises a conical section shell (1), a column section shell (2), a conical section shell (3), an L-shaped ring frame a (4), an L-shaped butt joint ring frame (5), an L-shaped ring frame b (6), a small omega-shaped ring frame (7), a large omega-shaped ring frame (8), an L-shaped ring frame c (9), an L-shaped butt joint ring frame b (10), an omega-shaped ring frame (11), a U-shaped ring frame (12), a main hoisting point joint (13), a stop block (14), a rear hoisting point joint (15), a concentrated force decomposition structure (16) and an I-shaped beam decomposition joint (17);
the front cone section (100) is connected with the middle column section (200) through an L-shaped butt joint ring frame a (5) in an inserting mode, the middle column section (200) is connected with the rear cone section (300) through an L-shaped butt joint ring frame b (10) in an inserting mode, the whole fuel tank only has two butt joint surfaces of the L-shaped butt joint ring frame a (5) and the L-shaped butt joint ring frame b (10), ring frames at other positions are arranged in corresponding shells, the whole fuel tank is provided with two lifting point structures connected with an airplane, a main lifting point joint (13) and a rear lifting point joint (15); one lifting point is arranged at the back of the middle column section (200), and the other lifting point is arranged at the back of the rear conical section (300); moreover, ring frame structures are arranged on two sides of each lifting point corresponding to the interior of the shell, and the ring frame structures and the respective cabin sections are integrally manufactured; the stop block (14) is arranged at the back of the rear conical section (300), ring frame structures are arranged on two sides of the inner part of the shell at the position corresponding to the stop block (14), and the ring frame structures and the rear conical section (300) are integrally manufactured; the internal structure is specifically as follows: the L-shaped ring frame a (4) and the L-butt joint ring frame a (5) are arranged in the front conical section (100) in a co-curing manner; the L-shaped ring frame b (6), the small omega-shaped ring frame (7, the large omega-shaped ring frame (8) and the L-shaped ring frame c (9) are arranged inside the middle column section (200) in a co-curing mode, and the L-shaped butt joint ring frame b (10), the omega-shaped ring frame (11) and the U-shaped ring frame (12) are arranged inside the rear cone section (300) in a co-curing mode.
2. The composite fuel tank for an aircraft according to claim 1, wherein the front cone section (100) and the middle pillar section (200) and the rear cone section (300) are radially connected by self-sealing bolts after being spliced by high-strength adhesive glue.
3. The high-rigidity composite fuel tank for the aircraft according to claim 1, wherein the front cone section (100) is of a light-shell-structured thin-wall carbon fiber composite structure, an L-shaped inner ring frame a (4) and an L-shaped butt ring frame a (5) are integrally manufactured, the skin thickness is 2mm, the annular co-curing annular frames are formed, and the structural materials are carbon fiber composite materials.
4. High stiffness composite fuel tank for aircraft according to claim 1, characterized in that the L-shaped ring frames a (4), b (6), c (9) are L-shaped in cross section.
5. The composite fuel tank for aircraft according to claim 1, characterized in that the central column section (200) is of a light-shell structure plus a thin-walled carbon fiber composite structure with a ring frame, is integrally manufactured, has a skin thickness of 2.5mm, and is circumferentially co-cured with the ring frame; the main hoisting point joint (13) is arranged in the shell and is provided with a thickened area, and small omega-shaped ring frames (7) and large omega-shaped ring frames (8) are arranged on two sides of the thickened area in the circumferential direction.
6. High stiffness composite fuel tank for aircraft according to claim 1, characterized in that the small Ω -shaped rim (7), the large Ω -shaped rim (8) have a shape characteristic of a cross section bearing a "zig-zag".
7. The composite fuel tank for aircraft according to claim 1, wherein the column casing (2) is formed by local thickening and transition treatment and is divided into an M main suspension point thickening region and an N main suspension point ring frame thickening region.
8. High-rigidity composite fuel tank for aircraft according to claim 1, characterized in that the structure for concentrated force decomposition (16) and the i-beam decomposition joint (17) are metal parts having an i-shaped cross section.
9. The composite fuel tank for aircraft according to claim 1, wherein the rear cone section (300) is a thin-walled carbon fiber composite structure with a light shell structure, and is internally provided with an omega-shaped ring frame (11) and a U-shaped ring frame (12), and is integrally manufactured, wherein the skin thickness is 2mm, and the annular co-curing annular frame is made of a carbon fiber composite material.
10. A composite fuel tank with high rigidity for aircraft according to claim 1, wherein the cone shell (3) is a thin-walled composite structure, the thick region is provided at the installation position of the stop block (14) and the rear suspension point joint (15), and the stop block (14) and the rear suspension point joint (15) are both installed at the outer side of the cone shell (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011246639.XA CN112478182A (en) | 2020-11-10 | 2020-11-10 | All-composite light fuel tank shell for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011246639.XA CN112478182A (en) | 2020-11-10 | 2020-11-10 | All-composite light fuel tank shell for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112478182A true CN112478182A (en) | 2021-03-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011246639.XA Pending CN112478182A (en) | 2020-11-10 | 2020-11-10 | All-composite light fuel tank shell for aircraft |
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| CN (1) | CN112478182A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113415430A (en) * | 2021-07-30 | 2021-09-21 | 天津爱思达新材料科技有限公司 | Lug beam structure of auxiliary fuel tank of airplane |
| CN113415431A (en) * | 2021-07-30 | 2021-09-21 | 天津爱思达新材料科技有限公司 | Winding structure for auxiliary fuel tank of airplane |
| US20240092498A1 (en) * | 2022-09-15 | 2024-03-21 | Lockheed Martin Corporation | Wing tank vaporizer for solid oxide fuel cell on unmanned aircraft |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731494A (en) * | 2020-06-04 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Composite fuel tank of aircraft |
| CN111731492A (en) * | 2020-06-04 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Fuel tank of aircraft |
| 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 |
-
2020
- 2020-11-10 CN CN202011246639.XA patent/CN112478182A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731494A (en) * | 2020-06-04 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Composite fuel tank of aircraft |
| CN111731492A (en) * | 2020-06-04 | 2020-10-02 | 天津爱思达新材料科技有限公司 | Fuel tank of aircraft |
| 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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113415430A (en) * | 2021-07-30 | 2021-09-21 | 天津爱思达新材料科技有限公司 | Lug beam structure of auxiliary fuel tank of airplane |
| CN113415431A (en) * | 2021-07-30 | 2021-09-21 | 天津爱思达新材料科技有限公司 | Winding structure for auxiliary fuel tank of airplane |
| CN113415431B (en) * | 2021-07-30 | 2023-12-29 | 天津爱思达新材料科技有限公司 | Ring winding structure of auxiliary fuel tank of airplane |
| US20240092498A1 (en) * | 2022-09-15 | 2024-03-21 | Lockheed Martin Corporation | Wing tank vaporizer for solid oxide fuel cell on unmanned aircraft |
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