CN107792380A - A kind of depopulated helicopter complicated shape composite integral tank structure - Google Patents
A kind of depopulated helicopter complicated shape composite integral tank structure Download PDFInfo
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- CN107792380A CN107792380A CN201711098713.6A CN201711098713A CN107792380A CN 107792380 A CN107792380 A CN 107792380A CN 201711098713 A CN201711098713 A CN 201711098713A CN 107792380 A CN107792380 A CN 107792380A
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- Prior art keywords
- oil
- fuel tank
- shirt rim
- oil box
- complicated shape
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- 239000002131 composite material Substances 0.000 title claims abstract description 35
- 239000002828 fuel tank Substances 0.000 claims abstract description 70
- 229910052802 copper Inorganic materials 0.000 claims abstract description 14
- 239000010949 copper Substances 0.000 claims abstract description 14
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 13
- 239000000945 filler Substances 0.000 claims abstract description 13
- 239000012530 fluid Substances 0.000 claims abstract description 11
- 238000005259 measurement Methods 0.000 claims abstract description 10
- 239000003921 oil Substances 0.000 claims description 81
- 239000006260 foam Substances 0.000 claims description 11
- 238000010276 construction Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 8
- 238000000034 method Methods 0.000 claims description 8
- 239000010410 layer Substances 0.000 claims description 4
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 238000004880 explosion Methods 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 239000000835 fiber Substances 0.000 claims description 3
- 239000003502 gasoline Substances 0.000 claims description 3
- 239000011229 interlayer Substances 0.000 claims description 3
- 238000011068 loading method Methods 0.000 claims description 3
- 239000000565 sealant Substances 0.000 claims description 3
- 238000006073 displacement reaction Methods 0.000 claims description 2
- 239000004519 grease Substances 0.000 claims 1
- 230000000694 effects Effects 0.000 abstract description 3
- 238000013461 design Methods 0.000 description 15
- 238000010586 diagram Methods 0.000 description 6
- 238000012546 transfer Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 4
- DOSMHBDKKKMIEF-UHFFFAOYSA-N 2-[3-(diethylamino)-6-diethylazaniumylidenexanthen-9-yl]-5-[3-[3-[4-(1-methylindol-3-yl)-2,5-dioxopyrrol-3-yl]indol-1-yl]propylsulfamoyl]benzenesulfonate Chemical compound C1=CC(=[N+](CC)CC)C=C2OC3=CC(N(CC)CC)=CC=C3C(C=3C(=CC(=CC=3)S(=O)(=O)NCCCN3C4=CC=CC=C4C(C=4C(NC(=O)C=4C=4C5=CC=CC=C5N(C)C=4)=O)=C3)S([O-])(=O)=O)=C21 DOSMHBDKKKMIEF-UHFFFAOYSA-N 0.000 description 3
- 238000007789 sealing Methods 0.000 description 3
- 239000004677 Nylon Substances 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 229920001778 nylon Polymers 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- 239000002023 wood Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000009833 condensation Methods 0.000 description 1
- 230000005494 condensation Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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
-
- 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 present invention relates to a kind of depopulated helicopter complicated shape composite integral tank structure, including fuel tank cap, oil box, copper mesh, left and right lid, oil-level measurement device and add, go out, for and return four hydraulic fluid ports, wherein oil box is divided into stage casing, side, bottom and all around four shirt rims.Fuel tank is placed under rotor, around propeller hub, and fuel tank cap and side are side skin in helicopter middle fuselage, and oil box bottom is placed on middle fuselage internal truss frame；Oil box passes through side skin and internal truss frame bolt connection under left and right shirt rim and middle fuselage, by front and rear shirt rim respectively with front and rear fuselage skin bolt connection, by bottom and go out, for, return three hydraulic fluid ports and oil-level measurement device blind hole flange bolt connection, it is glued by stage casing, side and fuel tank cap and is connected, is indirectly connected with by side and left and right lid.Fuel tank cap is glued with oil filler to be connected, and copper mesh is glued on fuel tank.The present invention has the advantages that high intensity, high rigidity, lightweight, rectification effect and the main shaft effect of protection propeller hub.
Description
Technical field
The present invention relates to a kind of depopulated helicopter complicated shape composite integral tank structure, belong to aircraft composite wood
Expect field of structural design.
Background technology
Tank design is directly connected to flight safety as the committed step among helicopter design, its superiority-inferiority.It is existing
Helicopter fuel tank mainly include metallic oil tank, plastic fuel tank, nylon or oil resistant rubber soft tank, but the structure of metallic oil tank
Weight is excessive, and plastic fuel tank sealing is poor, and nylon or oil resistant rubber soft tank are vulnerable to the influence of temperature and needed specific
Be fixedly mounted in tank bay.In addition, conventional fuel tank is mostly the separate part for being placed on fuselage interior, which increase
Unnecessary weight, fuselage interior space availability ratio is reduced, so tank design is had into a part for outer skin structure
Beneficial to lifting inner space utilization rate.But or conventional oil tank material is overweight, or intensity and toughness is too low, be not suitable for making gently
The stressed-skin construction of matter.Specific stiffness, the specific strength of composite are high, and are easy to make the complex configuration of suitable aerodynamic loading, so
The invention provides a kind of high intensity, high rigidity, lightweight complicated shape composite integral tank construction design method, purport
Reference is being provided for depopulated helicopter tank design.
The content of the invention
The technology of the present invention solves problem：Overcome the shortcomings of conventional helicopter sump, there is provided a kind of high intensity, high rigidity, light
The depopulated helicopter complicated shape composite integral tank structure of quality.
The technology of the present invention solution is：A kind of depopulated helicopter complicated shape composite integral tank structure, including
Fuel tank cap, oil box, oil filler, oil-out, oil-feed port, oil return opening, oil-level measurement device, copper mesh and left and right lid, wherein fuel tank
Body is divided into stage casing, side, bottom, preceding shirt rim, rear shirt rim, left shirt rim and right shirt rim；The fuel tank is placed under rotor, propeller hub week
Enclose, fuel tank cap and side are stressed-skin construction on the upside of helicopter middle fuselage, and oil box bottom is placed on middle fuselage internal truss frame；Institute
State side skin, fuselage interior truss bolt under the middle fuselage that oil box is gone straight up to by left and right shirt rim with nobody to be connected, by front and rear
Shirt rim with front and rear fuselage skin bolt connection, passes through bottom and oil-out, oil-feed port, oil return opening and oil-level measurement device blind hole respectively
Flange bolt connect, at bolt connection add fluid sealant, by stage casing, side and fuel tank cap be glued connect, by side with
Left and right lid is indirectly connected with, i.e., side is glued with left and right shape and connected, and left and right shape connects with left and right lid bolt again
Connect, crop the shape part away from bolt connection region to mitigate construction weight；Fuel tank cap is glued with oil filler to be connected；
Copper mesh is arranged in side, preceding shirt rim, rear shirt rim, left shirt rim, right shirt rim and fuel tank cap, is connected to be glued.
The Oiltank structure has the complex-curved profile of streamline, ensure that the aerodynamic configuration of aircraft, and fuel tank be stamped it is whole
Stream acts on, and is advantageous to reduce flight resistance.
Consider causes the elevated phenomenon of fuel tank internal pressure because gasoline is volatile at high temperature, the fuel tank internal is born
Airtight pressure within 30kPa, while passage is arranged on oil filler, cause blast to prevent fuel tank internal pressure very big
Occur so that the fuel tank can use under the high temperature conditions.
The Oiltank structure uses Woven cloth compounded material foams sandwich, ensure that the fiber lay down under large curved surface configuration
Folded precision so that fuel tank is less than 5000 μ ε in the interior screw-down structure maximum strain for bearing various operating loadings and 30kpa, and maximum becomes
Morpheme, which is moved, is less than 10mm, and significantly reduces construction weight；The stage casing of the oil box and the shape of oil box corner are excessively
Complexity, foam cutting difficulty is excessive, is existed using laminated plate structure, oil box from foamed sandwich structure to laminated plate structure
Transitional region.
The tank internal surface smears antistatic coating, to prevent that electrostatic induced current is excessive caused by internal oil drag and goes out
The existing generation for burning even explosion phenomenon.
Shirt rim curvature and area are all larger after described, but stand under load is less, in order to keep its rigidity and mitigate weight, by rear skirt
While being designed as 4 layers of laminate structures, while foam pressure stalk is designed in the vertical, in bolt hole bottom, regional area thickens.
Using composite vacuum bag assistant formation technique, fuel tank cap and oil box are fabricated separately, oil box integral into
Type technique causes its laying direction to need unified planning to facilitate actual laying, i.e. composite first surrounds side, preceding shirt rim, rear skirt
Side, left shirt rim and right shirt rim, return to be paved into bottom at shirt rim, then side is taped against from bottom.
The interlayer of composite laminated plate on the inside of fuel tank cap and oil box arranges anti-oil film, to ensure to strengthen composite wood
The oil preventing performance of material.
The present invention compared with prior art the advantages of be：
(1) present invention has the advantages of high intensity, high rigidity, lightweight.The high intensity of the present invention can bear 30kpa's
Internal pressure, high rigidity ensure that deformation displacement is less than 10mm under various operating modes, especially 30kpa, and high intensity, high rigidity pass through foam
Sandwich realizes that lightweight is passed through foamed sandwich structure and realized using the covering on the upside of middle fuselage.
(2) fuel tank is separate part in the past, is placed on fuselage interior, which increase unnecessary weight, reduces space
Utilization rate.It is the one of helicopter skining structure and Oiltank structure of the present invention is placed under the rotor of depopulated helicopter, around propeller hub
Part, avoid the unnecessary weight of inner tank so that helicopter inner space is easily arranged, space availability ratio is high.
(3) the special placement location of the fuel tank causes it to have protection to propeller hub main shaft so that the oil in fuel tank is advantageous to increase
Add the rigidity of structure, at the same at left and right sides of fuel tank arrangement lid, be easy to the inspection and maintenance of lifting airscrew propeller hub main shaft, and with
Fuselage interior is placed on toward fuel tank, without this advantage；
(4) Oiltank structure has complex-curved profile, ensure that the aerodynamic configuration of aircraft, and fuel tank is stamped rectification work
With, be advantageous to reduce flight resistance, and fuel tank was placed on fuselage interior in the past, without this advantage；
(5) two Path of Force Transfer are devised between the fuel tank and depopulated helicopter middle fuselage, i.e., bottom, which is placed on, wraps up in rubber blanket
Middle fuselage internal truss frame on and left and right shirt rim and middle fuselage internal truss frame bolt connection, this more Path of Force Transfer ensure fuel tank knots
The safety of structure, bolted quantity is decreased, it is easy to disassemble.And fuel tank and airframe structure part are mostly a kind of power transmission road in the past
Footpath, the i.e. bolt connection similar to shirt rim, and this bonding strength is stronger, is not easy to dismantle, fail-safety is poorer than the fuel tank.
Brief description of the drawings
Fig. 1 is composite integral tank structural representation provided in an embodiment of the present invention；
Fig. 2 is composite integral tank structure schematic top plan view provided in an embodiment of the present invention；
Fig. 3 is composite integral tank structure schematic side view provided in an embodiment of the present invention, wherein (a) is in Fig. 2
The diagrammatic cross-section of Section A-A, (b) are the zoomed-in view at B in (a), and (c) is the zoomed-in view at C, multiplication factor in (a)
It is 10 times；
Fig. 4 is copper mesh schematic diagram provided in an embodiment of the present invention；
Fig. 5 is shape schematic diagram provided in an embodiment of the present invention；
Fig. 6 is that oil filler provided in an embodiment of the present invention is glued connection diagram with fuel tank cap；
Fig. 7 is oil-out provided in an embodiment of the present invention, oil-feed port, oil return opening and tank bottoms blind hole flange bolt connection
Schematic diagram；Wherein (a) is the bolted overall schematic of this blind hole flange, and (b) is the method for hydraulic fluid port, oil-feed port and oil return opening
Blue schematic diagram, (c) are the bolted sectional view of this blind hole flange, and (d) is that the pad of hydraulic fluid port, oil-feed port and oil return opening is illustrated
Figure；
Fig. 8 is the rear shirt rim schematic diagram of composite integral tank structure provided in an embodiment of the present invention.
Wherein, shirt rim after 1-, 2- fuel tank cap, 3- oil fillers, 4- copper mesh, the left shapes of 5-, 6- stage casings, the preceding shirt rims of 7-,
The right lids of 8-, the right shirt rims of 9-, 10- sides, 11- bottoms, 12- oil-feed ports, 13- oil return openings, 14- oil-outs, 15- oil-level measurements
Device, the left shirt rims of 16-, the left lids of 17-, the right shapes of 18-, the passage of 19- oil fillers, 20- hydraulic fluid ports, oil-feed port and oil return opening
Flange, the pad of 21- hydraulic fluid ports, oil-feed port and oil return opening, the foam pressure stalk of shirt rim after 22-, the office after 23- at the nail of shirt rim
Portion strengthens.
Embodiment
As shown in Figure 1, 2, 3, a kind of depopulated helicopter complicated shape composite integral tank structure of the present invention, including oil
Case lid 2, oil box, oil filler 3, oil-out 14, oil-feed port 12, oil return opening 13, oil-level measurement device 15, copper mesh 4, left shape
5th, the part such as right shape 18, left lid 17, right lid 8.The part although oil box is formed in one, it is excessively complicated,
Stage casing 6, side 10, bottom 11, preceding shirt rim 7, rear shirt rim 1, left shirt rim 16, the part of right shirt rim 9 seven are classified as, is easy to analyze
And explanation.Fuel tank cap is to be glued connection with three oil box, oil filler and copper mesh parts；Oil box and oil-out, oil-feed port,
Four parts of oil return opening and oil-level measurement device are blind hole flange bolt connection, are with copper mesh and the base part of left and right shape two
It is glued connection, is bolt connection with middle fuselage interior metal truss；Left and right shape is glued with left and right lid respectively to be connected.
In design structure and material selection, fuel tank mainly uses Woven cloth compounded material foams sandwich, is meeting
In the case of strength and stiffness, significantly reduce construction weight and ensure that the fiber laying precision under large curved surface configuration.Due to
The shape of stage casing 6 and oil box corner is excessively complicated, and foam cutting difficulty is excessive, so these parts are using laminated hardened
Structure, and the transitional region from foamed sandwich structure to laminated plate structure be present in oil box.
In load transfer path design, fuel tank load is mostly derived from the pressure of interior oil, two kinds of Path of Force Transfer of design with
Ensure the safety of Oiltank structure, i.e. bottom truss support and left and right shirt rim bolt connection, the former is main posting path.Bottom 11
It is placed on middle fuselage internal truss frame, truss parcel rubber blanket, downward load is buffered by the deformation of rubber blanket；Left shirt rim
16th, right shirt rim 9 and middle fuselage internal truss frame bolt connection, load when transverse direction, longitudinal direction and positive overload is primarily subjected to, by having
Limit member calculates, and left and right shirt rim, which is respectively arranged 4 uniform bolts, can meet design requirement.This more Path of Force Transfer ensure fuel tank
The safety of structure, bolted quantity is decreased, it is easy to disassemble.
In technology mode selection, using composite vacuum bag assistant formation technique, fuel tank cap and oil box are separately made
Make.The integral forming technique of oil box causes stage casing 6, side 10, bottom 11 and preceding shirt rim 7, rear shirt rim 1, left shirt rim 16, right skirt
The laying direction on side 9 needs unified planning to facilitate actual laying.Oil box is complex-curved, in order to reduce machine direction in laying
Error, using braid composite rather than unidirectional belt composite.
Structure oil-leakage-prevention design on, between the first fuel tank cap and oil box, between fuel tank cap and hydraulic fluid port it is (as shown in Figure 6) use
It is glued connection；Second oil box uses blind hole flange bolt connection (as shown in Figure 7) with hydraulic fluid port, and rubber sheet gasket is placed on oil box
Outside, failed with preventing from by oil being corroded in fuel tank, pad is raised around oil-out, coordinates with oil-out pit, to carry
Sealing property is risen, flange is arranged in fuel tank internal, and flange upper bolt hole is blind hole, is connected by bolt with each hydraulic fluid port, in bolt
Laying sealant in hole, to increase sealing, oil-level measurement device and oil box connected mode are identical with oil-out, no longer superfluous herein
State；3rd fuel tank cap and the interlayer of the composite laminated plate on the inside of oil box arrange anti-oil film, and it is non-leakage to reach fuel tank with this
Effect；
In the design of anti-electric charge accumulation, tank surface lays one layer of copper mesh (schematic configuration is as shown in Figure 4), copper mesh and fuel tank
Surface glue connects in succession, and due to conductivity of composite material difference, metallic conductivity is strong, so mainly in shirt rim bolt connection region
Copper mesh is disposed about with rotor hub, electric current is drained on middle fuselage metallic framework, it is multiple to not burnt out because of electric charge accumulation
Condensation material so that the Oiltank structure could be used that in thunderstorm weather；Tank internal surface smears antistatic coating, to prevent because of inside
The generation for burning even explosion phenomenon that electrostatic induced current caused by oil drag is excessive and occurs；
In structure air-tightness and internal pressure control design case, due to volatile under gasoline load high temperature, so fuel tank should bear one
Fixed airtight pressure, such as inside can bear 30kPa, while passage 19 is arranged on oil filler, as shown in fig. 6, to prevent
Fuel tank internal pressure is very big and causes the generation of blast so that the fuel tank could be used that at high temperature.
In propeller hub Maintainable Design, fuel tank both sides are respectively arranged lid, oil box and shape 5 or right metal mold
Material 18 be glued connection, shape again with left lid 17 or the bolt connection of right lid 8.In order to mitigate the weight of shape, cut out
Cut the part away from bolt connection region, its schematic configuration such as Fig. 5.
As shown in figure 8, be shirt rim 1 after the present invention, because rear shirt rim only serves the connection function of fuel tank and rear body, so
It is only designed as 4 layers of laminate structures.But because rear shirt rim curvature and area are all larger, in order to keep its rigidity, after longitudinal design
The foam pressure stalk 22 of shirt rim, and the local enhancement 23 under bolt hole at the nail of rear shirt rim.
Above example is provided just for the sake of the description purpose of the present invention, and is not intended to limit the scope of the present invention.This
The scope of invention is defined by the following claims.The various equivalent substitutions that do not depart from spirit and principles of the present invention and make and repair
Change, all should cover within the scope of the present invention.
Claims (8)
- A kind of 1. depopulated helicopter complicated shape composite integral tank structure, it is characterised in that：Including fuel tank cap, fuel tank Body, oil filler, oil-out, oil-feed port, oil return opening, oil-level measurement device, copper mesh and left and right lid, wherein oil box be divided into stage casing, Side, bottom, preceding shirt rim, rear shirt rim, left shirt rim and right shirt rim；The fuel tank is placed under rotor, around propeller hub, fuel tank cap and Side is stressed-skin construction on the upside of helicopter middle fuselage, and oil box bottom is placed on middle fuselage internal truss frame；The oil box leads to Side skin, fuselage interior truss bolt under the middle fuselage that left and right shirt rim is gone straight up to nobody is crossed to be connected, by front and rear shirt rim respectively with Front and rear fuselage skin bolt connection, connected by bottom and oil-out, oil-feed port, oil return opening and oil-level measurement device blind hole flange bolt Connect, fluid sealant is added at bolt connection, be glued by stage casing, side and fuel tank cap and connected, by between side and left and right lid Connect in succession, i.e., side is glued with left and right shape and connected, and left and right shape with left and right lid bolt connection, crops remote again From the shape part in bolt connection region to mitigate construction weight；Fuel tank cap is glued with oil filler to be connected；Copper mesh is arranged in In side, preceding shirt rim, rear shirt rim, left shirt rim, right shirt rim and fuel tank cap, connected to be glued.
- 2. depopulated helicopter complicated shape composite integral tank structure according to claim 1, it is characterised in that：Institute Stating Oiltank structure has the complex-curved profile of streamline, ensure that the aerodynamic configuration of aircraft, and fuel tank is stamped rectified action, favorably In reduction flight resistance.
- 3. depopulated helicopter complicated shape composite integral tank structure according to claim 1, it is characterised in that：Examine Considered causes the elevated phenomenon of fuel tank internal pressure because gasoline is volatile at high temperature, the fuel tank internal is born within 30kPa Airtight pressure, while passage is arranged on oil filler, causes the generation of blast to prevent fuel tank internal pressure very big so that The fuel tank can use under the high temperature conditions.
- 4. depopulated helicopter complicated shape composite integral tank structure according to claim 1, it is characterised in that：Institute State Oiltank structure and use Woven cloth compounded material foams sandwich, ensure that the fiber laying precision under large curved surface configuration, make Obtain fuel tank and be less than 5000 μ ε in the interior screw-down structure maximum strain for bearing various operating loadings and 30kpa, maximum distortion displacement is small In 10mm, and significantly reduce construction weight；The stage casing of the oil box and the shape of oil box corner are excessively complicated, foam It is excessive to cut difficulty, the transitional region from foamed sandwich structure to laminated plate structure be present using laminated plate structure, oil box.
- 5. depopulated helicopter complicated shape composite integral tank structure according to claim 1, it is characterised in that：Institute State tank internal surface and smear antistatic coating, what is occurred burns very to prevent the electrostatic induced current caused by internal oil drag excessive To the generation of explosion phenomenon.
- 6. depopulated helicopter complicated shape composite integral tank structure according to claim 1, it is characterised in that：Institute State rear shirt rim curvature and area is all larger, but stand under load is less, and in order to keep its rigidity and mitigate weight, rear shirt rim is designed as into 4 Layer laminate structures, while foam pressure stalk is designed in the vertical, in bolt hole bottom, regional area thickens.
- 7. depopulated helicopter complicated shape composite integral tank structure according to claim 1, it is characterised in that：Adopt With composite vacuum bag assistant formation technique, fuel tank cap and oil box are fabricated separately, and the integral forming technique of oil box causes Its laying direction needs unified planning to facilitate actual laying, i.e. composite first surrounds side, preceding shirt rim, rear shirt rim, left shirt rim With right shirt rim, return to be paved into bottom at shirt rim, then side is taped against from bottom.
- 8. depopulated helicopter complicated shape composite integral tank structure according to claim 4, it is characterised in that： Fuel tank cap and the interlayer of the composite laminated plate on the inside of oil box arrange anti-oil film, to ensure to strengthen the grease proofness of composite Energy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711098713.6A CN107792380A (en) | 2017-11-09 | 2017-11-09 | A kind of depopulated helicopter complicated shape composite integral tank structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711098713.6A CN107792380A (en) | 2017-11-09 | 2017-11-09 | A kind of depopulated helicopter complicated shape composite integral tank structure |
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| CN107792380A true CN107792380A (en) | 2018-03-13 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109204851A (en) * | 2018-09-25 | 2019-01-15 | 江苏三强复合材料有限公司 | Oiltank structure and its manufacturing method |
| CN109255203A (en) * | 2018-11-09 | 2019-01-22 | 中国直升机设计研究所 | A kind of helicopter digital prototype Fast design method and system |
| CN110435902A (en) * | 2018-05-03 | 2019-11-12 | 劳斯莱斯有限公司 | Oil tank system |
| CN112407230A (en) * | 2020-10-30 | 2021-02-26 | 中国直升机设计研究所 | Multifunctional skin structure of unmanned helicopter |
| CN113428370A (en) * | 2020-03-23 | 2021-09-24 | 海鹰航空通用装备有限责任公司 | Integral oil tank and manufacturing method thereof |
| CN113928576A (en) * | 2021-11-19 | 2022-01-14 | 中国直升机设计研究所 | Helicopter composite material lightning protection capability restoration method |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2088281A (en) * | 1980-12-03 | 1982-06-09 | Goodyear Aerospace Corp | Fabric-reinforced Composite Material for a Flexible-walled Container and Method of Making Said Container |
| US5451015A (en) * | 1993-05-18 | 1995-09-19 | Bell Helicopter Textron Inc. | Crashworthy composite aircraft structure with integral fuel tank |
| CN102365216A (en) * | 2009-03-30 | 2012-02-29 | 三菱重工业株式会社 | Composite tank, manufacturing method therefor, and wing |
| CN103213683A (en) * | 2010-03-16 | 2013-07-24 | 北京航空航天大学 | Small multipurpose unmanned plane with oil tank embedded into blended wing body |
| US20130193150A1 (en) * | 2012-01-30 | 2013-08-01 | Neal Keefer | Molded fuel tank and method of manufacturing the same |
| CN106863836A (en) * | 2016-12-27 | 2017-06-20 | 航天神舟飞行器有限公司 | Composite overall structure fuel tank and its manufacture method |
-
2017
- 2017-11-09 CN CN201711098713.6A patent/CN107792380A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2088281A (en) * | 1980-12-03 | 1982-06-09 | Goodyear Aerospace Corp | Fabric-reinforced Composite Material for a Flexible-walled Container and Method of Making Said Container |
| US5451015A (en) * | 1993-05-18 | 1995-09-19 | Bell Helicopter Textron Inc. | Crashworthy composite aircraft structure with integral fuel tank |
| CN102365216A (en) * | 2009-03-30 | 2012-02-29 | 三菱重工业株式会社 | Composite tank, manufacturing method therefor, and wing |
| CN103213683A (en) * | 2010-03-16 | 2013-07-24 | 北京航空航天大学 | Small multipurpose unmanned plane with oil tank embedded into blended wing body |
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| CN110435902A (en) * | 2018-05-03 | 2019-11-12 | 劳斯莱斯有限公司 | Oil tank system |
| CN110435902B (en) * | 2018-05-03 | 2023-04-07 | 劳斯莱斯有限公司 | Fuel tank system |
| CN109204851A (en) * | 2018-09-25 | 2019-01-15 | 江苏三强复合材料有限公司 | Oiltank structure and its manufacturing method |
| CN109255203A (en) * | 2018-11-09 | 2019-01-22 | 中国直升机设计研究所 | A kind of helicopter digital prototype Fast design method and system |
| CN113428370A (en) * | 2020-03-23 | 2021-09-24 | 海鹰航空通用装备有限责任公司 | Integral oil tank and manufacturing method thereof |
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