CN104369857A - Whole oil tank structure of airplane - Google Patents
Whole oil tank structure of airplane Download PDFInfo
- Publication number
- CN104369857A CN104369857A CN201410546198.3A CN201410546198A CN104369857A CN 104369857 A CN104369857 A CN 104369857A CN 201410546198 A CN201410546198 A CN 201410546198A CN 104369857 A CN104369857 A CN 104369857A
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- fuel tank
- tank inner
- inner bag
- lower wall
- wing
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Abstract
A whole oil tank structure of an airplane comprises a plurality of oil tank inner containers made of composite materials, a front beam, a rear beam, an upper wall board and a lower wall board; the oil tank inner containers are arranged between the upper wall board and the lower wall board; the front beam and the rear beam are connected with the front edges and rear edges of the upper wall board and the lower wall board respectively; adjacent walls among the oil tank inner containers are bonded to structural ribs of a wing; the oil tank inner containers are sealed containers prefabricated through composite materials; and the outer walls of the oil tank inner containers are in bonding curing with the adjacent upper wall board, the lower wall board, the front beam and the rear beam.
Description
Technical field
The present invention relates to airplane design technology, the structure design of the integral wing tank of specifically composite material manufacture.
Background technology
The integral wing tank of aircraft is the device that the seal cavity utilizing wing structure to be formed stores fuel oil, and its structure is simple also can effectively utilize wing space, and reducing wing loads, is Oiltank structure form main in modern aircraft design.The enclosure space that existing integral wing tank takes full advantage of structure formation itself is sealed, and reaches and can store fuel oil, can provide again the object of airplane ascensional force, eliminate the weight of flexible bag.Modern integral tank is based on metal construction integral tank, and part aircraft integral tank uses composite material on a small quantity.Because composite material has lightweight, the high performance of intensity, good rigidity, Occupation coefficient is aboard more and more higher.Integral wing tank gordian technique is sealed storage fuel oil, and bear the pressure that fuel oil system needs, meanwhile, it is to provide again the important feature of airplane ascensional force, bears whole lift demands of aircraft flight.At present, advanced long endurance unmanned aircraft all adopts full composite material wing, high aspect ratio, short and thick fuselage design.Adopt composite wing structures to alleviate aircraft weight, short and thick fuselage holds the equipment such as a large amount of control, investigation, communication, navigation again, and fuselage interior does not almost have fuel storage space, and full composite material integral wing tank is finally inevitable design alternative.Domestic Duo Jia unit all in this project of exploitation, does not also have successfully.Trace it to its cause, one is the performance not making good use of composite material, and before directly indiscriminately imitating, integral wing tank design, adopts the method for type frame assembling, and assembly difficulty is large, not easily ensures assembly precision; Two is by integral tank method of designing in the past, main stress members ensures close, the airtight requirement of fuel tank oil, increase overall assembly precision and structural rigidity requirements, need to design special hermetically-sealed construction, manufacture requirements is high, can bear deformability little, and in aircraft flight, wing distortion is inevitable, more with existing manufacture technology of composite material difficulty.
Summary of the invention
The object of the invention is the deficiency for above-mentioned designing technique and propose a kind of new structure, design can meet aircraft utilization requirement, the full composite material integral wing tank that simultaneously can complete according to existing composite processing manufacturing capacity.
A kind of aircraft integral tank structure, it is characterized in that the multiple fuel tank inner bags containing composite material making, front-axle beam, the back rest and wainscot and lower wall panels, fuel tank inner bag is between wainscot and lower wall panels, front-axle beam and the back rest respectively connected leading edge and the trailing edge of wainscot and lower wall panels, between fuel tank inner bag, adjacent wall glueds joint into the structural ribs of wing, described fuel tank inner bag is the airtight container utilizing composite precast, and the outer wall of fuel tank inner bag respectively and adjacent wainscot, lower wall panels, front-axle beam, solidification by cement between the back rest.
Above-mentioned aircraft integral tank, has one deck elasticity packed layer respectively between fuel tank inner bag and wainscot, lower wall panels.
Above-mentioned aircraft integral tank, the strengthening rib of also useful composite precast between fuel tank inner bag.
Above-mentioned aircraft integral tank, the strength beam of also useful composite precast between fuel tank inner bag.
Above-mentioned fuel tank inner bag is woven by composite three dimensional and forms, according to each fuel tank inner bag in the position of wing and function and the fuel system taked, be provided with the installation site of necessary oil inlet, oil outlet, cross feed hole, air extractor vent and relevant apparatus thereof.Directly fit between adjacent fuel tank inner bag, form common rib or form strengthening rib.The front-axle beam of wing, the back rest, strength beam are woven by composite material or adopt mould to suppress and form, and need to arrange the fuel oil passing hole communicated with fuel tank inner bag according to fuel oil system, and the installation site of relevant apparatus.On wing, lower wall panels adopts composite material bending block, and the development along with composite technology also has better mode as trellis work plate etc.Finally, fill gap between fuel tank inner bag and upper lower wall panels with elasticity packed layer (normally sponge cushion), form the impact-proof structure of soft interlayer.Fill the gap between common rib, strengthening rib, fuel tank and each beam by composite base plate, increase the Joint strenght of total, make total form a complete stressed member.
The invention has the advantages that:
1) the fuel tank inner bag manufactured by composite material, be conducive to ensureing the close and airtight requirement of fuel tank oil, larger space is provided to wing structure selection glue, the radical function of composite material fuel tank inner bag stores fuel oil, ensure the sealing of fuel tank, seal more reliable between rib and rib, selection glue tends to the corrosion of resistance to fuel oil, can do oil resistance anticorrosion process; Structure selection glue mainly tends to high strength, can make full use of existingly to manufacture and design experience, is conducive to playing composite material maximum strength, meets Failure Analysis of Composite Materials principle, ensures fuel tank using function to greatest extent;
2) adopt formed honeycomb central layer to manufacture the upper and lower wallboard of wing and replace the long purlin riveted joint of metal in the past stressed-skin construction, upper and lower wing wallboard bending resistance, shearing resistance force request can be met, simplify upper and lower wall panel structure, more meet composite material manufacture characteristic, fuel tank lower surface can be made smooth, be conducive to reducing fuel tank excess oil, improve fuel utilization ratio.Orthogonal grid wallboard also can adopt (orthogonal grid wallboard is more suitable for large aircraft integral wing tank) as a same reason;
3) aircraft carries oily coefficient usually 30% ~ 60%, and the flight that the weight of fuel oil, gravity center shift directly affect aircraft controls safety (year oily coefficient both fuel oil accounts for the ratio of aircraft gross weight amount).The design of composite material fuel tank inner bag, is conducive to realizing fuel tank echelon design, controls aircraft fuel oil and consumes gravity center shift, ensure the sealing between fuel tank group and group.This feature to wing span more than 15 meters, the UAV Fuel system highly beneficial (because the fuel oil being distributed in wing is far away apart from the center of gravity of airplane, the integral tank of large span high aspect ratio wing must divide into groups to control) that aspect ratio is greater than 15.Support that wing increases production breakdown interface segmentation, fuel tank can be put in span scope portion long as far as possible, be conducive to improving aircraft and carry oily coefficient, and then increase aircraft radius;
4) adopt composite material fuel tank inner bag, support wing segmentation manufacture, support multispar wing structure, due to good seal between fuel tank and fuel tank, when local fuel tank is impaired, other fuel tanks are unaffected.The anti-Kill capability of overall aircraft is strong;
5) adopt composite material fuel tank inner bag, sponge soft cushioning (also can add other materials liner according to technical development) can be added between fuel tank and upper lower wall panels, the bulletproof function of flexible bag before integral tank can be made to have.The shellproof flexible bag of this similar, when small caliber bullet hits fuel tank, due to the effect of sponge soft cushioning, fuel tank can first to internal strain, then come unglued, elongation is reeled off raw silk from cocoons fracture, and shell hole can reduce gradually, after bullet passes through, shell hole can be pushed back by tank pressure by the sponge based composites taken out of, stop fuel oil outflow, thus it is not shellproof to change integral tank in the past, is afraid of the weakness of impacting.Seal between the dependence rib of fuel tanker grouping in the past and long purlin and realize, due to the reason of assembly method between rib and long purlin, can not realize sealing completely, wing wallboard simultaneously as fuel tank lower wall does not have buffer capacity, can crack after being impacted, and owing to can progressively expand by flight aerodynamic influence, and then fuel tank is made to lose the function storing fuel oil.
6) composite material fuel tank inner-tube structure is adopted to simplify manufacturing process, because composite material fuel tank inner bag has fixing shape and certain rigidity, positioning action can be played in assembling manufacturing process, namely by the upper and lower front-back of fuel tank positioning beam, upper lower wall panels respectively, simplify and glued joint assembling, avoid because structure stress part is out of shape the leakage of oil caused simultaneously.
Machine wing structure form is early finalized, and principal feature of the present invention is to utilize fuel tank inner bag, improves fuel tank integral sealing, utilizes structural strength to improve the voltage endurance of integral tank; Its principle is similar to the internal lining pipe of bike tyre or artillery cannon barrels, gives full play to material property, stressed in inner bag participation structure, reduces aircraft weight; Utilize inner bag rigidity, location is gluedd joint, and changes the process that wing in the past must be ensured by type frame assembling, adopts cementing jig assembling, more meet composite processing characteristic, save man-hour and raise the efficiency;
Below in conjunction with specific embodiment and accompanying drawing, this application is described in further detail:
Accompanying drawing explanation
Fig. 1 integral tank is illustrated in aircraft position
Fig. 2 integral tank longitudinal profile is illustrated
Fig. 3 integral tank horizontal section is illustrated
The common rib structure signal of Fig. 4
The structural representation of Fig. 5 strengthening rib
Fig. 6 is the structural representation with biserial fuel tank inner bag
The structural representation of Fig. 7 strength beam
Fig. 8 integral tank glueds joint signal
Numbering title in figure: 1 fuselage, 2 integral tanks, 3 wainscots, 4 back rest, 5 packed layers, 6 fuel tank inner bags, 7 lower wall panels, 8 strengthening ribs, 9 front-axle beams, 10 strength beams, 11 fixtures
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is described in further detail, but not as foundation the present invention being done to any restriction.
The integral tank 2 of aircraft, also referred to as wing wing box, is fixed on airframe 1.This integral tank structure, the multiple fuel tank inner bags 6, front-axle beam 9, the back rest 4 and the wainscot 3 that make containing composite material and lower wall panels 7, fuel tank inner bag 6 is between wainscot 3 and lower wall panels 7, front-axle beam 9 and the back rest 4 respectively connected leading edge and the trailing edge of wainscot 3 and lower wall panels 7, the strengthening rib 8 of also useful composite precast between fuel tank inner bag 6, described fuel tank inner bag 6 is the airtight containers utilizing composite precast, and the outer wall of fuel tank inner bag 6 respectively and adjacent wainscot 3, lower wall panels 7, front-axle beam 9, solidification by cement between the back rest 4.
Details is manufactured to the present invention set forth below in conjunction with presented hereinbefore.The present invention is a kind of design newly produced in conjunction with flexible bag and integral tank feature, therefore there is both advantages separately, adopt composite material inner bag, quite have a flexible bag, it bears fuel storage sealing function, because it has stiffness and strength, and be glued together with framing member, use support frame to ensure profile without the need to picture flexible bag, structure division load can be born as integral tank simultaneously, play the role of positioning in processing and assembling.
One deck elasticity packed layer 5 is had respectively between fuel tank inner bag and wainscot 3, lower wall panels 7.Other gaps adopt composite base plate or composite fiber to fill.
According to the task needs of structure design, diverse location wing structure rib intensity has different requirements, therefore, be designed with common rib, strengthening rib two kinds of versions, as shown in Figure 4, common rib structure is directly fitted by both sides fuel tank inner bag 6 outer wall and is formed, other are not had to strengthen structure, this cementing structure fits place if any highly not enough gap, must adopt composite base plate polishing, and the space that excessive fillet is formed should adopt fiber to fill up, in case form cavity when glueing joint, the defects such as bubble.This structure is mainly used in this place does not have outside connection request, and this place is not the structure of focal point of stress.High as local requirement of strength during wing stressed connection intersection point position, common rib structure does not just meet Structural strength calls, for this reason, must design strengthening rib.As shown in Figure 5, strengthening rib is made up of cementing strengthening rib 8 in the middle of two fuel tank inner bags 6 strengthening rib, in order to improve local strength, reaches said apparatus and installs force request.This cementing structure fits place if any the highly not enough gap produced, and must adopt composite base plate polishing, the space that excessive fillet is formed should adopt fiber to fill up, in case form cavity when glueing joint, the defects such as bubble.
According to wing general design requirement, large at wing aspect ratio, wing area is large, and whole wing relative thickness is little, and usually adopt many girder constructions, beam before, during and after employing, wherein central sill is strength beam, for increasing wing intensity.According to this structural requirement, devise triple-beam structure (many girder constructions in like manner) as shown in Figure 6, Figure 7, for many girder constructions wing.It is formed is increase strength beam 10 in the middle of front and rear beam, and fuel tank inner bag 6 is divided into front two rows and arranges, is communicated with as required, front-axle beam 9, strength beam 10, the back rest 4 should make corresponding passing hole between fuel tank, ensures fuel oil system function.
Process and assemble scheme of the present invention is as follows:
1, the processing of fuel tank inner bag 6: recommend to adopt three dimensional knitting method shaping, its step is as follows, designs stationary core rod by fuel oil system requirement design fuel tank inner bag and the perforate of each union piece end face, shaping on three-dimensional establishment equipment.According to the data published both at home and abroad, it is very complicated that three-dimensional works out shaping part, and this part manufacturing process should ensure.
2, the scheme of front-axle beam and back rest processing, recommends employing three axle weaving method shaping, also can adopt mould molding.This is general way.
3, the wainscot 3 of wing and lower wall panels 7 adopt folder honeycomb core can solve wallboard and to bear under Tension and Compression and shearing and bending combined action not unstability, honeycomb core machine-shaping can be adopted to glued joint and manufacture.
4, assembly method, locate on fixture 11 with lower wall panels 7, front-axle beam 9 and the back rest 4 and inner bag 6 are installed, can be shaping with the levelling Post RDBMS of composite wood backing strap for the gap between fuel tank inner bag and upper and lower wallboard, as shown in the figure, between fuel tank inner bag and lower wall panels, between fuel tank inner bag and wainscot, add soft foam-rubber cushion elasticity packed layer 5.
5, assembly error analysis, if whole fitting process directly splicing does not adjust, manufacturing errors be both each part error and, on height both beam, upper and lower wallboard manufacturing errors and, 1mm should be no more than by prior art level, as need assembly precision be improved, the height of contour of available adjustment composite material pad Altitude control wainscot.Profile is the same as before, and cutting precision can ensure.
Claims (4)
1. an aircraft integral tank structure, it is characterized in that the multiple fuel tank inner bags containing composite material making, front-axle beam, the back rest and wainscot and lower wall panels, fuel tank inner bag is between wainscot and lower wall panels, front-axle beam and the back rest respectively connected leading edge and the trailing edge of wainscot and lower wall panels, between fuel tank inner bag, adjacent wall glueds joint into the structural ribs of wing, described fuel tank inner bag is the airtight container utilizing composite precast, and the outer wall of fuel tank inner bag respectively and adjacent wainscot, lower wall panels, front-axle beam, solidification by cement between the back rest.
2. aircraft integral tank as claimed in claim 1, is characterized in that there is one deck elasticity packed layer respectively between fuel tank inner bag and wainscot, lower wall panels.
3. aircraft integral tank as claimed in claim 1 or 2, is characterized in that the strengthening rib of also useful composite precast between fuel tank inner bag.
4. aircraft integral tank as claimed in claim 3, is characterized in that the strength beam of also useful composite precast between fuel tank inner bag.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410546198.3A CN104369857A (en) | 2014-10-15 | 2014-10-15 | Whole oil tank structure of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410546198.3A CN104369857A (en) | 2014-10-15 | 2014-10-15 | Whole oil tank structure of airplane |
Publications (1)
| Publication Number | Publication Date |
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| CN104369857A true CN104369857A (en) | 2015-02-25 |
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Family Applications (1)
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| CN201410546198.3A Pending CN104369857A (en) | 2014-10-15 | 2014-10-15 | Whole oil tank structure of airplane |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908958A (en) * | 2015-05-28 | 2015-09-16 | 河南翱翔航空科技有限公司 | Wing fuel tank |
| CN105059555A (en) * | 2015-08-14 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Oil tank assembly oil leading devices and airplane with same |
| CN105205267A (en) * | 2015-09-24 | 2015-12-30 | 江西洪都航空工业集团有限责任公司 | Method for calculating load of wing integral fuel tank |
| CN105221748A (en) * | 2015-08-25 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of encapsulating method of aircraft integral tank |
| CN105253291A (en) * | 2015-10-14 | 2016-01-20 | 哈尔滨飞机工业集团有限责任公司 | Aerofoil integrated machine stiffened wall plate with comb-shaped connector and application |
| CN105445048A (en) * | 2015-11-24 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Test method for connection interface sealing failure of integrated fuel tank structure |
| CN105501450A (en) * | 2015-11-30 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned plane composite integral fuel tank sealing method |
| CN106585957A (en) * | 2016-12-14 | 2017-04-26 | 中航通飞研究院有限公司 | Composite wing integral oil tank and manufacturing method thereof |
| CN107244409A (en) * | 2017-05-31 | 2017-10-13 | 彩虹无人机科技有限公司 | A kind of composite wing integral tank structure |
| CN109305328A (en) * | 2018-11-12 | 2019-02-05 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wing box and aircraft |
| CN109911176A (en) * | 2019-03-20 | 2019-06-21 | 成都飞机工业（集团）有限责任公司 | A kind of integral wing tank area flexible connection dry catheter structure |
| CN110920913A (en) * | 2019-12-04 | 2020-03-27 | 中国航空工业集团公司成都飞机设计研究所 | Double-oil-tank structure of reinforced wall plate made of composite material with high aspect ratio |
| EP3705395A1 (en) * | 2015-09-25 | 2020-09-09 | The Boeing Company | Low speed airfoil design for aerodynamic improved performance of uavs |
| CN114228975A (en) * | 2022-01-20 | 2022-03-25 | 湖南航天环宇通信科技股份有限公司 | Multi-cabin integral oil tank of unmanned aerial vehicle |
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| GB576124A (en) * | 1941-05-16 | 1946-03-20 | Us Rubber Co | Improvements in puncture sealing walls for containers, especially for fuel tanks |
| US3519228A (en) * | 1967-09-29 | 1970-07-07 | Dow Chemical Co | Airfoil structure |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104908958A (en) * | 2015-05-28 | 2015-09-16 | 河南翱翔航空科技有限公司 | Wing fuel tank |
| CN105059555A (en) * | 2015-08-14 | 2015-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Oil tank assembly oil leading devices and airplane with same |
| CN105221748A (en) * | 2015-08-25 | 2016-01-06 | 中国航空工业集团公司西安飞机设计研究所 | A kind of encapsulating method of aircraft integral tank |
| CN105205267B (en) * | 2015-09-24 | 2019-03-29 | 江西洪都航空工业集团有限责任公司 | A kind of integral wing tank load calculation method |
| CN105205267A (en) * | 2015-09-24 | 2015-12-30 | 江西洪都航空工业集团有限责任公司 | Method for calculating load of wing integral fuel tank |
| EP3705395A1 (en) * | 2015-09-25 | 2020-09-09 | The Boeing Company | Low speed airfoil design for aerodynamic improved performance of uavs |
| CN105253291A (en) * | 2015-10-14 | 2016-01-20 | 哈尔滨飞机工业集团有限责任公司 | Aerofoil integrated machine stiffened wall plate with comb-shaped connector and application |
| CN105445048A (en) * | 2015-11-24 | 2016-03-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Test method for connection interface sealing failure of integrated fuel tank structure |
| CN105501450A (en) * | 2015-11-30 | 2016-04-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned plane composite integral fuel tank sealing method |
| CN105501450B (en) * | 2015-11-30 | 2020-09-18 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle composite material integral oil tank sealing method |
| CN106585957A (en) * | 2016-12-14 | 2017-04-26 | 中航通飞研究院有限公司 | Composite wing integral oil tank and manufacturing method thereof |
| CN106585957B (en) * | 2016-12-14 | 2023-03-31 | 中航通飞研究院有限公司 | Composite material wing integral oil tank and manufacturing method thereof |
| CN107244409A (en) * | 2017-05-31 | 2017-10-13 | 彩虹无人机科技有限公司 | A kind of composite wing integral tank structure |
| CN107244409B (en) * | 2017-05-31 | 2019-08-09 | 彩虹无人机科技有限公司 | A kind of composite wing integral tank structure |
| CN109305328A (en) * | 2018-11-12 | 2019-02-05 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of wing box and aircraft |
| CN109305328B (en) * | 2018-11-12 | 2024-01-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Wing box and aircraft |
| CN109911176A (en) * | 2019-03-20 | 2019-06-21 | 成都飞机工业（集团）有限责任公司 | A kind of integral wing tank area flexible connection dry catheter structure |
| CN110920913A (en) * | 2019-12-04 | 2020-03-27 | 中国航空工业集团公司成都飞机设计研究所 | Double-oil-tank structure of reinforced wall plate made of composite material with high aspect ratio |
| CN110920913B (en) * | 2019-12-04 | 2023-06-23 | 中国航空工业集团公司成都飞机设计研究所 | Double-oil tank structure of reinforced wallboard made of composite material with large aspect ratio |
| CN114228975A (en) * | 2022-01-20 | 2022-03-25 | 湖南航天环宇通信科技股份有限公司 | Multi-cabin integral oil tank of unmanned aerial vehicle |
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Application publication date: 20150225 |