CN105501450A - Unmanned plane composite integral fuel tank sealing method - Google Patents
Unmanned plane composite integral fuel tank sealing method Download PDFInfo
- Publication number
- CN105501450A CN105501450A CN201510853857.2A CN201510853857A CN105501450A CN 105501450 A CN105501450 A CN 105501450A CN 201510853857 A CN201510853857 A CN 201510853857A CN 105501450 A CN105501450 A CN 105501450A
- Authority
- CN
- China
- Prior art keywords
- fuel tank
- aquaseal
- composite panel
- unmanned plane
- bolt hole
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000002828 fuel tank Substances 0.000 title claims abstract description 69
- 239000002131 composite material Substances 0.000 title claims abstract description 59
- 238000007789 sealing Methods 0.000 title claims abstract description 25
- 238000000034 method Methods 0.000 title claims abstract description 22
- 239000000565 sealant Substances 0.000 claims abstract description 11
- 238000005498 polishing Methods 0.000 claims abstract description 7
- 239000000853 adhesive Substances 0.000 claims abstract description 5
- 230000001070 adhesive effect Effects 0.000 claims abstract description 5
- 238000003032 molecular docking Methods 0.000 claims description 7
- 229920000742 Cotton Polymers 0.000 claims description 3
- 239000004809 Teflon Substances 0.000 claims description 3
- 229920006362 Teflon® Polymers 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 239000008393 encapsulating agent Substances 0.000 claims description 3
- 238000010422 painting Methods 0.000 claims description 3
- 238000007711 solidification Methods 0.000 claims description 3
- 230000008023 solidification Effects 0.000 claims description 3
- 239000002904 solvent Substances 0.000 claims description 3
- 239000003795 chemical substances by application Substances 0.000 abstract 3
- 239000003973 paint Substances 0.000 abstract 1
- 238000010276 construction Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000012512 characterization method Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005538 encapsulation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 239000002699 waste material Substances 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
- B64D37/06—Constructional adaptations thereof
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Application Of Or Painting With Fluid Materials (AREA)
Abstract
The invention relates to an unmanned plane composite integral fuel tank sealing method. The unmanned plane composite integral fuel tank sealing method comprises that 1) the fuel tank framework is subjected to paint removing and polishing, and then is coated by a sealant; 2) after the sealant is solidified, the surface of the sealant is polished; 3) a rubber plate is bonded on a wallboard sealing surface through a rubber adhesive to form a composite board; 4) bolt holes are punched in the composite board; 5) a layer of isolating agent is applied to the rubber surface of the composite board; 6) the sealant is applied to the fuel tank framework; 7) corresponding bolt holes of the composite board and the fuel tank framework are aligned and are connected through bolts; after the bolts are tightened, when the joint of the composite board and the fuel tank framework is extruded, the sealant flows out, if no sealant flows out, the composite board and the fuel tank framework are separated, and the step 1 is repeated; 8) after the sealant is hardened, the assembly is dismounted, and redundant sealant is cut off; and 9) residual isolating agent on the sealing surface is removed. By applying one layer of isolating agent on the composite board bonding surface, the composite board can be separated from the fuel tank framework easily, and the wallboard dismounting requirement can be effectively satisfied.
Description
Technical field
The invention belongs to integral tank field of structural design, particularly relate to a kind of unmanned plane composites fuel tank encapsulating method.
Background technology
Fuel tank stores the significant points of fuel oil as aircraft, have very high requirement, and integral type mailbox has better leak tightness to leak tightness, and therefore aircraft more and more commonly uses integral type mailbox now.Overall aircraft formula fuel tank common at present because of its volume large, operating personal can enter inside and construct, and fuel tank wallboard is without dismounting requirement, so convenient construction and sealing.
Because unmanned plane volume is narrow and small, therefore the fuel tank of unmanned plane is also by the restriction in space.Unmanned plane fuel tank needs to adopt integral structure, therefore more can cause that in fuel tank, construction space is narrow and small, construction access is nervous, and unmanned plane covering and fuel tank wallboard curvature complicated and have dismounting requirement, be difficult to reach desirable sealing effectiveness.
Summary of the invention
The object of this invention is to provide a kind of unmanned plane composites fuel tank encapsulating method, solve construction access difficulty and the narrow and small problem of construction space of current unmanned plane integral tank structure existence and have the bending skinpiston of dismounting requirement to be difficult to the problem sealed.
For achieving the above object, the technical solution used in the present invention is: a kind of unmanned plane composites fuel tank encapsulating method, comprises
Step one, coating removal, polishing on fuel tank skeleton, by sinking, in length and breadth joint aquaseal to carry out paintings flat;
Step 2, when after sealant cures polishing solidification after described encapsulant surface;
Step 3, fuel tank wallboard sealing surface with aquaseal adhesive rubber plate formed composite panel;
Step 4, on described composite panel, beat bolt hole, the bolt hole on the bolt hole on described composite panel and described fuel tank skeleton joins work;
Step 5, be coated with one deck separant in the rubber face of described composite panel;
Step 6, on fuel tank reinforced seal face, be coated with aquaseal;
Step 7, the rubber face of described composite panel is opposed with the sealing surface of described fuel tank skeleton, and the bolt hole of the bolt hole of described composite panel with described fuel tank skeleton is alignd, a part of bolt hole penetrates bolt, and another part bolt hole inserts bearing pin;
Step 8, tighten described bolt, when described composite panel has described aquaseal to flow out with the surrounding any position at the described fuel tank skeleton place of combining, if be full of, then carry out step 10; If underfill, carry out step 9;
Step 9, described bolt unscrewed and separates the rubber face of described composite panel and the sealing surface of described fuel tank skeleton, then do not flow out described aquaseal position described fuel tank skeleton sealing surface on again add aquaseal, and repeat step 8;
Step 10, dismounting assembling after aquaseal hardness reaches predetermined extent, cut the aquaseal be extruded along sealing surface;
Step 11, remove separant residual on sealing surface with the cotton rag being soaked with solvent.
Further, the rubber plate in described step 3 is that docking forms, and docking mode adopts zigzag, and butt seam is less than 0.2mm.
Further, described rubber plate thickness is 1.5mm.
Further, the bolt layout type that composite panel described in step 7 penetrates bolt hole assembles for installing 1 group of bolt every 3 described bolts hole.
Further, the state that predetermined extent described in step 10 refers to aquaseal be in gluey and solid-state between.
Further, also step 12 is comprised: sealed by the joint teflon seal section bar of the described fuel tank wallboard of arbitrary neighborhood.
A kind of unmanned plane composites fuel tank encapsulating method of the present invention, carries out integral installation by forming composite panel and fuel tank skeleton at wallboard sealing surface sticker rubber plate, solves that fuel tank volume is narrow and small, the nervous problem that cannot construct of construction access; Again by being coated with one deck separant at composite panel bonding plane, making composite panel and fuel tank skeleton be easy to the method be separated, effectively can solve the problem that wallboard has dismounting to require.
Accompanying drawing explanation
Accompanying drawing to be herein merged in specification sheets and to form the part of this specification sheets, shows embodiment according to the invention, and is used from specification sheets one and explains principle of the present invention.
Fig. 1 is the fuel tank wallboard schematic diagram bonding with skeleton of unmanned plane composites fuel tank encapsulating method according to an embodiment of the invention;
Fig. 2 is rubber plate zigzag docking structure schematic diagram according to an embodiment of the invention.
Wherein 1 is wallboard, and 2 is rubber plates, and 3 is separants, and 4 is aquaseals, and 5 is skeletons, and 6 is rubber plates.
Detailed description of the invention
For making object of the invention process, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the present invention's part embodiment, instead of whole embodiments.Be exemplary type below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.Based on the embodiment in the present invention, those of ordinary skill in the art, not making the every other embodiment obtained under creation type work prerequisite, belong to the scope of protection of the invention.Below in conjunction with accompanying drawing, embodiments of the invention are described in detail.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end ", " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore limiting the scope of the invention can not be interpreted as.
As depicted in figs. 1 and 2, adopt a kind of unmanned plane composites fuel tank encapsulating method of the present invention,
First oil carries out case skeleton treatment:
1) coating removal, polishing on fuel tank skeleton.By sinking, in length and breadth joint aquaseal to carry out paintings flat;
2) when the described encapsulant surface after polishing solidification after sealant cures;
Then the process of fuel tank wallboard is carried out:
3) composite panel is formed at wallboard sealing surface rubber based adhesives adhesive rubber plate; Rubber plate is likely entire plate, be also likely each block of rubber plate is that docking forms, and docking mode adopts zigzag, and butt seam is less than 0.2mm.Rubber plate thickness is 1.5mm.
4) on described composite panel, beat bolt hole, the bolt hole on the bolt hole on described composite panel and described fuel tank skeleton joins work;
5) be coated with one deck separant in the rubber face of described composite panel, thus make composite panel be easy to be separated with fuel tank skeleton, and then realize the ability to dismantle of fuel tank;
Last fuel tank skeleton is connected encapsulation process with wallboard:
6) on fuel tank skeleton, aquaseal is coated with;
7) rubber face of described composite panel is opposed with the sealing surface of described fuel tank skeleton, and the bolt hole of the bolt hole of described composite panel with described fuel tank skeleton is alignd, a part of bolt hole penetrates bolt, and another part bolt hole inserts bearing pin.After described bolt tightening, should be able to aquaseal be squeezed out at described composite panel and described fuel tank skeleton junction, if flow out without aquaseal, then should take described composite panel and described fuel tank skeleton apart, and repeating said steps 1.
Install 1 when bolt hole wears bolt every 3 bolts hole to assemble with bolt, the order paying special attention to tie bolt should be evenly distributed on wallboard.Aquaseal should squeeze any position along edge and press out, if do not have solation to go out, should take apart, and gluing is installed again.All the other bolt hole pins or bolt block, and ensure to remain without aquaseal in bolt hole.
8) dismounting assembling after aquaseal hardness acquires a certain degree, cuts the aquaseal be extruded along sealing surface;
Aquaseal hardness can not too firmly can not be too soft, waste time and energy when aquaseal cuts the aquaseal extruded too firmly, and may wallboard be switched to, the too soft meeting of aquaseal hardness becomes flow regime, at this time cutting aquaseal not only can adhesion cutting knife, and composite panel and the fuel tank wallboard alignd may be caused to produce displacement, the state of best aquaseal be in glue and solid-state between.
9) separant residual on sealing surface is removed with the cotton rag being soaked with solvent.
So far complete the skeleton of detachable integral tank and the connection of wallboard, finally with teflon seal section bar, the joint of adjacent wallboard is sealed.
Unmanned plane composites fuel tank encapsulating method of the present invention, carries out integral installation by forming composite panel and fuel tank skeleton at wallboard sealing surface sticker rubber plate, solves that fuel tank volume is narrow and small, the nervous problem that cannot construct of construction access; Again by being coated with one deck separant at composite panel bonding plane, making composite panel and fuel tank skeleton be easy to the method be separated, effectively can solve the problem that wallboard has dismounting to require.
The above; be only optimum detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of described claim.
Claims (6)
1. a unmanned plane composites fuel tank encapsulating method, is characterized in that: comprise
Step one, coating removal, polishing on fuel tank skeleton, by sinking, in length and breadth joint aquaseal to carry out paintings flat;
Step 2, when after sealant cures polishing solidification after described encapsulant surface;
Step 3, fuel tank wallboard sealing surface with aquaseal adhesive rubber plate formed composite panel;
Step 4, on described composite panel, beat bolt hole, the bolt hole on the bolt hole on described composite panel and described fuel tank skeleton joins work;
Step 5, be coated with one deck separant in the rubber face of described composite panel;
Step 6, on fuel tank reinforced seal face, be coated with aquaseal;
Step 7, the rubber face of described composite panel is opposed with the sealing surface of described fuel tank skeleton, and the bolt hole of the bolt hole of described composite panel with described fuel tank skeleton is alignd, a part of bolt hole penetrates bolt, and another part bolt hole inserts bearing pin;
Step 8, tighten described bolt, when described composite panel has described aquaseal to flow out with the surrounding any position at the described fuel tank skeleton place of combining, if be full of, then carry out step 10; If underfill, carry out step 9;
Step 9, described bolt unscrewed and separates the rubber face of described composite panel and the sealing surface of described fuel tank skeleton, then do not flow out described aquaseal position described fuel tank skeleton sealing surface on again add aquaseal, and repeat step 8;
Step 10, dismounting assembling after aquaseal hardness reaches predetermined extent, cut the aquaseal be extruded along sealing surface;
Step 11, remove separant residual on sealing surface with the cotton rag being soaked with solvent.
2. unmanned plane composites fuel tank encapsulating method according to claim 1, is characterized in that, the rubber plate in described step 3 is that docking forms, and docking mode adopts zigzag, and butt seam is less than 0.2mm.
3. unmanned plane composites fuel tank encapsulating method according to claim 2, it is characterized in that, described rubber plate thickness is 1.5mm.
4. unmanned plane composites fuel tank encapsulating method according to claim 1, it is characterized in that, the bolt layout type that composite panel described in step 7 penetrates bolt hole assembles for installing 1 group of bolt every 3 described bolts hole.
5. unmanned plane composites fuel tank encapsulating method according to claim 1, is characterized in that, the state that predetermined extent described in step 10 refers to aquaseal be in gluey and solid-state between.
6. unmanned plane composites fuel tank encapsulating method according to claim 1, is characterized in that, also comprise step 12: sealed by the joint teflon seal section bar of the described fuel tank wallboard of arbitrary neighborhood.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510853857.2A CN105501450B (en) | 2015-11-30 | 2015-11-30 | Unmanned aerial vehicle composite material integral oil tank sealing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510853857.2A CN105501450B (en) | 2015-11-30 | 2015-11-30 | Unmanned aerial vehicle composite material integral oil tank sealing method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105501450A true CN105501450A (en) | 2016-04-20 |
| CN105501450B CN105501450B (en) | 2020-09-18 |
Family
ID=55709855
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510853857.2A Active CN105501450B (en) | 2015-11-30 | 2015-11-30 | Unmanned aerial vehicle composite material integral oil tank sealing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105501450B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146643A (en) * | 2016-12-06 | 2018-06-12 | 成都凯迪精工科技有限责任公司 | A kind of small reservoir manufacturing method for adapting to big dive angle |
| CN112072335A (en) * | 2020-09-25 | 2020-12-11 | 中国直升机设计研究所 | Conductive structure between composite material structural members and conductive processing method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2401627A (en) * | 1941-05-16 | 1946-06-04 | Us Rubber Co | Puncture sealing gas tank |
| CN101982247A (en) * | 2010-11-15 | 2011-03-02 | 陕西飞机工业（集团）有限公司 | Method for sealing and preventing integral wing tank of large-medium transport from corrosion |
| US7900412B2 (en) * | 2003-12-23 | 2011-03-08 | Airbus Uk Limited | Sealing material |
| CN203335845U (en) * | 2013-06-27 | 2013-12-11 | 江西洪都航空工业集团有限责任公司 | Novel airplane oil tank sealing structure |
| CN104369857A (en) * | 2014-10-15 | 2015-02-25 | 中航飞机股份有限公司西安飞机分公司 | Whole oil tank structure of airplane |
| CN204688426U (en) * | 2015-05-28 | 2015-10-07 | 河南翱翔航空科技有限公司 | Wing tank |
| CN105102319A (en) * | 2013-03-26 | 2015-11-25 | 三菱重工业株式会社 | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body |
-
2015
- 2015-11-30 CN CN201510853857.2A patent/CN105501450B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2401627A (en) * | 1941-05-16 | 1946-06-04 | Us Rubber Co | Puncture sealing gas tank |
| US7900412B2 (en) * | 2003-12-23 | 2011-03-08 | Airbus Uk Limited | Sealing material |
| CN101982247A (en) * | 2010-11-15 | 2011-03-02 | 陕西飞机工业（集团）有限公司 | Method for sealing and preventing integral wing tank of large-medium transport from corrosion |
| CN105102319A (en) * | 2013-03-26 | 2015-11-25 | 三菱重工业株式会社 | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body |
| CN203335845U (en) * | 2013-06-27 | 2013-12-11 | 江西洪都航空工业集团有限责任公司 | Novel airplane oil tank sealing structure |
| CN104369857A (en) * | 2014-10-15 | 2015-02-25 | 中航飞机股份有限公司西安飞机分公司 | Whole oil tank structure of airplane |
| CN204688426U (en) * | 2015-05-28 | 2015-10-07 | 河南翱翔航空科技有限公司 | Wing tank |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108146643A (en) * | 2016-12-06 | 2018-06-12 | 成都凯迪精工科技有限责任公司 | A kind of small reservoir manufacturing method for adapting to big dive angle |
| CN108146643B (en) * | 2016-12-06 | 2020-12-29 | 成都凯迪精工科技有限责任公司 | Manufacturing method of small oil tank suitable for large diving angle |
| CN112072335A (en) * | 2020-09-25 | 2020-12-11 | 中国直升机设计研究所 | Conductive structure between composite material structural members and conductive processing method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105501450B (en) | 2020-09-18 |
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