CN108146643A - A kind of small reservoir manufacturing method for adapting to big dive angle - Google Patents
A kind of small reservoir manufacturing method for adapting to big dive angle Download PDFInfo
- Publication number
- CN108146643A CN108146643A CN201611111502.7A CN201611111502A CN108146643A CN 108146643 A CN108146643 A CN 108146643A CN 201611111502 A CN201611111502 A CN 201611111502A CN 108146643 A CN108146643 A CN 108146643A
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- Prior art keywords
- fuel tank
- oil
- big
- small
- lower housing
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Classifications
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- 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
-
- 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
- B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Details Of Rigid Or Semi-Rigid Containers (AREA)
Abstract
The invention belongs to aviation field, more particularly to a kind of manufacturing method for the small reservoir for adapting to big dive angle.Design feature, manufacture difficult point of this technology according to small reservoir, collateral security fuel tank fuel feeding in the state of various navigation attitudes is smooth, fall the small fuel tank oil separating plate of 10 ° of " convex " font structure, band back rake angles for the end face of ingehious design fuel tank, ensure that aircraft fuel feeding 30Min under big dive angle (≯ 60 °) state is not parking；Compact oil suction, Breathable oil nozzle, the use of ball-type oil hammer, meet aircraft climb, rolling, the fuel feeding demand under the various flight attitudes such as underriding；The hollow grease proofing impact sponge of filling, makes fluid be unlikely to generate big Oil shocking under various big overload postures, makes the center of gravity of airplane that big variation not occur；Fuel tank matrix uses composite material, alleviates the weight of fuel tank, avoids the defects of traditional fuel tank is using Welded manufacturing process, fuel tank is lighter in the case of identical oil capacity, and cost is less expensive.
Description
Technical field
The invention belongs to aviation fields, more particularly to a kind of manufacturing method for the small reservoir for adapting to big dive angle, pass through
This method designs the small fuel tank oil separating plate that end face is used to fall 10 ° of " convex " font structure, band back rake angles, can realize that aircraft is being bowed greatly
Fuel feeding 30Min is not parking under the angle of attack (≯ 60 °) state；The use of the hollow grease proofing impact sponge of filling, makes aircraft fuel oil various
It is unlikely to generate big Oil shocking under big overload posture, makes the center of gravity of airplane that big variation not occur.
Background technology
With the high speed development of small-sized pilotless aircraft, to aircraft range, the requirement of flying height is higher and higher.Battery power
Small-sized pilotless aircraft voyage and cruise duration it is limited, it is desirable to by motor driving be changed to oil machine driving, aircraft be changed to oil machine drive
After dynamic, voyage and cruise duration are multiplied, and the payload of the also increased aircraft of powerful gasoline engine.To realize
Electric drive changes oily driving, wherein requiring the fuel tank of tool oil storage function, traditional fuel tanker uses Welded system mostly
It makes, but the fuel tank of small drone has its particular/special requirement：Identical oil capacity requirement fuel tank is lighter, of low cost, to adapt to bow greatly
Fuel feeding 30Min is not parking under the angle of attack (≯ 60 °) state, and fluid does not generate big impact concussion under big overload state.This will
A kind of realistic existing composite material is the Oiltank structure of matrix, has compact oil suction, Breathable oil nozzle, ensures that small fuel tank fluid is opposite
Stable oil separating plate prevents fluid from generating the hollow filling sponge of fuel tank of greater impact under big flight attitude.
Invention content
The object of the invention
Realize a kind of small reservoir manufacturing method of " convex " font structure, which can meet the small of 10 ° of back rake angles of band
Fuel tank oil separating plate realizes that aircraft fuel feeding 30Min under big dive angle (≯ 60 °) state is not parking；Use the hollow grease proofing punching of filling
Sponge is hit, meets aircraft and is unlikely to generate big Oil shocking, and the center of gravity of airplane is made not occur under various big overload postures
Big variation.
Technical solution
A kind of small reservoir manufacturing method for adapting to big dive angle, which is characterized in that include the following steps：
Step 1：According to the theoretical shape of fuel tank, the composite material mould of tank envelope is designed；
Step 2：According to fuel tank upper shell mould theory cavity plate type face, fuel tank upper shell is laid；
Step 3：According to fuel tank lower shell mold theory cavity plate type face, fuel tank lower housing is laid；；
Step 4：By short side block 21 with adhering with epoxy resin in fuel tank lower housing left and right sides, short side stop width direction
Stay half exposed；
Step 5：By long side block blocks 22 with adhering with epoxy resin in fuel tank lower housing front and rear sides, long stop width direction
Stay half exposed；
Step 6：By small fuel tank link stopper 23 with adhering with epoxy resin fall " convex " font pit mouth, and with fuel tank baseplane
10 ° of (semicircle nose end has a down dip) inclination angles are kept, except semicircle orifice outer periphery need to cement and seal with fuel tank sidewall；
Step 7：Oil nozzle external member 5 is inserted into 1 corresponding hole of fuel tank upper shell, and cementing secured, it is desirable that sealing；
Step 8：Oil pipe 6 is inserted in the corresponding oil-Absorbing nozzle of oil nozzle external member, and with small wire binding；
Step 9：Oil hammer 7 is inserted into oil pipe 6 and with small wire binding, steel wire there cannot be big protrusion, influence oil hammer small
Fuel tank it is free to slide；
Step 10：The fuel tank lower housing of step 7 will be completed, asphalt mixtures modified by epoxy resin is coated in advance on the block at surrounding emersion edge
The fuel tank upper housing component for completing step 10 is inserted into the fuel tank lower housing for completing step 7, notices that all edge link stoppers are equal by fat
It is bonded with fuel tank upper shell inside edge；
Step 11：Entirety is bonded as with the painting epoxy resin of cloth 3 is tightly connected in fuel tank upper-lower casing surrounding faying face, and
Sealing.
In the fuel tank lower housing 2, highly away from fuel tank lower shell surface edge about 10mm, it is packed into one end and cuts semicircle orifice
Cavernous body 4 and small 23 semicircle orifice of fuel tank link stopper are substantially aligned；
Advantageous effect
Design feature, manufacture difficult point of this technology according to small reservoir, collateral security fuel tank supply in the state of various navigation attitudes
It is oily smoothly, fall the small fuel tank oil separating plate of 10 ° of " convex " font structure, band back rake angles for the end face of ingehious design fuel tank, ensure that winged
Machine fuel feeding 30Min under big dive angle (≯ 60 °) state is not parking；Compact oil suction, Breathable oil nozzle, the use of ball-type oil hammer,
Meet aircraft climb, rolling, the fuel feeding demand under the various flight attitudes such as underriding；The hollow grease proofing impact sponge of filling, makes
Fluid is unlikely to generate big Oil shocking under various big overload postures, makes the center of gravity of airplane that big variation not occur；Fuel tank base
Body uses composite material, alleviates the weight of fuel tank, avoids the defects of traditional fuel tank is using Welded manufacturing process,
Fuel tank is lighter in the case of identical oil capacity, and cost is less expensive.
Description of the drawings
Fig. 1 is one Oiltank structure schematic diagram to be formed of the embodiment of the present invention；
Fig. 2 is one fuel tank shell mold schematic diagram of the embodiment of the present invention；
Fig. 3 is mold schematic diagram under one fuel tank shell of the embodiment of the present invention；
Fig. 4 is one fuel tank shell explosive view of the embodiment of the present invention；
Fig. 5 is one fuel tank lower housing sponge of embodiment of the present invention filling schematic diagram；
Fig. 6 is one fuel tank upper shell oil nozzle assembling schematic diagram of the embodiment of the present invention；
Fig. 7 is one fuel tank upper shell assembling schematic diagram of the embodiment of the present invention.
Wherein, 1- fuel tanks upper shell, 2- fuel tank lower housings, 21- short side blocks, 22- long side block blocks, the small fuel tank link stoppers of 23-,
3- is tightly connected cloth, 4- cavernous bodies, 5- oil nozzle external members, 6- oil pipes, 7- oil hammers.
Embodiment
The present invention is described in further details below in conjunction with the accompanying drawings, is please referred to Fig.1 to Fig. 7.
As shown in Figure 1, for Oiltank structure schematic diagram to be formed
Fuel tank shell uses glass fiber compound material, and thickness of shell 0.6mm is laid with mold and is molded.Housing is divided into
Two components of upper shell and lower housing, upper shell are connected with nozzle component, oil pipe, oil hammer, and the junction of oil nozzle and upper shell will
Ask sealing, oil nozzle in addition to slotting knot, also needs secured with finer wire butting with oil pipe, and oil hammer is designed as ball-type shape, after oil pipe grafting
Also finer wire butting is used, oil pipe will select soft material, and conducive to aircraft under different course postures, oil hammer can be rolled to
The lowest part of small fuel tank, so as to ensure the sucking of oil plant.The small fuel tank oral area of lower housing need to glue a small fuel tank block, and block retreats
Tiltedly, about 10 ° of inclination angle, in addition to partition board upper half circular hole, surrounding is required to adhering and sealing.Inclination angle passes through block half conducive to oil plant
Circular hole flows into small fuel tank and carries out oil plant supplement.In fuel tank hollow space, the oil resistant sponge of 15PPi porositys need to be filled, sponge was both
The too many space of fuel tank is not take up, in the case where aircraft carries out the motor-driven posture of big overload, and fuel oil can be controlled to generate moment impact, and
Fuel oil can also slowly flow freely in fuel tank.
This technology is that solution aircraft fuel feeding 30Min under big dive angle (≯ 60 °) state is not parking；Compact suction
Oil, Breathable oil nozzle, the use of ball-type oil hammer, meet aircraft climb, rolling, the fuel feeding need under the various flight attitudes such as underridings
It asks；The hollow grease proofing impact sponge of filling, makes fluid be unlikely to generate big Oil shocking under various big overload postures, makes aircraft
Big variation occurs for center of gravity；Fuel tank matrix uses composite material, alleviates the weight of fuel tank, avoids traditional fuel tank and is closed using aluminium
Gold solder connects the defects of manufacturing process, and fuel tank is lighter in the case of identical oil capacity, and cost is less expensive.
According to a kind of small reservoir manufacturing method for adapting to big dive angle of the present invention, include the following steps：
Step 1：According to the theoretical shape of fuel tank, the composite material mould of tank envelope is designed；
Step 2：According to fuel tank upper shell mould theory cavity plate type face, fuel tank upper shell is laid；
Step 3：According to fuel tank lower shell mold theory cavity plate type face, fuel tank lower housing is laid；；
Step 4：By short side block 21 with adhering with epoxy resin in fuel tank lower housing left and right sides, short side stop width direction
Stay half exposed；
Step 5：By long side block blocks 22 with adhering with epoxy resin in fuel tank lower housing front and rear sides, long stop width direction
Stay half exposed；
Step 6：By small fuel tank link stopper 23 with adhering with epoxy resin fall " convex " font pit mouth, and with fuel tank baseplane
10 ° of (semicircle nose end has a down dip) inclination angles are kept, except semicircle orifice outer periphery need to cement and seal with fuel tank sidewall；
Step 7：Semicircle orifice is cut into 4 one end of cavernous body, is packed into fuel tank lower housing 2, height has fuel tank lower shell surface
Edge about 10mm, sponge semicircle orifice and small 23 semicircle orifice of fuel tank link stopper are substantially aligned；
Step 8：Oil nozzle external member 5 is inserted into 1 corresponding hole of fuel tank upper shell, and cementing secured, it is desirable that sealing；
Step 9：Oil pipe 6 is inserted in the corresponding oil-Absorbing nozzle of oil nozzle external member, and with small wire binding；
Step 10：Oil hammer 7 is inserted into oil pipe 6 and with small wire binding, steel wire there cannot be big protrusion, influence oil hammer small
Fuel tank it is free to slide；
Step 11：The fuel tank lower housing of step 7 will be completed, asphalt mixtures modified by epoxy resin is coated in advance on the block at surrounding emersion edge
The fuel tank upper housing component for completing step 10 is inserted into the fuel tank lower housing for completing step 7, notices that all edge link stoppers are equal by fat
It is bonded with fuel tank upper shell inside edge；
Step 12：Entirety is bonded as, and close with the painting epoxy resin of cloth 3 is tightly connected in fuel tank upper-lower casing surrounding faying face
Envelope.
As shown in Fig. 2, for fuel tank shell mold schematic diagram, the figure illustrates mold design during laying fuel tank upper shell
Method：For convenience of demoulding, mold is divided into left and right two halves, and when use is inserted into positioning pin in the location hole at both ends, or so mold
Merge into entirety.Finished when glass fibre is answered material covering (0.6mm thick) laying, after its curing along mold opening cut,
Integer covering cuts out oil nozzle external member mounting hole along mold middle circle pit.Left and right ends dowel hole is pulled out at this time, is separated
Left and right mold handles the demoulding of fuel tank covering.
As shown in figure 3, for mold schematic diagram under fuel tank shell, the figure illustrates mold design during laying fuel tank lower housing
Method：Its specific laying operating procedure is identical with fuel tank upper shell operation order.
As shown in figure 4, fuel tank shell explosive view, the figure illustrates fuel tank upper-lower casing after respectively parts are assembled,
Upper-lower casing assembling, the process of sealing.Short side block 21 and long side block blocks 22 under fuel tank shell 2 it is Nian Jie securely after, on fuel tank
Housing 1 is covered with lower housing 2 together to good, and short side block 21 is inserted into after first coating epoxyn with long side block blocks 22 on fuel tank
Case inside mends viscous sealed connection cloth 3 in the joint of fuel tank upper-lower casing along surrounding, which act as sealing
Also firm connection fuel tank upper-lower casing, is integrated it outside the gap of fuel tank upper-lower casing.
As shown in figure 5, filling schematic diagram for fuel tank lower housing sponge, the figure illustrates filled inside fuel tank lower housing
The area of space of the oil resistant sponge 4 of 15PPi porositys, sponge be both not take up the too many space of fuel tank, were carried out in aircraft greater than carrier aircraft
Under dynamic posture, and fuel oil can be controlled to generate moment impact, and fuel oil can also slowly flow freely in fuel tank.
As shown in fig. 6, for fuel tank upper shell oil nozzle assembling schematic diagram, the figure illustrates fuel tank upper shells to connect oil nozzle external member
5th, the assembly relation of oil pipe 6 and oil hammer 7.Upper shell is connected with nozzle component, oil pipe, oil hammer, the junction of oil nozzle and upper shell
It is required that sealing, oil nozzle and oil pipe also need secured with finer wire butting in addition to slotting knot, and oil hammer is designed as ball-type shape, with oil pipe grafting
Finer wire butting is also used afterwards, and oil pipe will select soft material, and conducive to aircraft under different course postures, oil hammer can roll
To the lowest part of small fuel tank, so as to ensure the sucking of oil plant.
As shown in fig. 7, for fuel tank upper shell assembling schematic diagram, the figure illustrates the rigging position passes of fuel tank upper-lower casing
System, figure show its internal structure situation after being splitted from centre.
Claims (2)
1. a kind of small reservoir manufacturing method for adapting to big dive angle, which is characterized in that include the following steps：
Step 1：According to the theoretical shape of fuel tank, the composite material mould of tank envelope is designed；
Step 2：According to fuel tank upper shell mould theory cavity plate type face, fuel tank upper shell is laid；
Step 3：According to fuel tank lower shell mold theory cavity plate type face, fuel tank lower housing is laid；；
Step 4：By short side block 21 with adhering with epoxy resin in fuel tank lower housing left and right sides, short side stop width direction stays one
Half is exposed；
Step 5：By long side block blocks 22 with adhering with epoxy resin in fuel tank lower housing front and rear sides, long stop width direction stays one
Half is exposed；
Step 6：By small fuel tank link stopper 23 with adhering with epoxy resin in " convex " font pit mouth, and kept with fuel tank baseplane
10 ° of inclination angles, except semicircle orifice outer periphery need to cement and seal with fuel tank sidewall；
Step 7：Oil nozzle external member 5 is inserted into 1 corresponding hole of fuel tank upper shell, and cementing secured, it is desirable that sealing；
Step 8：Oil pipe 6 is inserted in the corresponding oil-Absorbing nozzle of oil nozzle external member, and with small wire binding；
Step 9：Oil hammer 7 is inserted into oil pipe 6 and with small wire binding, steel wire there cannot be big protrusion, influence oil hammer in small fuel tank
It is free to slide；
Step 10：The fuel tank lower housing of step 7 will be completed, epoxy resin is coated in advance on the block at surrounding emersion edge, it will
The fuel tank upper housing component for completing step 10 is inserted into the fuel tank lower housing for completing step 7, pays attention to all edge link stoppers and fuel tank
Upper shell inside edge is bonded；
Step 11：Entirety is bonded as, and close with the painting epoxy resin of cloth 3 is tightly connected in fuel tank upper-lower casing surrounding faying face
Envelope.
2. the small reservoir manufacturing method of big dive angle is adapted to as described in claim 1, which is characterized in that under the fuel tank
In housing 2, highly away from fuel tank lower shell surface edge about 10mm, it is packed into one end and cuts the cavernous body 4 of semicircle orifice and small fuel tank shelves
23 semicircle orifice of block is substantially aligned.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611111502.7A CN108146643B (en) | 2016-12-06 | 2016-12-06 | Manufacturing method of small oil tank suitable for large diving angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611111502.7A CN108146643B (en) | 2016-12-06 | 2016-12-06 | Manufacturing method of small oil tank suitable for large diving angle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108146643A true CN108146643A (en) | 2018-06-12 |
| CN108146643B CN108146643B (en) | 2020-12-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611111502.7A Active CN108146643B (en) | 2016-12-06 | 2016-12-06 | Manufacturing method of small oil tank suitable for large diving angle |
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| CN (1) | CN108146643B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111056021A (en) * | 2019-12-31 | 2020-04-24 | 西安沃祥航空科技有限公司 | Mechanical fuel oil gravity center control oil tank |
| CN111085660A (en) * | 2018-10-24 | 2020-05-01 | 四川特飞科技股份有限公司 | Oil tank manufacturing method and small unmanned aerial vehicle oil tank |
| CN112896532A (en) * | 2021-01-13 | 2021-06-04 | 中国商用飞机有限责任公司 | Oil tank cover and manufacturing process thereof |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3567536A (en) * | 1968-02-07 | 1971-03-02 | Goodyear Tire & Rubber | Container and method of preparation |
| GB2088281B (en) * | 1980-12-03 | 1985-06-12 | Goodyear Aerospace Corp | Fabric reinforced composite material for a flexible-walled container and method of making said container |
| US20130193150A1 (en) * | 2012-01-30 | 2013-08-01 | Neal Keefer | Molded fuel tank and method of manufacturing the same |
| CN204152693U (en) * | 2014-10-20 | 2015-02-11 | 重庆工商职业学院 | Fuel tank of small-sized general gasoline |
| 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 |
-
2016
- 2016-12-06 CN CN201611111502.7A patent/CN108146643B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3567536A (en) * | 1968-02-07 | 1971-03-02 | Goodyear Tire & Rubber | Container and method of preparation |
| GB2088281B (en) * | 1980-12-03 | 1985-06-12 | Goodyear Aerospace Corp | Fabric reinforced composite material for a flexible-walled container and method of making said container |
| US20130193150A1 (en) * | 2012-01-30 | 2013-08-01 | Neal Keefer | Molded fuel tank and method of manufacturing the same |
| CN204152693U (en) * | 2014-10-20 | 2015-02-11 | 重庆工商职业学院 | Fuel tank of small-sized general gasoline |
| 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 |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111085660A (en) * | 2018-10-24 | 2020-05-01 | 四川特飞科技股份有限公司 | Oil tank manufacturing method and small unmanned aerial vehicle oil tank |
| CN111056021A (en) * | 2019-12-31 | 2020-04-24 | 西安沃祥航空科技有限公司 | Mechanical fuel oil gravity center control oil tank |
| CN111056021B (en) * | 2019-12-31 | 2021-06-01 | 西安沃祥航空科技有限公司 | Mechanical fuel oil gravity center control oil tank |
| CN112896532A (en) * | 2021-01-13 | 2021-06-04 | 中国商用飞机有限责任公司 | Oil tank cover and manufacturing process thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108146643B (en) | 2020-12-29 |
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