CN105270641B - The plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit - Google Patents
The plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit Download PDFInfo
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- CN105270641B CN105270641B CN201510654377.3A CN201510654377A CN105270641B CN 105270641 B CN105270641 B CN 105270641B CN 201510654377 A CN201510654377 A CN 201510654377A CN 105270641 B CN105270641 B CN 105270641B
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- leading portion
- portion covering
- radome fairing
- fuel tank
- bird
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Abstract
This application provides the plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit, including radome fairing, cushioning fender, cock body, leading portion covering I and leading portion covering II, radome fairing is variable cross-section thick-walled structure, leading portion covering I is connected with radome fairing by connector, ensures that leading portion covering I is less than 1mm with rectification cover outer surface assembling jump；Cushioning fender is located at behind radome fairing, for separating leading portion covering I and radome fairing, the fuel oil in leading portion covering I and its rear structure is cannot be introduced into radome fairing.The application structure design is simple, manufactures and assemble very convenient, can effectively withstand the shock of flying bird, ensure that auxiliary fuel tank will not produce Leakage or parts come off and make the behavior of influence Flight Safety.
Description
Technical field
The application is related to the anti-bird impact design of the plug-in auxiliary fuel tank of aircraft, the plug-in auxiliary fuel tank of aircraft that particularly a kind of anti-bird is hit
Leading edge structure.
Background technology
Aircraft is in flight, if plug-in auxiliary fuel tank is hit by flying bird, it may occur that auxiliary fuel tank is damaged, and fuel oil is let out
Leakage etc. influences the situation of aircraft safety.
The design of the plug-in auxiliary fuel tank of civil aircraft, it is necessary to meet what CAAC formulated《Airplane in transportation category seaworthiness mark
It is accurate》In regulation in 25.571 (e) (1) clause, that is, must assure that its shock in the bird by 1.80 kilograms of (4 pounds) weights
Afterwards, aircraft remains to successfully complete this flight, and aircraft takes Hai Ping with relative velocity of the bird along aircraft flight flight path during collision
Face Vc or 2,450 meters of (8000 feet) 0.85Vc, the more severe case in both.When bird is hit, plug-in auxiliary fuel tank leading edge structure is first
Hit, to meet clause requirement it is necessary to design a kind of plug-in auxiliary fuel tank leading edge structure that can withstand bird strike.
Typically there are following several designs：
1) auxiliary fuel tank leading edge designs a sharp head, in bird strike, for flying bird of riving.
2) cancel the plug-in form of auxiliary fuel tank, it is designed as Conformal Fuel Tanks.
Design for auxiliary tank of aircraft leading edge, to consider that manufacturing process and assembling should simple as far as possible, quick, sides
Just, and aerodynamic configuration meets to require.Requirement of the first design to manufacturing process is higher；Second of design needs
The profile of whole aircraft, the difficulty increase of design, manufacture and assembling are changed, and the pilot project for needing to verify increases, not only
Lose time and waste of manpower.
So it is badly in need of designing a kind of simple in construction and disclosure satisfy that anti-bird hits the plug-in auxiliary fuel tank leading edge structure of requirement.
The content of the invention
, will not after bird is hit this application provides a kind of plug-in auxiliary fuel tank leading edge structure of aircraft in order to solve problem above
Produce situations such as oil leak or parts come off and influence Flight Safety, and simple in construction need not change aircraft configuration.
The plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit, including radome fairing, cushioning fender, cock body, leading portion covering I
With leading portion covering II, radome fairing is variable cross-section thick-walled structure, and minimum thickness section is located at rectification shroud rim, is 5mm~10mm, most
Big thickness x cross sectional is located at radome fairing center, is 10mm~30mm, between minimum thickness and maximum gauge section for circular arc gradually
Become transition, to radome fairing edge chamfer；Leading portion covering I is connected with radome fairing by connector, ensures leading portion covering I and radome fairing
Outer surface assembling jump is less than 1mm；Cushioning fender is located at behind radome fairing, by being welded to connect on leading portion covering I；Cock body welds
It is connected in the hole among cushioning fender, for separating leading portion covering I and radome fairing, makes in leading portion covering I and its rear structure
Fuel oil cannot be introduced into radome fairing.The position of centre of gravity of auxiliary fuel tank can be adjusted by changing the length dimension of cock body；Leading edge
Covering I and leading portion covering II are designed to different thickness, are connected together by welding, play loss of weight effect.
The advantages of the application, is that structure design is simple, manufactures and assemble very convenient, disclosure satisfy that《Airplane in transportation category is fitted
Navigation mark is accurate》In regulation in 25.571 (e) (1) clause, effectively withstand the shock of flying bird, ensure that auxiliary fuel tank will not produce
Leakage or parts come off and make the behavior of influence Flight Safety.
This application is described in further detail below in conjunction with specific embodiment accompanying drawing：
Brief description of the drawings：
Fig. 1 is plug-in auxiliary fuel tank leading edge structure signal；
Fig. 2 is Fig. 1 regional area I amplification signal；
Fig. 3 is that the plug-in auxiliary fuel tank leading edge structure for not including radome fairing is illustrated；
Fig. 4 is Fig. 3 A to signal；
Fig. 5 is radome fairing signal；
Fig. 6 is that plug-in auxiliary fuel tank leading edge structure bird hits the signal of radome fairing center position；
Fig. 7 is that plug-in auxiliary fuel tank leading edge structure bird hits the signal of radome fairing upper position；
Fig. 8 is that plug-in auxiliary fuel tank leading edge structure bird hits the signal of the position of skins front edges I.
Numbering title in figure：1st, radome fairing；2nd, leading portion covering I；3rd, cushioning fender；4th, cock body；5th, plate nut；6th, leading portion
Covering II；7th, frame；8th, 90 ° of sunk screws of cross recess；9th, bird body 10, maximum gauge section 11, minimum thickness section
Specific embodiment
As shown in figure 1, the plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit, including radome fairing 1, cushioning fender 3, plug
Body 4, leading portion covering I 2 and leading portion covering II 6, radome fairing 1 are variable cross-section thick-walled structure, and minimum thickness section 11 is located at radome fairing
Edge, it is 5mm~10mm, maximum gauge section 10 is located at radome fairing center, is 10mm~30mm, minimum thickness and maximum
It is circular arc gradual transition between thickness x cross sectional；Leading portion covering I 2 is connected with radome fairing 1 by connector, ensure leading portion covering I 2 with
The outer surface of radome fairing 1 assembling jump is less than 1mm；Cushioning fender 3 is located at behind radome fairing 1, by being welded to connect in leading portion covering I
On 2；Cock body 4 is welded in the hole among cushioning fender 3, for separating leading portion covering I 2 and radome fairing 1, make leading portion covering I 2 and
Fuel oil in its rear structure cannot be introduced into radome fairing 1.
Specific design example, as shown in FIG. 1 to 3, plug-in auxiliary fuel tank leading edge structure is by radome fairing 1, leading portion covering I 2, preceding
90 ° of section covering II 6, cushioning fender 3, cock body 4, plate nut 5 and cross recess sunk screws 8 form.Dome material can be selected
2A12-T4；3A21-O, thickness 2.5mm can be selected in the material of leading portion covering I 2；The material of leading portion covering II 6 is 5A02-O, and thickness is
2mm；The material of cushioning fender 3 is 5A06-O, thickness 2mm；Cock body material is 5A06-O.
As shown in figure 5, radome fairing 1 is variable cross-section thick-walled structure, minimum thickness section 11 is located at rectification shroud rim, is 5mm
~10mm, maximum gauge section 10 are located at radome fairing center, are 10mm~30mm, minimum thickness and maximum gauge section it
Between be circular arc gradual transition, the edge chamfer of radome fairing 1.
During assembling, 12 plate nuts 5 are uniformly arranged on leading portion covering I 2, and cushioning fender 3 passes through with leading portion covering I 2
Spot welding is connected with argon arc welding, and leading portion covering I 2 is connected with leading portion covering II 6 by argon arc welding, and cock body 4 passes through argon with cushioning fender 3
Arc-welding is connected, and radome fairing 1 is connected with leading portion covering I 2 by 12 cross recesses, 90 ° of sunk screws.
Present application contemplates the hydrodynamics behavior that bird body is shown in knockout process, it is contemplated that three kinds of impingement positions,
As shown in Figure 6 to 8.The overall length of bird body 9 and diameter ratio are 2 in figure, the model both ends of bird body 9 be it is hemispherical, centre be it is cylindric,
Its numerical computation method is represented using SPH particles.The mass of bird body 9 is 1.8kg, stroke speed 116.7m/s.
When bird body 9 hits 1 center of radome fairing, the profile to be smoothly transitted by the class hemispherical surface of radome fairing 1 and change
The structure design of section heavy wall, radome fairing 1 is set to be fully able to withstand the shock of bird body without being destroyed, the fragment of bird body 9
Slipped from the outer surface of radome fairing 1 and leading portion covering I 2.
When bird body 9 hits 1 top of radome fairing, bird body 9 is in contact with the top on the top of radome fairing 1 and skins front edges I, leads to
The profile and the structure design of variable cross-section heavy wall that the arc surface of over commutation cover 1 smoothly transits, make radome fairing be fully able to withstand bird
The shock of body 9 the anterior design by lower limit and crimp edge of leading portion covering I 2, ensure that itself and radome fairing without being destroyed
The smooth continuous profile being consistent afterwards with rectification cover outer surface, bird hit rear leading portion covering I 2 only with the junction of radome fairing 1
Thereafter occurs small depression at covering, this depressed deformation does not influence the safety of aircraft flight.Bird body 9 passes through radome fairing 1, leading portion
The outer surface of covering I 2 and leading portion covering II 6 is slipped.
When bird body 9 is without radome fairing 1, when directly hitting leading portion covering I 2 and leading portion covering II 6, leading portion covering I 2 is with before
Locally there is small depression in section covering II 6 external upper, and this depressed deformation does not influence the safety of aircraft flight.Bird body 9 passes through
The outer surface of leading portion covering I 2 and leading portion covering II 6 is slipped.
The position of centre of gravity of auxiliary fuel tank can also be adjusted by changing the length dimension of cock body 4；The He of skins front edges I 2
Leading portion covering II 6 may be designed to different thickness, be connected together by welding, play loss of weight effect.
Claims (3)
1. the plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit, including radome fairing, cushioning fender, cock body, the and of leading portion covering I
Leading portion covering II, it is characterised in that radome fairing is variable cross-section thick-walled structure, and minimum thickness section is located at rectification shroud rim, is 5mm
~10mm, maximum gauge section are located at radome fairing center, are 10mm~30mm, between minimum thickness and maximum gauge section
For circular arc gradual transition；Leading portion covering I is connected on radome fairing by connector, ensures leading portion covering I and rectification cover outer surface
Assembling jump is less than 1mm；Cushioning fender is located at behind radome fairing, and by being welded to connect on leading portion covering I, cock body is welded on slow
Rush in the hole among baffle plate, for separating leading portion covering I and radome fairing, make fuel oil in leading portion covering I and its rear structure without
Method enters radome fairing.
2. the plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird according to claim 1 is hit, it is characterised in that can pass through
Change the position of centre of gravity of the length adjustment auxiliary fuel tank of cock body.
3. the plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird according to claim 1 is hit, it is characterised in that leading portion covers
Skin I and leading portion covering II are designed to different thickness, are connected together by welding, play loss of weight effect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510654377.3A CN105270641B (en) | 2015-10-10 | 2015-10-10 | The plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510654377.3A CN105270641B (en) | 2015-10-10 | 2015-10-10 | The plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105270641A CN105270641A (en) | 2016-01-27 |
| CN105270641B true CN105270641B (en) | 2018-01-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510654377.3A Active CN105270641B (en) | 2015-10-10 | 2015-10-10 | The plug-in auxiliary fuel tank leading edge structure of aircraft that a kind of anti-bird is hit |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10479517B2 (en) * | 2016-12-05 | 2019-11-19 | The Boeing Company | Composite fan cowl with a core having tailored thickness |
| CN108082505B (en) * | 2017-04-11 | 2024-05-10 | 空客(北京)工程技术中心有限公司 | Stop device, moving mechanism and aircraft |
| CN108945488B (en) * | 2017-05-23 | 2021-08-03 | 成都飞机工业（集团）有限责任公司 | Shape-preserving oil tank |
| CN108791814B (en) * | 2018-06-19 | 2020-02-04 | 吉林化工学院 | Aircraft radome fairing with impact resistance |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4172573A (en) * | 1977-12-22 | 1979-10-30 | Royal Industries, Inc. | Fuel tank |
| US4511105A (en) * | 1982-01-13 | 1985-04-16 | The United States Of America As Represented By The Secretary Of The Air Force | Compartmented, filament wound, one-piece aircraft fuel tanks |
| US5467889A (en) * | 1994-07-12 | 1995-11-21 | Aerotrans | Nestable elastic fuel tank and method for making same |
| CN202879798U (en) * | 2012-08-28 | 2013-04-17 | 中航工业三五一厂 | Plug-in auxiliary fuel oil tank for lightning protection airplanes |
| CN205044986U (en) * | 2015-10-10 | 2016-02-24 | 中航飞机股份有限公司西安飞机分公司 | External bellytank leading edge structure of aircraft that anti bird was hit |
-
2015
- 2015-10-10 CN CN201510654377.3A patent/CN105270641B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4172573A (en) * | 1977-12-22 | 1979-10-30 | Royal Industries, Inc. | Fuel tank |
| US4511105A (en) * | 1982-01-13 | 1985-04-16 | The United States Of America As Represented By The Secretary Of The Air Force | Compartmented, filament wound, one-piece aircraft fuel tanks |
| US5467889A (en) * | 1994-07-12 | 1995-11-21 | Aerotrans | Nestable elastic fuel tank and method for making same |
| CN202879798U (en) * | 2012-08-28 | 2013-04-17 | 中航工业三五一厂 | Plug-in auxiliary fuel oil tank for lightning protection airplanes |
| CN205044986U (en) * | 2015-10-10 | 2016-02-24 | 中航飞机股份有限公司西安飞机分公司 | External bellytank leading edge structure of aircraft that anti bird was hit |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105270641A (en) | 2016-01-27 |
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Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
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Effective date of registration: 20210610 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |