CN109592009A - A kind of aircraft abdomeinal fin structure - Google Patents
A kind of aircraft abdomeinal fin structure Download PDFInfo
- Publication number
- CN109592009A CN109592009A CN201710938807.3A CN201710938807A CN109592009A CN 109592009 A CN109592009 A CN 109592009A CN 201710938807 A CN201710938807 A CN 201710938807A CN 109592009 A CN109592009 A CN 109592009A
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- CN
- China
- Prior art keywords
- aircraft
- fin structure
- abdomeinal fin
- covering
- layers
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The present invention provides a kind of aircraft abdomeinal fin structure, it is connected by L-type material with aircraft fuselage structure, including two layers of covering (6) and multiple reinforcement partitions (3), wherein every layer of covering (6) is laminated by one layer of exterior skin (1) and one layer of inside panel (2), two layers of covering (6) is bonded the component that the V-shaped course section of a vertical section is in shuttle shape, and multiple reinforcement partitions (3) are along course arranged for interval in the component inside；Two layers of covering (6) and multiple reinforcement partitions (3) are made up of four pieces of titanium alloy TC 4 thin plate superplastic formings/diffusion technique integrated molding.Aircraft abdomeinal fin structure provided by the present invention, (SPF/DB) process is connected using titanium alloy superplastic forming/diffusion, abdomeinal fin structure only uses one set of die one-pass molding, improve the integrality of structure, manufacturing cost is substantially reduced, the manufacturing cycle is reduced, reduces workload, structure precision is high, light-weight.
Description
Technical field
The invention belongs to field of airplane structure, and in particular to a kind of aircraft abdomeinal fin structure.
Background technique
Generally being disposed with abdomeinal fin structure in aircraft rear body abdomen (has single abdomeinal fin immediately below being arranged in and is arranged in two sides
Double abdomeinal fins point), the purpose is to improve the shipping-direction stability of aircraft, compensation vertical fin area is insufficient, while also can be under fuselage
Portion's air-flow plays guide functions, at the same while preventing from taking off, landing surprisingly wipe damage to airframe structure.
Traditional abdomeinal fin structure is generally aluminum alloy outer cover and the riveting of partition stringer forms, i.e. aluminum alloy combination part, and zero
Number of packages mesh is various, and connection is complicated, and weight weight structure low efficiency, installation workload is big, and manufacturing cost is high, and the period is long.As one kind
Similar airfoil structure, side projection area is big, and the space that two pieces of coverings surround is narrow, and connection construction channel accessibility is poor, connects non-
Often difficult, quality of connection is unreliable, is easy to appear situations such as overproof and in-flight rivet falls off.
Summary of the invention
The purpose of the present invention is to provide a kind of aircraft abdomeinal fin structure, at least one for overcoming or alleviated by the prior art is above-mentioned
Defect.
The purpose of the present invention is achieved through the following technical solutions: a kind of aircraft abdomeinal fin structure passes through L-type material and airframe
Structure is connected, including two layers of covering and multiple reinforcement partitions, wherein every layer of covering is by one layer of exterior skin and one layer of inside panel
It is laminated, two layers of covering is bonded the component that the V-shaped course section of a vertical section is in shuttle shape, and multiple reinforcement partitions are along boat
To arranged for interval in the component inside；Two layers of covering and multiple reinforcement partitions by four pieces of titanium alloy TC 4 thin plate superplastic formings/
Diffusion technique integrated molding is made.
Preferably, four pieces of titanium alloy TC 4 thin plates stack gradually placement, are used for wherein being located in the middle two pieces of thin plates
Form two inside panels, positioned at outside two pieces of thin plates for form two exterior skins, the exterior skin being placed adjacent with
One inside panel is bonded the covering, and two inside panels are bonded the reinforcement partition.
Preferably, the reinforcement partition is arranged 18.
Preferably, positioned at aircraft abdomeinal fin structure course both ends leading edge and rear vertical bottom directly by two layers outside
Covering is bonded, so that aircraft two position when surprisingly wiping ground is first damaged and absorbs portion of energy.
Preferably, the lamella thickness for forming the inside panel is δ 1.0mm, for forming the exterior skin
Lamella thickness is δ 0.7mm, and the aircraft abdomeinal fin structure course overall length after molding is 2315mm, and vertical maximum height is
840mm, side projection area are 1.57m2, the skin thickness is δ 1.2mm, and the reinforcement partition thickness is 0.8mm, and two add
The spacing of strong partition room is 110~130mm, and aircraft abdomeinal fin structure V-shaped root maximum gauge is 72mm, front and rear edge and lower edge
The R value at place is 1.2mm.
Preferably, the aircraft abdomeinal fin structure outer wall surface carries out taper chemistry milling from top to bottom vertically to mitigate
Construction weight.
A kind of beneficial effect of aircraft abdomeinal fin structure provided by the present invention is, using titanium alloy superplastic forming/diffusion
(SPF/DB) process is connected, abdomeinal fin structure only uses one set of die one-pass molding, improves the integrality of structure, substantially reduces system
This is caused, the manufacturing cycle is reduced, reduces workload, structure precision is high, light-weight；Opposite alloy riveting composite structures, the thin-walled
Titanium alloy hollow structure obtains about 20% loss of weight benefit；The structural member manufactured with this technique, the physics of material, chemically
It can be essentially identical with the performance of raw material.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of aircraft abdomeinal fin structure of the present invention；
Fig. 2 is aircraft abdomeinal fin structure of the present invention along course cross-sectional view；
Fig. 3 is the scheme of installation of aircraft abdomeinal fin structure of the present invention；
Fig. 4 is the first step schematic diagram in aircraft abdomeinal fin structure fabrication process of the present invention；
Fig. 5 is the second step schematic diagram in aircraft abdomeinal fin structure fabrication process of the present invention；
Fig. 6 is the third step schematic diagram in aircraft abdomeinal fin structure fabrication process of the present invention；
Fig. 7 is the 4th step schematic diagram in aircraft abdomeinal fin structure fabrication process of the present invention；
Fig. 8 is the 5th step schematic diagram in aircraft abdomeinal fin structure fabrication process of the present invention；
Fig. 9 is the 6th step schematic diagram in aircraft abdomeinal fin structure fabrication process of the present invention.
Appended drawing reference:
1- exterior skin, 2- inside panel, 3- reinforce partition, 4- leading edge, 5- rear, 6- covering.
Specific embodiment
To keep the purposes, technical schemes and advantages of the invention implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the present invention
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall within the protection scope of the present invention.
Aircraft abdomeinal fin structure of the invention is described in further details with reference to the accompanying drawing.
As shown in Figure 1, a kind of aircraft abdomeinal fin structure, including two layers of covering 6 and multiple reinforcement partitions 3, wherein every layer of illiteracy
Skin 6 is laminated by one layer of exterior skin 1 and one layer of inside panel 2, and two layers of covering 6 is bonded the V-shaped course of a vertical section
Section is in the component of shuttle shape, and multiple reinforcements partitions 3 in the component inside, two layers of covering 6 and multiple add along course arranged for interval
Strong partition 3 is made up of four pieces of titanium alloy TC 4 thin plate superplastic formings/diffusion technique integrated molding.
Abdomeinal fin forming process is as shown in Fig. 4 to 9.Four pieces of titanium alloy TC 4 thin plates are stacked gradually into placement (see Fig. 4) first,
Combination Welding, there are two the blank pocket of outer layer air cavity and an internal layer air cavity, is used at tool wherein being located in the middle two pieces of thin plates
Two inside panels 2 are formed, two pieces of thin plates positioned at outside reserve ectonexine air inlet mouth of pipe, shaping for forming two exterior skins 1
At a temperature of the control such as ventilated (high pressure argon gas), be vented to ectonexine air cavity respectively, that is, be mainly " exterior skin superplastic forming
Diffusion connection (see Fig. 6) → inside panel superplastic forming (see Fig. 7 and Fig. 8) → interior exterior skin diffusion connection of (see Fig. 5) → inside panel
Four work steps of (see Fig. 9) " are completed in a thermal cycle.The exterior skin 1 being placed adjacent after the completion is combined structure with an inside panel 2
At covering 6, two inside panels 2, which are bonded, reinforces partition 3, as shown in Figure 2.The outer dimension of abdomeinal fin by mold type chamber guarantee,
The position for reinforcing partition 3 is formed according to the only solder flux arrangement of inside panel 2.
Weak link, the area are designed at the leading edge 4 at aircraft abdomeinal fin structure course both ends and the vertical bottom of rear 5 simultaneously
Domain is directly bonded by two layers of exterior skin 1, without inside panel 2 and reinforces partition 3, as shown in Figure 1, so that in unexpected feelings
Condition, which is got off the plane, first damages and absorbs portion of energy at weak link when wiping ground, avoid the damage of abdomeinal fin Yu fuselage junction as far as possible.
According to the rule that abdomeinal fin stress level becomes larger from lower edge to root, abdomeinal fin outer wall is milled using taper chemistry
It cuts, improves the Thickness Distribution of component, mitigate construction weight to greatest extent.
Finally, abdomeinal fin is connected by two L-type materials with fuselage, and L-type material uses steel rivet to connect with abdomeinal fin respectively, then uses spiral shell
L-type material is connected to fuselage lower wall by bolt, and arrangement reinforcer is corresponded to inside siding, and type of attachment is as shown in Figure 3.
Illustrate aircraft abdomeinal fin structure of the invention below by a specific embodiment.
As shown in Figure 1, aircraft abdomeinal fin structure course overall length is 2315mm, vertical maximum height is 840mm, side projection face
Product is 1.57m2, aircraft abdomeinal fin structure V-shaped root maximum gauge is 72mm, and the R value of front and rear edge and lower edge is
1.2mm.Situation is carried in conjunction with abdomeinal fin, arranges 18 reinforcement partitions 3 altogether, two spacing reinforced between partition 3 are 110~130mm.It should
Structure is made up of four pieces of titanium alloy TC 4 thin plates of superplastic forming/diffusion connection process, as needed in forming
The lamella thickness of covering 2 is δ 1.0mm, and the lamella thickness for forming exterior skin 1 is δ 0.7mm, and covering 6 after molding is thick
Degree is δ 1.2mm, and reinforcement 3 thickness of partition is 0.8mm.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
In the technical scope disclosed by the present invention, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of protection of the claims
It is quasi-.
Claims (6)
1. a kind of aircraft abdomeinal fin structure is connected by L-type material with aircraft fuselage structure, which is characterized in that including two layers of covering (6)
And multiple reinforcement partitions (3), wherein every layer of covering (6) is laminated by one layer of exterior skin (1) and one layer of inside panel (2),
Two layers of covering (6) is bonded the component that the V-shaped course section of a vertical section is in shuttle shape, and multiple reinforcement partitions (3) are along course
Arranged for interval is in the component inside；Two layers of covering (6) and multiple reinforcement partitions (3) pass through the super modeling of four pieces of titanium alloy TC 4 thin plates
Forming/diffusion technique integrated molding is made.
2. aircraft abdomeinal fin structure according to claim 1, which is characterized in that four pieces of titanium alloy TC 4 thin plates successively layer
Stack and set, wherein be located in the middle two pieces of thin plates for form two inside panels (2), positioned at outside two pieces of thin plates at
Exterior skin described in type two (1), the exterior skin (1) being placed adjacent and an inside panel (2) are bonded the covering (6), in two
Covering (2) is bonded the reinforcement partition (3).
3. aircraft abdomeinal fin structure according to claim 2, which is characterized in that the reinforcement partition (3) is arranged 18.
4. aircraft abdomeinal fin structure according to claim 3, which is characterized in that before the both ends of aircraft abdomeinal fin structure course
Edge (4) and the vertical bottom of rear (5) are directly bonded by two layers of exterior skin (1), so that aircraft should when surprisingly wiping ground
Two positions are first damaged and absorb portion of energy.
5. aircraft abdomeinal fin structure according to claim 4, which is characterized in that for forming the thin plate of the inside panel (2)
Thickness is δ 1.0mm, and the lamella thickness for forming the exterior skin (1) is δ 0.7mm, the aircraft abdomeinal fin after molding
Structure course overall length is 2315mm, and vertical maximum height is 840mm, and side projection area is 1.57m2, covering (6) thickness
It is δ 1.2mm, reinforcement partition (3) thickness is 0.8mm, and two spacing reinforced between partition (3) are 110~130mm, aircraft abdomen
Fin structure V-shaped root maximum gauge is 72mm, and the R value of front and rear edge and lower edge is 1.2mm.
6. aircraft abdomeinal fin structure according to claim 1, which is characterized in that the aircraft abdomeinal fin structure outer wall surface is along vertical
To progress taper chemistry milling from top to bottom to mitigate construction weight.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710938807.3A CN109592009A (en) | 2017-09-30 | 2017-09-30 | A kind of aircraft abdomeinal fin structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710938807.3A CN109592009A (en) | 2017-09-30 | 2017-09-30 | A kind of aircraft abdomeinal fin structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109592009A true CN109592009A (en) | 2019-04-09 |
Family
ID=65956737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710938807.3A Pending CN109592009A (en) | 2017-09-30 | 2017-09-30 | A kind of aircraft abdomeinal fin structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109592009A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112792152A (en) * | 2020-12-14 | 2021-05-14 | 北京航星机器制造有限公司 | Skin extrusion cold-pressing air-bulging forming method with active cooling channel |
| CN113997014A (en) * | 2021-10-29 | 2022-02-01 | 北京星航机电装备有限公司 | Integrated forming method for titanium alloy skin with mounting part |
| CN114571190A (en) * | 2022-03-08 | 2022-06-03 | 中国航空制造技术研究院 | SPF/DB hollow structure forming method |
-
2017
- 2017-09-30 CN CN201710938807.3A patent/CN109592009A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112792152A (en) * | 2020-12-14 | 2021-05-14 | 北京航星机器制造有限公司 | Skin extrusion cold-pressing air-bulging forming method with active cooling channel |
| CN113997014A (en) * | 2021-10-29 | 2022-02-01 | 北京星航机电装备有限公司 | Integrated forming method for titanium alloy skin with mounting part |
| CN114571190A (en) * | 2022-03-08 | 2022-06-03 | 中国航空制造技术研究院 | SPF/DB hollow structure forming method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190409 |
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| WD01 | Invention patent application deemed withdrawn after publication |