CN205906193U - Aircraft area muscle combined material sphere frame structure - Google Patents
Aircraft area muscle combined material sphere frame structure Download PDFInfo
- Publication number
- CN205906193U CN205906193U CN201620781761.XU CN201620781761U CN205906193U CN 205906193 U CN205906193 U CN 205906193U CN 201620781761 U CN201620781761 U CN 201620781761U CN 205906193 U CN205906193 U CN 205906193U
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- CN
- China
- Prior art keywords
- hat
- shape
- combined material
- covering
- aircraft
- 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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Links
- 239000000463 material Substances 0.000 title claims abstract description 10
- 210000003205 muscle Anatomy 0.000 title abstract description 5
- 239000006260 foam Substances 0.000 claims abstract description 14
- 239000002131 composite material Substances 0.000 claims description 20
- 230000002787 reinforcement Effects 0.000 claims description 18
- 239000011208 reinforced composite material Substances 0.000 claims description 14
- 239000008188 pellet Substances 0.000 claims 1
- 239000002023 wood Substances 0.000 claims 1
- 238000005260 corrosion Methods 0.000 abstract description 2
- 239000010985 leather Substances 0.000 abstract 4
- 238000005728 strengthening Methods 0.000 abstract 3
- 239000011162 core material Substances 0.000 description 7
- 150000001875 compounds Chemical class 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
Landscapes
- Laminated Bodies (AREA)
Abstract
The utility model provides an aircraft area muscle combined material sphere frame structure for link to each other with fuselage panel, including combined material leather case (1), interfacing part (2), shape for hat strengthening rib (3), foam core (4), combined material leather case (1) be the shell structure of spherical crown appearance, evenly arranges 8 shape for hat strengthening rib (3) along radial direction on combined material leather case (1) convex surface or concave surface, and it has foam core (4) to fill in shape for hat strengthening rib (3), and leather case (1) is through interfacing part (2) and fuselage panel to linking. The utility model provides an aircraft area muscle combined material sphere frame structure can effectively improve the availability factor of structure, further improve the fatigue performance can and anti -corrosion performance, the atress is more equitable, reduces aircraft structure weight, and is with low costs.
Description
Technical field
The utility model belongs to field of airplane structure, particularly pressure bulkhead structure technology and in particular to aircraft band muscle
Compound material ball surface frame structure.
Background technology
Pressure bulkhead on aircraft, respectively be located at head and rear body, be the interface of aircraft air-tight section and non-hermetically sealed area.
Pressure bulkhead bears the gas pressure loads of engine room inside, provides the air pressure environment of safety and comfort for passenger.The pressure bulkhead of head is also
Installation site can be provided for radar, the pressure bulkhead of afterbody can be system pipeline and wire provides passage and fixing point.Traditional gas
Close mount structure, typically adopts the flat board pressure bulkhead of metal material, and flat board pressure bulkhead is adopted to access node with the intersection of fuselage wallboard
Structure.Often weight is larger for such pressure bulkhead organization plan, and stress is not reasonable, and reduces the pay(useful) load of aircraft.
Utility model content
The purpose of this utility model is to provide a kind of aircraft band rib reinforced composite material sphere mount structure, reduces airtight mount structure
Weight, improve stressing conditions.
The purpose of this utility model is achieved through the following technical solutions: a kind of aircraft band rib reinforced composite material sphere mount structure,
For being connected with fuselage wallboard, including composite covering, interfacing part, shape for hat reinforcement, foam core, described composite covering
For the shell structure of spherical crown profile, described composite covering radially respectively arranges a plurality of described shape for hat reinforcement,
It is filled with described foam core, described composite covering is by described interfacing part and fuselage wallboard pair in described shape for hat reinforcement
Even.
Preferably, 8 described shape for hat reinforcements are evenly arranged on the convex surface of described composite covering.
Preferably, 8 described shape for hat reinforcements are evenly arranged on the concave surface of described composite covering.
Preferably, described foam core material is pmi foam.
A kind of aircraft having the beneficial effects that with rib reinforced composite material sphere mount structure provided by the utility model, Ke Yiyou
Effect improves the service efficiency of structure, and stress is more reasonable, reduces aero-structure weight, low cost, the use of composite enters one
Step improves fatigue behaviour and corrosion resistance, reduces the use of sphere frame connector, reduces the damage that connector brings to structure
The probability producing with crackle.
Brief description
Fig. 1 is the top view with the composite covering in rib reinforced composite material sphere mount structure for the aircraft of the present utility model；
The aircraft of the present utility model for Fig. 1 for the Fig. 2 is with the shape for hat reinforcement in rib reinforced composite material sphere mount structure in convex surface
A-a direction sectional view；
The aircraft of the present utility model for Fig. 1 for the Fig. 3 is with the shape for hat reinforcement in rib reinforced composite material sphere mount structure in concave surface
A-a direction sectional view；
Fig. 4 is aircraft band rib reinforced composite material sphere mount structure schematic diagram of the present utility model.
Reference:
1- composite covering, 2- interfacing part, 3- shape for hat reinforcement, 4- foam core.
Specific embodiment
For making purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, is further described in more detail to the technical scheme in the utility model embodiment.In the accompanying drawings, ad initio
To the element that same or similar label represents same or similar element or has same or like function eventually.Described reality
Applying example is a part of embodiment of the present invention, rather than whole embodiments.Embodiment below with reference to Description of Drawings is to show
Example property it is intended to be used for explaining the utility model, and it is not intended that to restriction of the present utility model.Based in the utility model
Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of not making creative work,
Broadly fall into the scope of the utility model protection.
Below in conjunction with the accompanying drawings the utility model aircraft band rib reinforced composite material sphere mount structure is described in further details.
As shown in Figure 1 and Figure 4, aircraft band rib reinforced composite material sphere mount structure, for being connected with fuselage wallboard, including compound
Material covering 1, interfacing part 2, shape for hat reinforcement 3, foam core 4.Composite covering 1 is the shell structure of spherical crown profile, is combined
Material covering 1 is a big monoblock, laying on spherical die, and by adopting composite, the number of parts of sphere frame subtracts
Few, manufacture and assembling process can be simplified, the use being simultaneously connected with part also can reduce, and reduces the damage to covering 1, reduce fatigue and split
The probability that line produces, in order to increase rigidity and the stability of covering 1, on composite covering 1, radially each arrangement is many
Shape for hat reinforcement 3 described in bar, prioritizing selection is to be evenly arranged 8 shape for hat reinforcements 3 on the convex surface of composite covering 1,
Or 8 shape for hat reinforcements 3 are evenly arranged on composite covering 1 concave surface, as shown in Figures 2 and 3.Covering 1 and shape for hat add
Strong muscle 3 passes through filled and process core 4 in secondary curing molding, and shape for hat reinforcement 3, this foam core 4 prioritizing selection pmi foam.
Covering 1 passes through interfacing part 2 with fuselage wallboard to even, to ensure the air-tightness of the airtight cabin structure of aircraft with this.
In terms of mechanical characteristic, hemisphere made by sphere frame, and that is, spherical radius is consistent with fuselage radius, now uniform on deckle board
Tension just all, directly passes to body shell covering.Sphere frame, under cabin pressure effect, covering is everywhere open to answer
Power, compared with traditional flat board pressure bulkhead, weight is lighter, and stress is more reasonable.
The above, specific embodiment only of the present utility model, but protection domain of the present utility model does not limit to
In this, any those familiar with the art in the technical scope that the utility model discloses, the change that can readily occur in
Change or replace, all should cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with described
Scope of the claims is defined.
Claims (4)
1. a kind of aircraft band rib reinforced composite material sphere mount structure, for being connected with fuselage wallboard it is characterised in that including composite wood
Pellet skin (1), interfacing part (2), shape for hat reinforcement (3), foam core (4), described composite covering (1) is the shell of spherical crown profile
Body structure, radially respectively arranges a plurality of described shape for hat reinforcement (3), described shape for hat on described composite covering (1)
It is filled with described foam core (4), described composite covering (1) is by described interfacing part (2) and fuselage wallboard in reinforcement (3)
To even.
2. aircraft band rib reinforced composite material sphere mount structure according to claim 1 is it is characterised in that in described composite
8 described shape for hat reinforcements (3) are evenly arranged on the convex surface of covering (1).
3. aircraft band rib reinforced composite material sphere mount structure according to claim 1 is it is characterised in that in described composite
8 described shape for hat reinforcements (3) are evenly arranged on the concave surface of covering (1).
4. aircraft band rib reinforced composite material sphere mount structure according to claim 1 is it is characterised in that described foam core (4)
Material is pmi foam.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620781761.XU CN205906193U (en) | 2016-07-22 | 2016-07-22 | Aircraft area muscle combined material sphere frame structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620781761.XU CN205906193U (en) | 2016-07-22 | 2016-07-22 | Aircraft area muscle combined material sphere frame structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205906193U true CN205906193U (en) | 2017-01-25 |
Family
ID=57805105
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620781761.XU Active CN205906193U (en) | 2016-07-22 | 2016-07-22 | Aircraft area muscle combined material sphere frame structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205906193U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107128475A (en) * | 2017-05-10 | 2017-09-05 | 江苏美龙振华科技有限公司 | A kind of plate composite pressure bulkhead |
| WO2021014033A1 (en) * | 2019-07-24 | 2021-01-28 | CiTD ENGINEERING & TECHNOLOGIES SL | Pressure bulkhead |
-
2016
- 2016-07-22 CN CN201620781761.XU patent/CN205906193U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107128475A (en) * | 2017-05-10 | 2017-09-05 | 江苏美龙振华科技有限公司 | A kind of plate composite pressure bulkhead |
| CN107128475B (en) * | 2017-05-10 | 2023-08-11 | 江苏美龙振华科技有限公司 | Flat composite pressure bulkhead |
| WO2021014033A1 (en) * | 2019-07-24 | 2021-01-28 | CiTD ENGINEERING & TECHNOLOGIES SL | Pressure bulkhead |
| EP3851370A4 (en) * | 2019-07-24 | 2022-08-03 | CITD Engineering & Technologies SL | Pressure bulkhead |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |