CN204775992U - Rib structure - Google Patents
Rib structure Download PDFInfo
- Publication number
- CN204775992U CN204775992U CN201520434718.1U CN201520434718U CN204775992U CN 204775992 U CN204775992 U CN 204775992U CN 201520434718 U CN201520434718 U CN 201520434718U CN 204775992 U CN204775992 U CN 204775992U
- Authority
- CN
- China
- Prior art keywords
- edge strip
- web
- pillar
- rib structure
- rib
- 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.)
- Active
Links
Landscapes
- Rod-Shaped Construction Members (AREA)
Abstract
The utility model provides a rib structure belongs to aircraft structural design field, relates to airfoil structural design technique, and this rib structure passes through combined material shop layer and designs and an integrated forming, include web (4), connect edge strip (1), link up edge strip (2) and a plurality of pillar (3), pillar (3) parallel parallel configuration, web (4) are located in adjacent pillar (3), and web (4) are gone up and are opened web plate hole (5), link up edge strip (2) perpendicular to pillar (3) and run through pillar (3) and web (4), it is equipped with and is used for connecting wall joining of plates edge strip 1 to link up edge strip (2) outside. This rib structure design simple process, production efficiency height make aircraft rib structure's biography power continuous, direct simultaneously.
Description
Technical field
The utility model belongs to field of airplane structure, is specifically related to a kind of for the rib structure in aircraft wing box.
Background technology
Rib, as the main dimension shape of wing box, supporting construction, bears in wing box inside and transmits local load.Existing aircraft rib structure is generally metal riveting or integrated machine adds structure, and composite material rib mostly generally also is combination rib structure.Metal riveting and combination rib are made up of edge strip, web and pillar, and web does some lightening holes, pillar is crisscross to be connected on web, plays the effect increasing rib rigidity.The problems such as it is low that this combination rib structure exists production efficiency, and fastener assembling is complicated, fatigue property is low; Integrated machine adds rib can reach the same effect that assembling is simple, production efficiency is high with RTM rib, but the maximum inferior position that integrated machine adds rib is the degree of utilization problem of its weight cost and material, and the Occupation coefficient that integrated machine adds part woollen generally only can reach about 10% of material.
Utility model content
The purpose of this utility model is to solve above-mentioned deficiency of the prior art, solves combination rib efficiency of assembling low, and fastener connects complicated and that fatigue property is low problem; Solve integrated machine and add the problem that rib weight is large and stock utilization is low, the shaping of the utility model RTM rib structure improves overall aircraft technological level plays facilitation.
The purpose of this utility model is achieved through the following technical solutions: a kind of rib structure, comprise web, connect edge strip, through edge strip and several pillars, described pillar parallel side-by-side arrangement, described web is positioned at described adjacent struts, and web hole is opened on described web, achieve the assembling of box intersegmental part system part and check.Described through edge strip is perpendicular to pillar and run through pillar and web, is provided with the connection edge strip for connecting wallboard outside described through edge strip, makes the power transmission of aircraft rib structure continuously, directly.Described web, connection edge strip, through edge strip, pillar and web hole are all by composite plys design also monolithic molding.
Preferably, described rib structure is RTM monolithic molding, achieves obvious weight loss effect.
In above-mentioned either a program preferably, integrally formed reinforcement boss is provided with around described web hole.
In above-mentioned either a program preferably, described connection edge strip is provided with long purlin breach.
The utility model advantageously carries high with posting efficiency, that fastener assembling quantity is few, technique is simple, production efficiency is high advantage; Make the power transmission of aircraft rib structure continuously, directly simultaneously; And achieve the assembling of box intersegmental part system part by the design of web holes and check; The overall rib of composite material RTM is shaped and achieves obvious weight loss effect, reaches the loss of weight effect of 30% relative to integrated machine ribbing.
Accompanying drawing explanation
Fig. 1 is the structural representation of the preferred embodiment according to rib structure of the present utility model.
Fig. 2 is the web hole generalized section embodiment illustrated in fig. 1 according to rib structure of the present utility model.
Reference numeral:
1-connection edge strip, the through edge strip of 2-, 3-pillar, 4-web, 5-web hole, 6-strengthen boss, 7-long purlin breach.
Detailed description of the invention
In order to understand the rib structure according to the utility model scheme better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to rib structure of the present utility model.
As shown in Figure 1, a kind of rib structure, comprise web 4, connect edge strip 1, through edge strip 2 and several pillars 3, described pillar 3 parallel side-by-side arrangement, the multiple pillar 3 of vertical layout on rib web 4, the effect of pillar 3 is the top compressive load of bearing wallboard on the one hand, divides rib web into multiple grid on the other hand, improves the stability of local ribs web; Pillar 3 and through edge strip 2 surround polylith web 4, it is mainly with the form transmitted load of shearing flow, thus, described web 4 is positioned at described adjacent struts 3, simultaneously, web hole 5 opened by described web 4, as shown in Figure 2, this accompanying drawing midfield plate hole 5 is represented by dotted lines, and web hole 5 is after monolithic molding, be shaped by machine up, achieve like this system part in box section by, install and check.In the present embodiment, described through edge strip 2 is perpendicular to pillar 3 and run through pillar 3 and web 4, and through edge strip 2 is the architectural features from the through back rest of front-axle beam on whole rib, and the part axial load of the back rest to front-axle beam is transmitted in its effect.Be provided with the connection edge strip 1 for connecting wallboard outside described through edge strip 2, described web 4, connection edge strip 1, through edge strip 2, pillar 3 and web hole 5 are all by composite plys design also monolithic molding.
It should be noted that, in the present embodiment, described rib structure is RTM monolithic molding.
As the present embodiment one preferred embodiment, be provided with integrally formed reinforcement boss 6 around described web hole 5, limit, hole boss 6 and web 4 are integral layer pressing formations, this ensure that effective diffusion of Kong Bian local load, limit, hole local failure can not be there is, high relative to the intensity of regelate.
In the present embodiment, described connection edge strip 1 is provided with long purlin breach 7, connect the connection that edge strip 1 mainly ensures rib and wallboard, connect edge strip 1 to be connected with wallboard by fastener between two long purlin breach 7, connect edge strip 1 and add long purlin breach 7 in long purlin by place's machine, on guarantee Material Stiffened Panel, long purlin is through.
More than be described in detail in conjunction with specific embodiment of the utility model, but be not to restriction of the present utility model, everyly according to technical spirit of the present utility model, technical scope of the present utility model is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of pipeline note of the present utility model, oil drainage structure technical scheme.
Claims (4)
1. a rib structure, it is characterized in that: comprise web (4), connect edge strip (1), through edge strip (2) and several pillars (3), described pillar (3) parallel side-by-side is arranged, described web (4) is positioned at described adjacent struts (3), and web hole (5) is opened on described web (4), described through edge strip (2) is perpendicular to pillar (3) and run through pillar (3) and web (4), described through edge strip (2) outside is provided with the connection edge strip (1) for connecting wallboard, described web (4), connect edge strip (1), through edge strip (2), pillar (3) and web hole (5) are all by composite plys design also monolithic molding.
2. rib structure as claimed in claim 1, is characterized in that: described rib structure is RTM monolithic molding.
3. rib structure as claimed in claim 1, is characterized in that: described web hole (5) is provided with integrally formed reinforcement boss (6) around.
4. rib structure as claimed in claim 1, is characterized in that: described connection edge strip (1) is provided with long purlin breach (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520434718.1U CN204775992U (en) | 2015-06-23 | 2015-06-23 | Rib structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520434718.1U CN204775992U (en) | 2015-06-23 | 2015-06-23 | Rib structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204775992U true CN204775992U (en) | 2015-11-18 |
Family
ID=54516094
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520434718.1U Active CN204775992U (en) | 2015-06-23 | 2015-06-23 | Rib structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204775992U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109606625A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of big height rib structure |
| CN109625245A (en) * | 2018-11-02 | 2019-04-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general-purpose aircraft composite material rudder and production method |
-
2015
- 2015-06-23 CN CN201520434718.1U patent/CN204775992U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109625245A (en) * | 2018-11-02 | 2019-04-16 | 中国航空工业集团公司西安飞机设计研究所 | A kind of general-purpose aircraft composite material rudder and production method |
| CN109606625A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of big height rib structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106114819A (en) | A kind of composite airfoil structure | |
| CN205475694U (en) | Assembled steel construction house | |
| CN204775992U (en) | Rib structure | |
| CN102196963A (en) | Fuselage structure for the combined fastening of an insulation mattress and devices, and aircraft including such a structure | |
| CN102514708A (en) | Integral central wing box made of composite materials | |
| CN103832578A (en) | Modular structural assembly | |
| CN105539812A (en) | Aircraft wing spar butting joint | |
| CN100577512C (en) | Joint of body and wing of large-sized civil aeroplane | |
| CN205906205U (en) | Combined material covers body structure | |
| CN204871587U (en) | Aircraft combined material adds muscle wallboard structure | |
| CN103192979B (en) | Aircraft tail beam transition section structure | |
| CN204775991U (en) | Flivver panel beating combination spar structure | |
| CN211519868U (en) | Whole oil tank of aircraft wing box section formula | |
| CN205906207U (en) | Cargo airplane horizontal stabilizer box segment structure | |
| CN205610556U (en) | Two glass solar photovoltaic board reinforced structures | |
| CN208168177U (en) | A kind of double-layer heat insulation steel roof structure containing hangar system | |
| CN204297055U (en) | A kind of whole wing spar structure | |
| CN205203352U (en) | Close frame wallboard of longeron | |
| CN207609507U (en) | Sectional-type blade and wind power generating set | |
| CN203612196U (en) | Wing rib | |
| CN207191395U (en) | A kind of high-mechanic joint | |
| CN205712719U (en) | A kind of clean board building toilet | |
| CN202144417U (en) | Novel elevator cab wall structure | |
| CN221024136U (en) | Detachable composite aircraft engine cabin upper wall | |
| CN204658279U (en) | A kind of fusion joining disk fixed frame |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |