CN103625633A - Main bearing pillar for composite aerofoil wing box - Google Patents
Main bearing pillar for composite aerofoil wing box Download PDFInfo
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- CN103625633A CN103625633A CN201310374604.8A CN201310374604A CN103625633A CN 103625633 A CN103625633 A CN 103625633A CN 201310374604 A CN201310374604 A CN 201310374604A CN 103625633 A CN103625633 A CN 103625633A
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- pillar
- bearing pillar
- wing box
- composite material
- root segment
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Abstract
The invention belongs to the field of designing of airplane structures and specifically to a main bearing pillar used in the wing box of an airplane. The main bearing pillar is characterized by being composed of a basic section and two ends, wherein the cross section of the basic section of the pillar is square, the cross section of each of the two ends is in a groove shape, and the main bearing pillar is molded from an IB type 1-class 133-grade/YMS3101 composite through autoclave molding. The main bearing pillar provided by the invention has the beneficial effects of good designability, good processability and capacity of meeting same bearing requirements under the conditions of limited materials and weight.
Description
Technical field
The invention belongs to aeroplane structure design field, be specifically related to a kind of for the primary load bearing pillar in aircraft wing box.
Background technology
Inner at aircraft wing box, rib is comprised of web and pillar, does some lightening holes on web, and pillar is crisscross to be connected on web, plays the effect that increases rib rigidity.In general, pillar adopts hard ware, and cross sectional shape is " T " font, " L " type or grooved.Above-mentioned metal mainstay weight is large, and section moment of inertia is little, and pressurized characteristic is poor.
Summary of the invention
The object of the invention is: large in order to solve rib metal mainstay weight, section moment of inertia is little the problem that pressurized characteristic is poor and the new technical scheme that designs.
Technical scheme of the present invention is: a kind of composite material aerofoil wing box primary load bearing pillar, it is characterized in that, by root segment and two terminations, formed, pillar root segment cross sectional shape is " mouth " type, two ends cross sectional shape is grooved, adopt 133 grades/YMS3101 of I Type B 1 class composite material, the moulding of Autoclave forming mode.
The laying ratio of 0 ° of described pillar root segment, ± 45 °, 90 ° direction one-way tapes is respectively 30-60%, 60-30%, 10-40%.
The outside laying that increases of the two ends that is grooved in described cross section is thickeied.
Described laminated material is consistent with root segment, and laying and pillar two ends bond by cementation method.
The described rectangle and trapezium channel section degree of depth is 1/4-3/4 of root segment " mouth " type section depth.
The invention has the beneficial effects as follows: designability is good, processibility is good, at limited material and weight condition, is issued to identical load bearing requirements.
Accompanying drawing explanation
Fig. 1 is T-shape pillar schematic diagram
Fig. 2 is " L-type pillar schematic diagram
Fig. 3 is primary load bearing pillar figure
1, pillar root segment 2, strut end head
Fig. 4 is A-A cross-sectional view
Fig. 5 is B-B cross-sectional view
Fig. 6 is C-C cross-sectional view
Fig. 7 is flute profile termination notch depth dimensional characteristic schematic diagram
The specific embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
Primary load bearing pillar, is characterized in that, root segment and two terminations, consists of, and pillar root segment cross sectional shape is " mouth " type, and two ends cross sectional shape is grooved.
Described stay material is composite material---133 grades/YMS3101 of I Type B 1 class, adopt the moulding of Autoclave forming mode, and root segment and termination are Integratively paving, without tomography.
The laying ratio of 0 ° of described pillar root segment, ± 45 °, 90 ° direction one-way tapes is respectively 60%, 30%, 10%.
Described strut end head connects crushing strength requirement for guaranteeing fastener, local thickening, and thickening laying and root segment bond by cementation method, and thickening laying thickness is 2 times of basic layer thicknesses.
The described rectangle and trapezium channel section degree of depth is 2/3 of root segment " mouth " type section depth.
Claims (5)
1. a composite material aerofoil wing box primary load bearing pillar, is characterized in that, root segment and two terminations, consists of, pillar root segment cross sectional shape is " mouth " type, two ends cross sectional shape is grooved, adopts 133 grades/YMS3101 of I Type B 1 class composite material, the moulding of Autoclave forming mode.
2. composite material aerofoil wing box primary load bearing pillar according to claim 1 and 2, is characterized in that, the laying ratio of 0 ° of described pillar root segment, ± 45 °, 90 ° direction one-way tapes is respectively 30-60%, 60-30%, 10-40%.
3. composite material aerofoil wing box primary load bearing pillar according to claim 1, is characterized in that, the outside laying that increases of the two ends that is grooved in described cross section is thickeied.
4. composite material aerofoil wing box primary load bearing pillar according to claim 5, is characterized in that, described laminated material is consistent with root segment, and laying and pillar two ends bond by cementation method.
5. composite material aerofoil wing box primary load bearing pillar according to claim 1, is characterized in that, the described rectangle and trapezium channel section degree of depth is 1/4-3/4 of root segment " mouth " type section depth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310374604.8A CN103625633A (en) | 2013-08-23 | 2013-08-23 | Main bearing pillar for composite aerofoil wing box |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310374604.8A CN103625633A (en) | 2013-08-23 | 2013-08-23 | Main bearing pillar for composite aerofoil wing box |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103625633A true CN103625633A (en) | 2014-03-12 |
Family
ID=50207173
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310374604.8A Pending CN103625633A (en) | 2013-08-23 | 2013-08-23 | Main bearing pillar for composite aerofoil wing box |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103625633A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5735486A (en) * | 1995-08-11 | 1998-04-07 | Deutsche Forschungsanstalt Fur Luft-Und Raumfahrt E.V. | Aircraft wing |
| CN102372084A (en) * | 2010-07-08 | 2012-03-14 | 空中客车运营公司 | Method for realization of an aircraft structure and resulting structure |
| CN102514708A (en) * | 2011-10-26 | 2012-06-27 | 中国商用飞机有限责任公司 | Integral composite material central wing box |
| CN103003146A (en) * | 2010-07-09 | 2013-03-27 | 空中客车运营简化股份公司 | Method for producing a central wing box |
| CN203612196U (en) * | 2013-08-23 | 2014-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Wing rib |
-
2013
- 2013-08-23 CN CN201310374604.8A patent/CN103625633A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5735486A (en) * | 1995-08-11 | 1998-04-07 | Deutsche Forschungsanstalt Fur Luft-Und Raumfahrt E.V. | Aircraft wing |
| CN102372084A (en) * | 2010-07-08 | 2012-03-14 | 空中客车运营公司 | Method for realization of an aircraft structure and resulting structure |
| CN103003146A (en) * | 2010-07-09 | 2013-03-27 | 空中客车运营简化股份公司 | Method for producing a central wing box |
| CN102514708A (en) * | 2011-10-26 | 2012-06-27 | 中国商用飞机有限责任公司 | Integral composite material central wing box |
| CN203612196U (en) * | 2013-08-23 | 2014-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Wing rib |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140312 |