CN105620718A - Integrated spar crack resistant rib - Google Patents
Integrated spar crack resistant rib Download PDFInfo
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- CN105620718A CN105620718A CN201410589341.7A CN201410589341A CN105620718A CN 105620718 A CN105620718 A CN 105620718A CN 201410589341 A CN201410589341 A CN 201410589341A CN 105620718 A CN105620718 A CN 105620718A
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- rib
- spar
- crack arrest
- crack
- crack resistant
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Abstract
The invention discloses an integrated spar crack resistant rib. The crack resistant rib is arranged at the position 1/3 of the height of a spar. The width of the crack resistant rib is 1/3 of the width of a horizontal edge rib. Experiments show that the integrated spar crack resistant rib has the good damage tolerance characteristic, the integrated spar crack expansion speed is effectively reduced, and the parameter selection effect of the integrated spar crack resistant rib is optimal.
Description
Technical field
The invention belongs to field of airplane structure, particularly to a kind of whole wing spar crack arrest rib.
Background technology
Wing spar is longitudinal stress part important in wing structure, and it bears the shearing of wing, moment of flexure, and bears the moment of torsion of wing together with the closed chamber of wallboard composition, and large aircraft wing spar is frequently with whole wing spar.
At present, the domestic Damage Tolerance Analysis to composite spar structure has had a set of more complete method, but study relatively fewer in whole wing spar Damage Tolerance Analysis, lack the guidance method to the design of whole wing spar structural damage extended attribute, for the design of whole wing spar web crack arrest rib, especially parameter is chosen or blank. External ripe type cannot obtain in open source literature about the design of whole wing spar crack arrest rib.
Summary of the invention
The technical problem to be solved in the present invention is in that whole wing spar damage tolerance problem, by correlation test and theory analysis, explore the crack arrestment mechanism of whole wing spar crack arrest rib, study extended attribute and the crack arrest rib crack arrest ability of crackle on spar web, finally determine crack arrest bead structures form and parameter selection method.
Thering is provided a kind of whole wing spar crack arrest rib for solving the problems referred to above technical solution of the present invention, described crack arrest rib is arranged on 1/3 place of spar height, and crack arrest rib width is the 1/3 of horizontal edge strip width.
Preferably, the thickness of described crack arrest rib is the 1/3 of described crack arrest rib width.
Accompanying drawing explanation
Below in conjunction with accompanying drawing, specific embodiments of the present invention are further described in detail, wherein:
Fig. 1 is whole wing spar crack arrest rib schematic diagram
Fig. 2 is whole wing spar crack arrest rib sectional view
Detailed description of the invention
First embodiment of the invention provides a kind of whole wing spar crack arrest rib. Whole wing spar is as shown in Figure 1, it is made up of upper edge strip 2, lower edge strip 3, pillar 4, web 5, crack arrest rib 1, by arranging crack arrest rib 1 on whole wing spar web 5, it is possible to effectively reduce whole wing spar crack growth rate, improve whole wing spar and hinder tolerance design level.
The parameter of whole wing spar crack arrest rib 1 is mainly crack arrest rib height h, crack arrest rib width d, crack arrest rib thickness t.
Crack arrest rib parameter selection method of the present invention is: crack arrest rib height h is equal to the 1/3 of spar height H, and crack arrest rib width d is equal to the 1/3 of lower edge strip width (D-down), and crack arrest rib thickness t is equal to the 1/3 of crack arrest rib width d.
It has been experienced that, a kind of whole wing spar crack arrest rib of the present invention is respectively provided with good damage tolerance characteristic, effectively reduces whole wing spar crack growth rate, and the whole wing spar crack arrest rib parameter that the present invention provides chooses best results.
Claims (2)
1. a whole wing spar crack arrest rib, it is characterised in that crack arrest rib is arranged on 1/3 place of spar height, crack arrest rib width is the 1/3 of horizontal edge strip width.
2. whole wing spar crack arrest rib according to claim 1, it is characterised in that the thickness of described crack arrest rib is the 1/3 of described crack arrest rib width.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589341.7A CN105620718A (en) | 2014-10-28 | 2014-10-28 | Integrated spar crack resistant rib |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410589341.7A CN105620718A (en) | 2014-10-28 | 2014-10-28 | Integrated spar crack resistant rib |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105620718A true CN105620718A (en) | 2016-06-01 |
Family
ID=56036150
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410589341.7A Pending CN105620718A (en) | 2014-10-28 | 2014-10-28 | Integrated spar crack resistant rib |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105620718A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458623A (en) * | 2017-08-04 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of T tails aircraft vertical fin spar testpieces design method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2312483A (en) * | 1996-04-24 | 1997-10-29 | British Aerospace | Joint assembly |
| CN102501965A (en) * | 2011-11-08 | 2012-06-20 | 中国商用飞机有限责任公司 | Section bar for upper edge strip of wing rib of outer wing of airplane |
| CN102944211A (en) * | 2012-11-12 | 2013-02-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining area of crack arrest rib of aircraft integral wing spar |
| CN103587677A (en) * | 2012-08-16 | 2014-02-19 | 空中客车西班牙运营有限责任公司 | Highly integrated inner structure of a torsion box of an aircraft lifting surface |
-
2014
- 2014-10-28 CN CN201410589341.7A patent/CN105620718A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2312483A (en) * | 1996-04-24 | 1997-10-29 | British Aerospace | Joint assembly |
| CN102501965A (en) * | 2011-11-08 | 2012-06-20 | 中国商用飞机有限责任公司 | Section bar for upper edge strip of wing rib of outer wing of airplane |
| CN103587677A (en) * | 2012-08-16 | 2014-02-19 | 空中客车西班牙运营有限责任公司 | Highly integrated inner structure of a torsion box of an aircraft lifting surface |
| CN102944211A (en) * | 2012-11-12 | 2013-02-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining area of crack arrest rib of aircraft integral wing spar |
Non-Patent Citations (1)
| Title |
|---|
| 翟新康等: "飞机整体翼梁结构断裂特性分析研究", 《航空计算技术》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107458623A (en) * | 2017-08-04 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of T tails aircraft vertical fin spar testpieces design method |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160601 |