CN202896871U - Novel wing spar - Google Patents
Novel wing spar Download PDFInfo
- Publication number
- CN202896871U CN202896871U CN 201220590713 CN201220590713U CN202896871U CN 202896871 U CN202896871 U CN 202896871U CN 201220590713 CN201220590713 CN 201220590713 CN 201220590713 U CN201220590713 U CN 201220590713U CN 202896871 U CN202896871 U CN 202896871U
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- wing
- wing spar
- spar
- novel
- composite material
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Abstract
The utility model discloses a novel wing spar, and belongs to the technical field of the structure of an airplane. For the improvement of a wing spar material and a layout structure, the wing spar adopts a three-dimensional woven composite material, and is formed by means of integrated RTM (resin transfer molding). Compared with the conventional wing spar which is made from the metal material, the novel wing spar which is made from the composite material can be used for reducing the weight of the structure of the airplane spar. The three-dimensional woven composite material is used for connecting yarns of a plurality of systems into a space net structure due to a weaving machining method, so that the novel wing spar is good in integrity, the defect that the conventional laminated composition material is weak in interlayer and can not resist the impact can be overcome, the mechanical property of a textile along a thickness direction can be improved, and the novel wing spar is lower in cost, and is suitable for the batch production. According to the novel wing spar, a double-wing spar is improved, and the triangular layout of double spars is used, so that the stability when a force is applied onto a high wing can be improved, and the safety and reliability of the wing of the airplane can be improved.
Description
Technical field
The utility model relates to the civil aviation technical field of structures, specifically, it is a kind of Novel double-girder wing spar, to the twin-spar construction wing spar material that consisted of by Front wing spar and the wing back rest and the improvement of layout structure, effectively alleviate aircraft wing central spar structural weight, the novel wing spar of the safety when the raising aircraft wing is stressed.
Background technology
Improve two general objectives of Commercial Market competitive power: the one, remarkable performance driving economy is weighed with life cycle cost, load carrying ability and voyage usually; The 2nd, environmental performance, its measurement index then is remarkable reduce fuel oil consumption, noise and combined environment impact, improves simultaneously the traveling comfort in the cabin.The core that realizes this two general objective is: the technology such as light structures, advanced aerodynamics and innovation manufacturing process.And the effective means one that reduces structural weight is to adopt advanced design and analysis means, the 2nd, and advanced composite material, titanium alloy, aluminum lithium alloy and other new material and the integrated structure of a large amount of employings.
Along with the development in epoch, use large-scale integral structure and replace traditional riveting composite structures to become a megatrend of the outer aircaft configuration development of Now Domestic.Integrally-built advantage is that mainly structural-load-carrying capacity is strong, lightweight construction, processing technology is simple, stress concentration portion position and potential endurance crack crack initiation source are few, and under identical material property and weight prerequisite, integral structure also reduces manufacturing cost greatly than conventional unitized construction.
But for aircraft, the weight of existing wing relatively and the wing weight in the ideal also have certain gap, can further alleviate wing weight and there is no at present alternate manner.
The utility model content
For the deficiencies in the prior art, the utility model proposes a kind of Novel double-girder wing spar, to the twin-spar construction wing spar material that consisted of by Front wing spar and the wing back rest and the improvement of layout structure, be specially:
The wing spar adopts the three-dimensional woven composite material, by whole resin transfer molding; And the web upper limb of wing spar and lower edge are designed with edge strip and lower edge strip in the same way, the obtuse angle that upper edge strip and lower edge strip all become to equate with web, the section of wing spar is " C " type structure.
For the wing spar structure with double wing spanner, Front wing spar is relative with the opening direction of " C " type structure of the wing back rest in the utility model.And the web of the wing back rest has bending at engine suspension strengthening rib place, and knuckle is towards the leading edge of a wing.
The utility model has the advantage of:
1, the utility model wing spar adopts the wing spar to adopt the three-dimensional woven composite material, by whole RTM moulding, make wing spar good integrity, shock-resistant, be easy to moulding, and effectively alleviate the weight of wing spar, simplify technique, reduce the stress concentration phenomenon; The programmable features of its design has guaranteed that the spar of producing any model need not to change production facilities, only needs new design reprogramed to get final product.
2, the utility model wing spar improves for the layout structure of double-longeron wing spar, adopt the triangle layout structure, can effectively promote the wing overall performance, wing can be born along the next wing load of air flow line, reduced the transverse bending moment along air flow line at wing and body joint place;
3, the utility model wing spar technique is simple, and cost is low.
Description of drawings
Fig. 1 is the topology layout scheme drawing of the utility model double-longeron wing spar.
Among the figure:
The upper edge strip of 1-Front wing spar 2-wing back rest 101-web 102-
Edge strip 104-bending under the 103-
The specific embodiment
Below in conjunction with accompanying drawing the utility model is further specified.
The performance of composite material after being subject to impact load can sharply descend, but civil aircraft composite structure wing spar is positioned at wing inside, be subject to the situation of load seldom, therefore the whole composite material that adopts becomes possibility, fragile in order to improve tradition stratum and composite material interlayer, the easily phenomenon of layering, so a kind of novel wing spar of the utility model, material and topology layout by the wing spar are improved, are specially:
The wing spar adopts the three-dimensional woven composite material, by whole RTM(Resin Transfer Molding, resin transfer moulding) moulding.Its concrete structure is by requiring to determine that comprise that the dimensional parameters of each direction in space changes, local structure strengthen, and the designs such as local punching loss of weight all can realize by the programming to three-dimensional loom.Above-mentioned three-dimensional woven composite material is a kind of as woven composite material, is to utilize woven job operation that the yarn of a plurality of systems is linked as the space net structure, then the and high-performance composite materials that obtain compound with matrix under certain condition.The characteristics of three-dimensional machine composite material are: the yarn bundle of warp-wise and broadwise planar is 90 ° and interweaves or arrange, and with performance in the face that improves composite material, has then improved the stability of material through the yarn bundle of structural thickness direction.Owing to the existence of fortifying fibre on the thickness direction, strengthened the interlaminar shear strength of material, reduce lamination, and improved its shock resistance and fatigue property.The three-dimensional woven composite material also has stronger profiling ability, can one-shot forming have the weaving preformed member of profiled-cross-section, such as various quadrature solid slabs, Varying-thickness solid slab, central hole structure box beam, H-girder etc., and loom is relatively simple, cost is lower, is suitable for batch manufacturing.Thus the wing spar good integrity by the above-mentioned material moulding, shock-resistant, be easy to moulding, and effectively alleviate the weight of wing spar, simplify technique, reduce the stress concentration phenomenon.
Meet in the material at three-dimensional woven, the preferred carbon fiber ring epoxy resin composite material of the utility model, the density of carbon fiber ring epoxy resin composite material is about 1.7g/cm3, modulus of elasticity 230GPa, tensile strength are more than 3500Mpa, than present Aluminium Alloys in Common Use density of material 2.7g/cm3, modulus of elasticity 70GPa, pulling strengrth 400MPa, have lightweight, the advantage such as intensity is high, and is anticorrosive.
In order to make wing spar easier employing three-dimensional woven composite material and RTM moulding, therefore in the utility model web 101 upper limbs of wing spar are designed with upper edge strip 102 and lower edge strip 103 in the same way with lower edge, upper edge strip 102 and the obtuse angle that lower edge strip 103 all equates with 101 one-tenth of webs, the section of wing spar is " C " type structure.
For having the double wing spanner wing spar structure of Front wing spar 1 with the wing back rest 2, Front wing spar 1 is relative with the opening direction of " C " type structure of the wing back rest 2; The bending 104 that the web 101 of the wing back rest 2 has at engine suspension strengthening rib place in the utility model, knuckle is towards the leading edge of a wing.Make thus the wing back rest 2 form the triangle layout structure.Because the wing back rest 2 is equivalent to two power bars from end to bending 104, thereby the transverse bending moment of the former wing back rest 2 ends can be changed into the wing back rest 2 axial stresses, thereby has guaranteed the substantivity of the wing back rest 2 power transmissions, high efficiency.And consider that bending 104 places that are positioned at the wing back rest 2 on the wing are hanging driving engine, engine thrust can produce very large moment of torsion to wing structure equally, therefore the wing back rest 2 adopts this triangle layout structure design to increase wing box inside configuration space, thereby has alleviated to a great extent the effect to the wing end that this torsion produces.This design of the wing back rest 2 has guaranteed that also the installation of each high lift device of trailing edge place is interference-free.
Claims (6)
1. novel wing spar is characterized in that: the wing spar adopts the three-dimensional woven composite material, by whole resin transfer molding (RTM) process one-shot forming.
2. a kind of novel wing spar as claimed in claim 1, it is characterized in that: described three-dimensional woven composite material is the carbon fiber ring epoxy resin composite material
3. a kind of novel wing spar as claimed in claim 1, it is characterized in that: the web upper limb of wing spar and lower edge are designed with edge strip and lower edge strip in the same way.
4. a kind of novel wing spar as claimed in claim 3 is characterized in that: the obtuse angle that described upper edge strip and lower edge strip all become to equate with web, the section of wing spar is " C " type structure.
5. a kind of novel wing spar as claimed in claim 4, it is characterized in that: for the wing spar structure with double wing spanner, Front wing spar is relative with the opening direction of " C " type structure of the wing back rest.
6. a kind of novel wing spar as claimed in claim 1, it is characterized in that: for the wing spar structure with double wing spanner, the web of the wing back rest has bending at engine suspension strengthening rib place, and knuckle is towards the leading edge of a wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220590713 CN202896871U (en) | 2012-11-09 | 2012-11-09 | Novel wing spar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220590713 CN202896871U (en) | 2012-11-09 | 2012-11-09 | Novel wing spar |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202896871U true CN202896871U (en) | 2013-04-24 |
Family
ID=48117571
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220590713 Expired - Fee Related CN202896871U (en) | 2012-11-09 | 2012-11-09 | Novel wing spar |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202896871U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104097764A (en) * | 2013-04-02 | 2014-10-15 | 波音公司 | Continuously curved spar and method of manufacturing |
| CN104743095A (en) * | 2013-12-31 | 2015-07-01 | 空中客车西班牙运营有限责任公司 | Highly integrated infused box made of composite material and method of manufacturing |
-
2012
- 2012-11-09 CN CN 201220590713 patent/CN202896871U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104097764A (en) * | 2013-04-02 | 2014-10-15 | 波音公司 | Continuously curved spar and method of manufacturing |
| CN104097764B (en) * | 2013-04-02 | 2018-10-12 | 波音公司 | The spar and its manufacturing method of continuous bend |
| CN104743095A (en) * | 2013-12-31 | 2015-07-01 | 空中客车西班牙运营有限责任公司 | Highly integrated infused box made of composite material and method of manufacturing |
| CN104743095B (en) * | 2013-12-31 | 2019-06-07 | 空中客车西班牙运营有限责任公司 | Highly integrated perfusion case and manufacturing method made of composite material |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130424 Termination date: 20131109 |