• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The object of the invention is a hybrid tube (22), in particular for an aircraft seat structure S, said structure comprising ribs (10) intended to receive said hybrid tube (22), this hybrid tube (22) comprising a tube (24) made of carbon, monolithic and at least one sleeve (26) made of metallic material, the connection being made by gluing
    公开号:FR3024432A1
    申请号:FR1457475
    申请日:2014-08-01
    公开日:2016-02-05
    发明作者:Jose Portoles；Dominique Nogues；Matthieu Landais
    申请人:Epsilon Composite SA；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to a hybrid type of structural tube, in particular usable for the production of an aeronautical seat structure. In aeronautics, and constantly, both manufacturers and operators seek to reduce the empty weight of an aircraft in order to reduce the consumption related to the navigation of this empty mass. Fuel is an extremely important item in the profitability of an airplane and any reduction in consumption results in a certain economy. On the other hand, it is an issue that should not suffer weight savings, it is the safety of passengers, especially in case of accident.
    [0002] It is also necessary to maintain or even improve the comfort of said passengers. Knowing that users of this mode of transportation spend most of the flight and waiting on the ground while seated; the seats represent an important part of the study of an airplane. A seat is composed of a seat and a backrest for the part directly receiving the user, and this seat / backrest assembly is received in a support structure S which is itself connected to the floor of the aircraft. If the seat / backrest assembly can be arranged from a comfort material such as foam, with a shell of composite material for example, it is not the same for the structure S support of said shell. Indeed, the structure S provides the interface between the floor and the seat or seats. As the floor is resistant, it is necessary to adjust the strength of the support so that it can correspond to the needs defined by the aeronautical standards in force. In addition, to avoid accident, we must maintain the integrity of the structure S in case of shock in these standards.
    [0003] The seats currently adapted to meet these different conditions and requirements are made of specific aluminum alloy grades.
    [0004] The structure S comprises, as shown in the prior art figure, ribs 10, connecting spars 12 and feet 14 for attachment to the floor of said aircraft. These ribs 10 have an L-shape generally so as to receive the seat 16 of the seat on the horizontal leg of the L and the backrest 18 of the seat on the vertical portion of said L also, the seat and the backrest being shown in broken lines. . These ribs 10 also receive the armrests associated with the seats, not shown. The connecting beams 12 are arranged to mechanically connect these ribs 10 parallel to each other and support them because all the ribs do not necessarily have a foot.
    [0005] The longitudinal members are generally circular section tubes, monolithic, which are mounted through housings 20, open, formed in said ribs. These tubes are currently made of specific aluminum alloy, monolithic. This alloy has an important advantage which is that of plasticity. Under an impact, the tubes deform without breaking. The tubes do not generate free sections, broken on one side and may create an additional risk of injury to passengers in the event of an accident. One solution is to replace the aluminum tubes with carbon tubes so as to reduce the final weight of the structure S. It is found that the all-carbon monolithic tubes have a very high strength but under stress, the rupture is total and risk of generate free sections. The present invention proposes a structural tube S in particular for an aeronautical seat, which comprises an arrangement able to overcome the problems that have just been mentioned and to reduce the weight of said structure S. The tube according to the present invention is now described in FIG. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1: A view of a prior art structure S, FIG. hybrid tube according to the present invention, with partial tearing on the middle part of the sleeve, FIG. 2: a view of the comparative curves of tests with a tube according to the present invention, with regard to a curve obtained with a tube of the art anterior and a curve to be obtained with the hybrid tube. - Figure 3: a view of a structure S arranged with the hybrid tube according to the present invention. In FIG. 1, the hybrid tube 22 according to the present invention comprises a carbon tube 24 and at least one sleeve 26.
    [0006] The carbon tube 24 is obtained preferentially and as in the best embodiment by pultrusion so as to benefit from the advantages of this manufacturing process. Indeed, the pultruded tube is of great dimensional accuracy, perfect straightness. In addition, the fibers may be arranged at an angle to the desired unidirectional, 45 °, 60 ° desired tensile direction with the desired diameters and fiber types. These fibers can be chosen from high-strength carbon to achieve high performance up to 6000MPa in tensile strength with a Young's modulus of 250 to 300 GPa.
    [0007] Pultrusion also makes it possible to continuously manufacture and cut the lengths of tubes with great precision. Each tube 24 used is carbon and monolithic. Each sleeve 26 is made of metal material, in this case the material is an aluminum alloy currently used and aeronautical standards.
    [0008] The sleeves 26 are provided at the right of the housing 20 of each rib 10. The sleeve 26 is fitted by interlocking and mounted coaxially on the carbon tube 24. The sleeve 26 is the diameter of the housing 20 of the rib 10, the interlocking game near.
    [0009] It is the carbon tube 24 which has an outside diameter equal to the inside diameter of the sleeve 26, this to play near mounting. Each sleeve 26 is advantageously provided with an orifice 28 for the injection of the adhesive 30 as will be explained further or to exert a pressure to promote the flow between the carbon tube and said sleeve.
    [0010] Each sleeve is indeed reported and secured to the carbon tube by gluing. Another way of joining could also be hooping for example.
    [0011] The glue is introduced at the sleeve / carbon tube interface by any means either by injection and / or vacuum drawing. It is necessary to ensure a perfect distribution of the adhesive in a layer of uniform thickness. An adhesive suitable for this type of assembly is an epoxy-type adhesive.
    [0012] This hybrid tube 22 thus constituted, subjected to stress tests, shows excellent mechanical strength with a work of plastic mechanical deformation of the sleeve and a rupture of the carbon tube 24, this at the right of each end of the sleeve, the stresses being accumulated to the right of the periphery of said sleeve. In order to overcome this drawback, the present invention proposes to thin the ends of each sleeve 26, forming a chamfer 32-1, 32-2 end device. This chamfer is formed at the distal ends. Preferably the slope is gentle angle being of the order of 3 °. On the curves of Figure 2, there is shown the deformation E of an aluminum alloy connecting tube on the curve C1, biased by a load F, namely a force exerted in the median plane of said sleeve, perpendicularly. There is a satisfactory plastic deformation, without complete rupture. Curve C2 shows the deformation of a hybrid connecting tube according to the present invention. It can be seen that the maximum resistance is greatly improved with a sleeve made in the same tube as before, therefore with the same aluminum alloy, this combined with a monolithic tube made of pultruded carbon. Note that the deformed is also plastic because of the presence of the sleeve. On the other hand, the examination shows a rupture of the carbon tube in the middle part of the sleeve, that is to say that the sections of pultruded carbon tube thus generated are not dissociated from the sleeve, which avoids any injury to the sleeve. passenger by the sections of tube, by the very fact of this rupture. This therefore allows to benefit from a high energy absorption shock experienced by the passenger on the seat, related to the rupture of the connecting tube but with a plastic deformation related to the deformation of the sleeve. Once the rupture of the composite tube established, the sections of the composite tube on either side of the rupture, remain perfectly bonded to the sleeves by the adhesive and as the metal sleeve remains monolithic, the ends are not dissociated.
    [0013] The tube according to the present invention makes it possible to gain the difference in weight related to the replacement of a part of the aluminum alloy tube by a carbon tube, ie 15 to 20% gain to give an idea. In addition to this, it is found that the strength of the hybrid tube according to the present invention is greatly increased beyond what is necessary. It is therefore possible to maintain all the safety associated with the standards in force while further reducing the thickness of the sleeves and the carbon tube so as to comply with said standard. This is a second source of weight savings. This weight gain is in no way a loss of safety but with equal safety allows significant weight gain to allow passenger-friendly and environmentally friendly consumption savings. Thus, the object is to produce a hybrid tube according to the invention whose profile is that of the curve C3. In FIG. 3, the structure S equipped with the hybrid tubes 22 according to the present invention comprises ribs and hybrid tubes, the sleeves being arranged in line with the ribs, which constitute the points of application of the forces related to a possible accident. The outer diameter remains the same as the diameter of the prior art provided that it is useful, only the thickness of the metal sleeve is reduced and the carbon tube adapted.
    [0014] If the outer diameter of the sleeves is retained, the existing ribs can then also be kept with their housing and their approval if necessary. In addition, the grade of aluminum alloy can also be changed. Another advantage due to the short length represented by the metallic material in the hybrid tube according to the present invention, it is possible to replace the aluminum alloy material with another metallic material such as titanium whose properties can to be even superior.
    权利要求:
    Claims (6)
    [0001]
    REVENDICATIONS1. Hybrid tube (22) in particular for an aircraft seat structure S, said structure comprising ribs (10) intended to receive said hybrid tube (22), this hybrid tube (22) comprising a carbon tube (24), monolithic and at least one sleeve (26) of metallic material, attached and secured to said carbon tube.
    [0002]
    2. Hybrid tube (22) in particular for structure S of aircraft seat, according to claim 1, characterized in that the joining is carried out by gluing.
    [0003]
    3. Hybrid tube (22) in particular for aircraft seat structure S, according to claim 1 or 2, characterized in that the metal material of the sleeve (26) is an aluminum alloy.
    [0004]
    4. Hybrid tube (22) in particular for aircraft seat structure S, according to claim 1 or 2, characterized in that the carbon tube (24) is a tube obtained by pultrusion.
    [0005]
    Hybrid tube (22), in particular for an aircraft seat structure S, according to claim 1, 2 or 3, characterized in that the sleeve (26) comprises two peripheral chamfering devices (32-1, 32-2). end.
    [0006]
    6. An aircraft seat structure S comprising at least two ribs (10) each comprising at least two housings (20) and at least two hybrid tubes (22) according to one of claims 1 to 5, said tubes (22). hybrids passing through said housing, the tube (24) being monolithic and the sleeves (26) being arranged in line with the housing (20).
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3174791B1|2021-04-28|Tube having a hybrid-type structure, in particular for an aircraft seat
    CA2651129C|2014-07-08|Pressure-sealed floor for aircraft
    CA2823844C|2019-01-15|Ultra lightweight seat for aircraft
    CA2500494C|2009-11-24|Longeron for aircraft and centre-wing section equipped with such a longeron
    EP2426051B1|2014-03-19|Jet engine pylon comprising aligned front attachment points
    EP2597017B1|2016-04-20|Lightweight composite tubular crossmember for an automobile dashboard
    EP2906411B1|2018-07-04|Production method of a one piece connecting rod
    FR2963070A1|2012-01-27|AIRCRAFT COMPRISING A ROD COMPRISING A PART OF COMPOSITE MATERIAL
    CA2757910C|2018-01-16|Fabrication method for a composite structural panel for the trailing edge of an aircraft element
    EP3245107B1|2019-02-20|Energy-absorbing element for car bumper
    EP2701973B1|2017-08-23|Aircraft fuselage and method for constructing a floor in such a fuselage
    EP3331725B1|2020-04-22|Deformable vehicle seat
    FR2986500A1|2013-08-09|CLOSED STRUCTURAL ASSEMBLY HAS AN IMPROVED COMPRESSION
    EP2032419B1|2010-08-11|Structure part obtained via butt-joining for motor vehicle
    FR2984273A1|2013-06-21|Support for fixing floor at fuselage of aircraft, has cruciform shaped branches comprising protuberances, where rails and frames are placed perpendicular to each other such that support ensures direct connection among rails and frames
    WO2011073573A2|2011-06-23|Structural composite trailing edge panel for an aircraft element
    EP2722537A1|2014-04-23|Manufacturing process of an end connector of an elongate member and thus produced end connector
    WO2021170925A1|2021-09-02|Vehicle having a structure that exhibits a third load path between the cradle and a front side rail
    WO2016083726A1|2016-06-02|Landing gear for a light aircraft, comprising at least two wheels
    FR2988372A1|2013-09-27|Front-retractable landing gear for aircraft, has clevis pin, where distance between leg axis and clevis pin and distance between another leg axis and strut axis are higher than distance between strut axis and clevis pin
    同族专利:
    公开号 | 公开日
    JP6513785B2|2019-05-15|
    FR3024432B1|2018-02-02|
    CN106573679B|2019-05-31|
    CN106573679A|2017-04-19|
    EP3174791A1|2017-06-07|
    WO2016016538A1|2016-02-04|
    EP3174791B1|2021-04-28|
    BR112017002005A2|2018-01-30|
    US20170240284A1|2017-08-24|
    JP2017523085A|2017-08-17|
    US10343780B2|2019-07-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO1982003366A1|1981-03-30|1982-10-14|Ian Cecil Toll|Improvements in aircraft seating|
    US20040212243A1|2003-04-28|2004-10-28|Johnson Glenn A.|Curved beam aircraft passenger seat|
    US20100196637A1|2007-04-02|2010-08-05|Mt Aerospace Ag|Method for producing fibre-reinforced hollow bodies and products formed using said method|
    US3511536A|1968-08-28|1970-05-12|Tenryu Industries|Bench|
    US3816571A|1969-11-28|1974-06-11|Warner Lambert Co|Fabrication of soft plastic lens|
    CA1255481A|1986-05-30|1989-06-13|Dale A. Kneller|Pipe joining method|
    TW351918U|1994-02-25|1999-02-01|Shimano Kk|Hollow fishing rod and its insert|
    US5765285A|1995-08-09|1998-06-16|The B.F. Goodrich Company|Method of bending a rigid thermoplastic pipe|
    US5653507A|1995-10-03|1997-08-05|Balt/Trinity|Modular church pew system|
    US6059369A|1997-05-01|2000-05-09|Lear Corporation|Composite vehicle seat back frame and method of manufacturing thereof|
    JPH11262545A|1998-03-17|1999-09-28|Mizuno Corp|Badminton racket shaft|
    US6299251B1|2000-07-31|2001-10-09|Sebert Harper|Foldable park bench|
    AR035143A1|2002-08-15|2004-04-14|Formar S A|COMPOSITE TUBE FORMED BY A METAL EXTERIOR TUBE WITH INTERIOR COATING OF PLASTIC MATERIAL, PROCEDURES FOR ITS MANUFACTURE, AND ITS USE|
    JP2004330559A|2003-05-06|2004-11-25|Ube Nitto Kasei Co Ltd|Method for producing fiber-reinforced hollow structure|
    JP2005012933A|2003-06-19|2005-01-13|Furukawa Electric Co Ltd:The|Cold-shrinking rubber insulating tube|
    JP4784362B2|2005-03-25|2011-10-05|東レ株式会社|Tubular body|
    US7767134B2|2005-06-29|2010-08-03|Philip Morris Usa Inc.|Templated carbon monolithic tubes with shaped micro-channels and method for making the same|
    US8205833B2|2006-12-22|2012-06-26|The Boeing Company|Composite leg structure for a lightweight aircraft seat assembly|
    US7717519B2|2006-12-22|2010-05-18|The Boeing Company|Composite seat back structure for a lightweight aircraft seat assembly|
    US8393574B2|2006-12-22|2013-03-12|The Boeing Company|Composite leg structure for a lightweight aircraft seat assembly|
    US7716797B2|2006-12-22|2010-05-18|The Boeing Company|Composite seat pan structure for a lightweight aircraft seat assembly|
    JP4965347B2|2007-06-18|2012-07-04|大成プラス株式会社|Tubular composite and manufacturing method thereof|
    JP5255831B2|2007-12-27|2013-08-07|株式会社デルタツーリング|Shock absorbing structure, shell-type frame member and seat structure|
    US20090165662A1|2007-12-31|2009-07-02|Nim-Cor, Inc.|Bridge mandrels for anilox and print roller applications and techniques for making them|
    JP2009232803A|2008-03-28|2009-10-15|Daiwa Seiko Inc|Fishing rod|
    US9592648B2|2009-06-01|2017-03-14|Gates Corporation|Low-permeation flexible fuel hose|
    CN101590314A|2009-06-18|2009-12-02|徐建昇|The preparation method of fibrous racket frame|
    JP5838448B2|2009-08-07|2016-01-06|イーメックス株式会社|Conductive polymer composite structure, method for producing conductive polymer composite structure, and actuator element|
    FR2970945B1|2011-02-01|2016-06-10|Benjamin Jacob Saada|ULTRA-LIGHT MONOPIECE SEAT FOR AIRCRAFT|
    US8840740B2|2011-06-24|2014-09-23|The Boeing Company|Apparatus for preventing spark propagation|
    EP2825366B1|2012-03-14|2018-02-21|B/E Aerospace Inc.|Composite structural element and method|
    US9493646B2|2012-04-13|2016-11-15|Ticona Llc|Blow molded thermoplastic composition|
    US9765219B2|2012-04-13|2017-09-19|Ticona Llc|Polyarylene sulfide components for heavy duty trucks|
    US9718248B2|2012-10-12|2017-08-01|The Boeing Company|Thermoplastic composite structures embedded with at least one load fitting and methods of manufacturing same|
    MX2015004661A|2012-10-18|2015-08-07|Toray Industries|Carbon fiber-reinforced resin composition, method for manufacturing carbon fiber-reinforced resin composition, molding material, method for manufacturing molding material, and carbon-fiber reinforced resin molded article.|
    GB201221034D0|2012-11-22|2013-01-09|Mantaray Innovations Ltd|Flexible pipe coupling|
    US9630717B2|2013-04-26|2017-04-25|Encore Interiors, Inc.|Aircraft seating assembly with reduced spacing|
    MA39944A|2014-05-02|2017-03-08|Reliant Worldwide Plastics Llc|Method and system for homogenous thermoplastic seat back assembly|
    FR3024432B1|2014-08-01|2018-02-02|Epsilon Composite|HYBRID TYPE STRUCTURE TUBE, IN PARTICULAR FOR AERONAUTICAL SEAT|
    ES2828695T3|2015-06-24|2021-05-27|Mitsubishi Chem Corp|Method and device for manufacturing fiber reinforced resin material|FR3024432B1|2014-08-01|2018-02-02|Epsilon Composite|HYBRID TYPE STRUCTURE TUBE, IN PARTICULAR FOR AERONAUTICAL SEAT|
    JP1566449S|2016-03-14|2017-01-10|
    JP1566448S|2016-03-14|2017-01-10|
    EP3538439A1|2016-11-10|2019-09-18|Safran Seats USA LLC|Noncircular base frame tube cross-sections|
    US11260774B2|2020-04-13|2022-03-01|Freedman Seating Company|Modular transportation seat frame|
    法律状态:
    2015-07-09| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-05| PLSC| Publication of the preliminary search report|Effective date: 20160205 |
    2016-05-17| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-11| PLFP| Fee payment|Year of fee payment: 4 |
    2018-08-30| PLFP| Fee payment|Year of fee payment: 5 |
    2019-08-29| PLFP| Fee payment|Year of fee payment: 6 |
    2020-08-27| PLFP| Fee payment|Year of fee payment: 7 |
    2021-08-31| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457475A|FR3024432B1|2014-08-01|2014-08-01|HYBRID TYPE STRUCTURE TUBE, IN PARTICULAR FOR AERONAUTICAL SEAT|FR1457475A| FR3024432B1|2014-08-01|2014-08-01|HYBRID TYPE STRUCTURE TUBE, IN PARTICULAR FOR AERONAUTICAL SEAT|
    PCT/FR2015/051948| WO2016016538A1|2014-08-01|2015-07-16|Tube having a hybrid-type structure, in particular for an aircraft seat|
    EP15744272.4A| EP3174791B1|2014-08-01|2015-07-16|Tube having a hybrid-type structure, in particular for an aircraft seat|
    US15/500,960| US10343780B2|2014-08-01|2015-07-16|Tube having a hybrid-type structure, in particular for an aircraft seat|
    CN201580038141.5A| CN106573679B|2014-08-01|2015-07-16|Mixing tube and aircraft seat structure for armchair structure|
    BR112017002005A| BR112017002005A2|2014-08-01|2015-07-16|hybrid tube, and s seat structure.|
    JP2017505502A| JP6513785B2|2014-08-01|2015-07-16|Airplane seat structure|
    [返回顶部]