• 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:
    A movable panel such as a fin (2) is connected to a supporting structure such as a wing (1) of an aircraft by hinges (3) comprising flexible blades (4 and 5), elastic, juxtaposed and provided opposed inclinations, so as to allow easy rotation of the panel 2, in response to the movements of an actuator (13); the hinges (3), however, are rigid against other forces, such as aerodynamic suction forces, so that inadmissible movements of the panel (2).
    公开号:FR3014410A1
    申请号:FR1362434
    申请日:2013-12-11
    公开日:2015-06-12
    发明作者:Christophe Casse
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    [0001] The invention relates to an aircraft hinge, disposed between an aircraft movable panel that can consist of a fin or a rudder, and a bearing structure belonging to the aircraft, may be a wing or other element related to the fuselage. Ailerons and control surfaces must be inclined at will to change the trajectory of the aircraft. They are articulated to the structures that carry them by hinges. Generally used hinges of a widespread kind, comprising a pivot fixed to the supporting structure, on which the movable panels engage by rotating yokes. The orientation of the panels is determined by the control of actuators such as cylinders, whose opposite ends are articulated to the panels and to the supporting structure, a lever arm being formed on the panels between the axis of rotation and the point articulation of the actuator. However, it can be considered that these hinges are relatively bulky and heavy. Precautions must also be taken against the risk of blockage, since several hinges must in practice be used simultaneously to support each of the panels, by distributing them on the line of junction between the panel and the supporting structure: the alignment between the axes of the hinges must be fully respected, which requires to build a fixed hinge and the other floating, that is to say with a game of deflection. This freedom, however, must be reconciled with the need to retain the panel against excessive displacement due to aerodynamic forces or gravity, forcing to add stop devices and further complicates the assembly.
    [0002] A simplified device has been proposed in US 5,463,794 A and consists of a hinge in the form of a flexible blade, the opposite ends of which are embedded on the supporting structure and the panel. A pivot point is formed on the hinge by notching it in the middle, so as to give it locally a reduced thickness. The actuators then impose substantially deformations of the blade by making it take variable angles, the apex coincides with the location of the notch. This design does not seem to be acceptable, however, since the angles formed by the blade must remain very small to avoid plastic mechanical stress around the notch. One can still fear either fatigue cracking in the case of metal blades, or delamination in the case of composite blades formed of stacked layers. The subject of the invention is a hinge of a different kind, whose main characteristics are a simplicity of constitution combined with a reliable mechanical resistance, and which is likely to improve the traditional design, allowing simplified assemblies between the panel mobile aircraft and the structure that carries it, without having weak points as in the design of the aforementioned document. In a general form, the invention thus relates to an assembly comprising a panel of an aircraft and a carrier structure of the aircraft and a hinge positioned between the panel and the carrier structure. The invention is remarkable in that the hinge comprises at least two blades made of a flexible and elastic material, each of the blades comprising a first end attached to the panel, an opposite second end fixed to the supporting structure and a free intermediate portion between the panel and the supporting structure, and in that the intermediate parts intersect at a crossing point. Preferably, the assembly according to the invention also comprises a first tab associated with the panel and a second tab associated with the carrier structure, such that: the first and second tabs each comprise a lower face and an upper face; the first ends of the two blades are each fixed on one side of the first tongue; and the second ends are each fixed on one face of the second tongue, in opposition to the first ends with respect to the point of intersection. According to an alternative embodiment, the hinge of the assembly according to the invention comprises at least three blades arranged with alternating inclinations along the junction direction of the panel to the supporting structure. According to another variant embodiment, the hinge of the assembly according to the invention comprises a flexible sheet covering the blades and fixed by opposite edges to the panel and to the supporting structure.
    [0003] According to yet another variant embodiment, the hinge of the assembly according to the invention comprises an elastomer block in which the blades are embedded. In a preferred embodiment, the assembly according to the invention comprises an actuator articulated between the panel and the supporting structure and arranged under the hinge.
    [0004] According to a preferred variant of this embodiment, the assembly according to the invention also comprises a first point of articulation on the supporting structure and a second point of articulation on the panel, and the actuator comprises a first end assembled to the bearing structure on the first hinge point and a second end joined to the panel on the second hinge point.
    [0005] In this embodiment, the second point of articulation of the assembly according to the invention is aligned with the point of intersection along an axis perpendicular to a longitudinal axis of the actuator passing through the first and the second end of the actuator. Finally, the invention relates to an aircraft comprising an assembly according to the invention. The invention will now be described in more detail with reference to the following figures, which represent the various aspects and characters of certain non-exclusive embodiments of others: FIG. 1 is a view of a first embodiment of the invention; - Figure 2 illustrates the mechanism of the hinge; - Figure 3 illustrates the hinge in perspective; - Figures 4 and 5 illustrate two embodiments; and FIG. 6 represents another embodiment. In the embodiment described in Figure 1, the trailing edge of a wing 1 is shown in the transverse direction of the aircraft. The wing 1 is extended by a fin 2 and is connected to it by a hinge 3, which will be described in detail by means of FIG. 2. The hinge 3 comprises two resilient and flexible blades 4 and 5, juxtaposed in the line of FIG. junction between the wing 1 and the fin 2 (here, the transverse direction of the aircraft), and each of which comprises a first end, respectively 6 and 7, attached to the wing 2, and a second end, respectively 8 and 9, opposite to the previous and fixed to the wing 1. The bindings are here more precisely on rigid tongues 10 and 11, respectively belonging to the wing 2 and the wing 1 and each provided with a face upper and a lower face parallel. The tabs 10 and 11 have substantially the same thickness and are located at the same level, so are substantially facing one another, when the wing and the wing are assembled. The first end 8 of the blade 4 is fixed to the lower surface of the tongue 11 and its opposite end 6 is fixed to the upper face of the tongue 10; the opposite arrangement exists for the blade 5, whose first end 9 is fixed to the upper face of the tongue 11 and the opposite end 7 to the lower face of the tongue 10. Thus, the blades 4 and 5 have opposite inclinations and, in the reading direction from left to right, the blade 4 is called "rising blade" and blade 5 is called "descending blade". Views along the direction of the junction between the wing 1 and the wing 2, the blades 4 and 5 have an X arrangement; the blades 4 and 5 intersecting at a cross point referenced by 12. The device is completed by an actuator 13 (visible in Figure 1), which is a cylinder whose first end 13a is connected to the wing 1 on a first hinge point 14 and a second end 13b is connected to the fin 2 on a second hinge point 15. The actuator 13 is arranged under the hinge 3 such that: - the longitudinal axis of the actuator 13 is coincident with the straight line passing through the hinge points 14 and 15 and parallel to the longitudinal axis of the hinge 3, passing through the ends 8 and 7 of the hinge; and the pivot point 15 of the actuator 13 is aligned with the crossing point 12 of the hinge 3 in a plane perpendicular to the longitudinal axis of the actuator 13. When a length variation of the actuator 13 is controlled, the blades 4 and 5 fold (Figure 2) and the hinge 3 is deformed, causing the rotation of the fin 2 about an axis 16 of rotation (non-material). The axis 16 is intrinsic to the assembly of the hinge assembly 3 + actuator 13 on the wing 1 and the fin 2. The axis 16 is aligned with the crossing point 12 and the hinge point 15 and is located between these two points, generally at a short distance from the crossing point 12 of the blades 4 and 5.
    [0006] The distance component between the axis 16 and the articulation point 15, in the direction perpendicular to the direction of extension of the actuator 13, thus forms a lever arm R, which can advantageously be chosen as large as possible to exert the same rotational force on the fin 2, by means of a lower actuator 13 and therefore smaller and lighter.
    [0007] The blades 4 and 5 can be constructed of metal (steel, titanium, etc.), or composite material, depending on whether one wishes to favor the characteristics of elasticity, fatigue resistance, or other. The hinge 3 may comprise other blades, as shown in Figure 3: it also comprises a blade 17 similar to the blade 4 and two blades 18 and 22 similar to the blade 5. Such an arrangement reinforces the hinge 3 and increase its stability against twisting movements. It is advantageous for this to alternate the blades 4 and 17 "rising" from the wing 1 to the wing 2 and the blades 5, 18 and 22 "down". The appearance of the hinge 3 can be improved if it is covered with a flexible sheet 19 (Figure 4), whose ends are fixed to the upper faces of the tongues 10 and 11, or if the blades 4 and 5 are embedded in a elastomer block 20 (FIG. 5). Figure 6 shows an alternative embodiment, applicable to a spoiler panel 21, backed by a fixed flap 23, which extends the wing 1 rearwardly. The features of the previous embodiment are not modified; we simply observe some variations of shapes or dimensions of a secondary nature. The invention could be applied to any other orientable panel of the aircraft, for example to the tail empennage.
    [0008] The number of hinges 3, for each movable panel, will be determined according to safety standards to maintain the strength of the junction and a good respect of the kinematics of rotation, even in case of rupture of one of the hinges 3. The elasticity Moderate blades 4 and 5 in the directions other than bending, however, increases the number of hinges 3 without using floating devices to restore the isostaticity of the assembly.
    权利要求:
    Claims (9)
    [0001]
    REVENDICATIONS1. An assembly comprising a panel (2) of an aircraft and a carrier structure (1) of the aircraft, the assembly also comprising a hinge (3) positioned between the panel (2) and the supporting structure (1), characterized in that the hinge (3) comprises at least two blades (4, 5) made of a flexible and elastic material, each of the blades comprising a first end (6, 7) fixed to the panel, an opposite second end (8, 9) attached to the supporting structure and a free intermediate portion between the panel and the supporting structure, and in that the intermediate portions intersect at a cross point (12).
    [0002]
    2. The assembly of claim 1, further comprising a first tongue (10) associated with the panel (2) and a second tongue (11) associated with the carrier structure (1), the first and second tongues each comprising a lower face and a upper face, the assembly being characterized in that: - the first ends (8,9) of the two blades (4,5) are each fixed on one side of the first tongue (10); and - the second ends (6, 7) are each fixed on one face of the second tongue, in opposition to the first ends with respect to the point of intersection (12).
    [0003]
    3. Assembly according to any one of claims 1 to 2, characterized in that the hinge (3) comprises at least three blades (4, 5, 17, 18, 22) arranged with alternating inclinations along the direction of joining the panel (2) to the supporting structure (3).
    [0004]
    4. Assembly according to any one of claims 1 to 3, characterized in that the hinge (3) comprises a flexible sheet (19) covering the blades (4, 5, 17, 18, 22) and fixed by opposite edges to the panel (2) and to the supporting structure (1).
    [0005]
    5. An assembly according to any one of claims 1 to 4, characterized in that the hinge (3) comprises an elastomer block (20) in which the blades (4, 5, 17, 18, 22) are embedded.
    [0006]
    6. An assembly according to any one of claims 1 to 5, characterized in that it comprises an actuator (13) articulated between the panel (2) and the carrier structure (1) arranged under the hinge.
    [0007]
    7. Assembly according to the preceding claim, also comprising a first hinge point (14) on the carrier structure (1) and a second hinge point (15) on the panel (2), characterized in that the actuator comprises a first end (13a) connected to the supporting structure (1) on the first articulation point (14) and a second end (13b) assembled to the panel on the second articulation point (15).
    [0008]
    8. An assembly according to the preceding claim, characterized in that the second hinge point (15) is aligned with the point of intersection (12) along an axis perpendicular to a longitudinal axis of the actuator passing through the first (13a) and the second end (13b) of the actuator.
    [0009]
    9. Aircraft, characterized in that it comprises a hinge according to any one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    US9604716B2|2017-03-28|
    US20150166171A1|2015-06-18|
    FR3014410B1|2017-08-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE956915C|1952-09-12|1957-01-24|Oliver C Eckel Fa|Suspension device for connecting leaves, especially for swing doors, with the fixed frame|
    DE3908256A1|1989-03-14|1990-09-20|Walter Dipl Ing Feilhauer|Joint|
    US5318422A|1992-11-05|1994-06-07|Erland Robert K|Vacuum bag molding apparatus with channel and spline edge-seal|
    EP1085152A2|1999-09-17|2001-03-21|Advanced Technology Institute of Commuter-Helicopter, Ltd.|Flap hinge mechanism and method for manufacturing the same|
    WO2003062052A1|2002-01-22|2003-07-31|Eads Deutschland Gmbh|Joint for connecting components together on opposite longitudinal sides in addition to a flexible strip used for said joint|EP3187413A1|2015-12-30|2017-07-05|Airbus Defence and Space GmbH|Aircraft wing with spoiler|
    WO2017185121A1|2016-04-29|2017-11-02|Facc Ag|Aerodynamic profiled body for an aircraft|
    EP3446964A1|2017-08-21|2019-02-27|Claverham Limited|Control surface attachment|US3751760A|1971-07-06|1973-08-14|A Wakeman|Pliable tape structure|
    US5098043A|1990-02-27|1992-03-24|Grumman Aerospace Corporation|Integrated power hinge actuator|
    US5388788A|1993-12-16|1995-02-14|The Boeing Company|Hinge fairings for control surfaces|
    US5463795A|1994-03-02|1995-11-07|The Stanley Works|Concealed bearing hinge and method of making same|
    US6027074A|1997-02-27|2000-02-22|Mcdonnell Douglas|Reinforced elastomer panel|
    US6209824B1|1997-09-17|2001-04-03|The Boeing Company|Control surface for an aircraft|
    US6145791A|1998-01-09|2000-11-14|Northrop Grumman Corporation|Elastomeric transition for aircraft control surface|
    US7051982B1|1998-03-27|2006-05-30|Bae Systems Plc|Fairing arrangements for aircraft|
    US6076766A|1998-07-01|2000-06-20|Mcdonnell Douglas Corp.|Folding wing for an aircraft|
    US7328481B2|2005-03-10|2008-02-12|Nokia Corporation|Hinges and associated devices|
    US8899563B2|2009-06-11|2014-12-02|United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Flexible volumetric structure|DE202014103159U1|2014-07-09|2014-09-29|Christian Stroetmann|Device housing, which has a mounting option for a flexible or bendable display and at least two housing parts, which are connected by a hinge / hinge|
    EP3153404B1|2015-10-06|2020-09-23|Safran Landing Systems UK Limited|Aircraft assembly|
    US9964989B2|2015-12-24|2018-05-08|Intel Corporation|Orbiting hinge|
    法律状态:
    2015-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-22| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-09-10| ST| Notification of lapse|Effective date: 20210805 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362434A|FR3014410B1|2013-12-11|2013-12-11|AIRCRAFT HINGE BETWEEN A MOBILE PANEL AND A CARRIER STRUCTURE|FR1362434A| FR3014410B1|2013-12-11|2013-12-11|AIRCRAFT HINGE BETWEEN A MOBILE PANEL AND A CARRIER STRUCTURE|
    US14/566,299| US9604716B2|2013-12-11|2014-12-10|Aircraft hinge arranged between a movable panel and a load-bearing structure|
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