• 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 invention relates to a front fairing of a mast of an aircraft comprising a cap (62), made in one piece, which extends over almost the entire area of the front fairing and which is configured to occupy a closed position in which a peripheral edge (76) of the cap (62) and a peripheral edge (78) of the front fairing and / or nacelle (46) are contiguous, and an open position in which the peripheral edge (76) of the cap (62) is at least partially spaced from the peripheral edge (78) of the front fairing and / or the nacelle (46), the front fairing comprising at least one locking system for holding the cap (62) in position. closed position.
    公开号:FR3079215A1
    申请号:FR1852459
    申请日:2018-03-22
    公开日:2019-09-27
    发明作者:Thierry Theron
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    FRONT FAIRING OF AN AIRCRAFT MAST COMPRISING A MOBILE HAIR AND AIRCRAFT EQUIPPED WITH SAID FRONT FAIRING
    The present application relates to a front fairing of an aircraft mast comprising a movable cover as well as to an aircraft equipped with said front fairing.
    According to one configuration, an aircraft 10 comprises several engine assemblies 12 positioned under the wing 14.
    As illustrated in FIGS. 1 and 2, a motor assembly 12 comprises:
    a motor 16 in which a primary air flow circulates, a nacelle 18 positioned around the motor 16 so as to delimit with the latter an annular duct in which a secondary air flow flows, and a mast 20 which ensures the connection between the engine 16 and the wing 14.
    The mast 20 comprises a rigid primary structure, which ensures inter alia the transmission of forces between the engine 16 and the airfoil 14, and a secondary structure 22 which envelops the primary structure and which limits the drag of the mast 20.
    This secondary structure 22 includes a front fairing 24, positioned at the front of the airfoil 14, a central fairing 26, positioned under the airfoil 14 and in line with the nacelle 18, as well as a rear fairing 28 called the lower rear aerodynamic fairing. or APF ("Aft Pylon Fairing" in English), positioned at the rear of the nacelle 18.
    For the present application, a longitudinal direction is parallel to the axis of the motor 16.
    The terms front and rear refer to the direction of flow of the primary air flow in the engine in operation, the primary air flow entering the engine at the front and leaving the engine at the rear.
    The terms upper and lower refer to a position along a vertical axis, an upper element being further away from the ground than a lower element when the aircraft is on the ground.
    According to one embodiment, visible in FIGS. 3 to 5, the front fairing 24 has an aerodynamic surface which includes a curved front zone 30, an upper zone 32 in the extension of the curved front zone 30 and two right and left lateral zones 34.1, 34.2 arranged on either side of the upper zone 32.
    The front fairing 24 comprises a plurality of juxtaposed panels, shaped according to the aerodynamic surface of the front fairing 24 and fixed on a chassis also called a substructure. One of these panels, positioned on the upper zone 32, more precisely behind the upper zone 32, has an air grille 36.
    To allow access to the interior of the secondary structure, the front fairing 24 comprises:
    a right front movable panel 36.1 and a right rear movable panel 38.1 positioned on the right lateral zone 34.1, a left front movable panel 36.2 and a left rear movable panel 38.2 positioned on the left lateral zone 34.2, at least one upper movable panel 40 positioned in the upper area 32.
    Each of these movable panels 36.1, 36.2, 38.1, 38.2 and 40 can be completely detached from the rest of the front fairing 24. Thus, each movable panel 36.1, 36.2, 38.1, 38.2 and 40 is connected to the rest of the front fairing 24 by a plurality of fasteners 42 positioned over the entire periphery of the movable panel with a pitch of the order of 10 cm.
    Consequently, when an operator wishes to access the interior of the front fairing 24, he must generally dismantle all the movable panels 36.1, 36.2, 38.1, 38.2 and 40 and unscrew more than a dozen fasteners 42 (of the order about twenty) for each of them. During the intervention, the operator must correctly store each dismantled mobile panel so as not to damage it. Finally, at the end of his intervention, all the fasteners 42 must be screwed back on. Thus, the dismantling and reassembly operations of the movable panels are relatively long and tedious.
    The present invention aims to remedy the drawbacks of the prior art.
    To this end, the subject of the invention is a front fairing of an aircraft mast, having an aerodynamic surface which extends between a nacelle and a wing of the aircraft, at the front of the wing, and which comprises a curved front zone, an upper zone in the extension of the curved front zone and two right and left lateral zones arranged on either side of the upper zone, said front fairing comprising a chassis and a cover.
    According to the invention, the front fairing is characterized in that:
    the cap is a single piece, produced in one piece, in the form of a wall which comprises a front portion, an upper portion, a right side portion and a left side portion shaped respectively as the curved front area, the area upper and the two right and left lateral zones of the aerodynamic surface of the front fairing, the cover is configured to occupy a closed position in which a peripheral edge of the cover and a peripheral edge of the front fairing and / or of the nacelle are joined and an open position in which the peripheral edge of the cover is at least partially spaced from the peripheral edge of the front fairing and / or of the nacelle, and the front fairing comprises at least one locking system for keeping the cover in the closed position.
    The fact of providing a single piece in place of a multitude of panels makes it possible to reduce the number of fasteners and therefore the duration of intervention to access the equipment positioned under the front fairing.
    Finally, this solution provides better accessibility to the equipment positioned under the front fairing when the cover is removed.
    According to another characteristic, the upper portion of the cap comprises an opening and the front fairing comprises an upper panel, independent of the cap, secured to the chassis, having a ventilation grille, the upper panel and the cap having shapes which cooperate so as to ensure continuity between the cover and the top panel when the cover is in the closed position.
    According to a first embodiment, the cap is configured to be completely detached from the chassis in the open position.
    According to a second embodiment, the front fairing comprises at least one articulation permanently connecting the cover and the chassis, said articulation being configured to rotate the cover relative to the chassis around a pivot axis between the closed and open positions .
    According to one configuration, the pivot axis is oriented in a horizontal direction, approximately perpendicular to a longitudinal direction and / or positioned near a rear edge of the cap.
    According to another characteristic, the locking system comprises a plurality of removable fasteners connecting the cap and the chassis to maintain the cap in the closed position.
    The invention also relates to an aircraft comprising a front fairing of a mast according to one of the preceding characteristics.
    Other characteristics and advantages will emerge from the description of the invention which follows, description given by way of example only, with reference to the appended drawings among which:
    FIG. 1 is a perspective view of an aircraft,
    FIG. 2 is a view of a secondary structure of an aircraft mast which illustrates an embodiment,
    FIG. 3 is a perspective view of a front fairing of a secondary structure of an aircraft mast which illustrates an embodiment of the prior art,
    FIG. 4 is a diagrammatic section along the plane PI of FIG. 3,
    FIG. 5 is a schematic section along the plane P2 of FIG. 3,
    FIG. 6 is a perspective view of a front fairing of a secondary structure of an aircraft mast which illustrates an embodiment of the invention, said front fairing comprising a cover in the closed position,
    FIG. 7 is a diagrammatic section along the plane PI of FIG. 6,
    FIG. 8 is a schematic section along the plane P2 of FIG. 6,
    FIG. 9 is a perspective view of the front fairing visible in FIG. 6, its cover being in the open position, which illustrates a first embodiment, and
    Figure 10 is a perspective view of the front fairing visible in Figure 6, its cover being in the open position, which illustrates a second embodiment.
    In Figures 6 to 10, there is shown a front fairing 50 of a secondary structure of an aircraft mast.
    Geometrically, as illustrated in FIG. 6, the front fairing 50 extends between a nacelle 46 and a wing 48 of the aircraft, at the front of the wing 48, and has an aerodynamic surface S50 which comprises a curved front zone 52, an upper zone 54 in the extension of the curved front zone 52 and two right and left lateral zones 56.1, 56.2 arranged on either side of the upper zone 54.
    The upper zone 54 comprises a narrow front part 54.1 and a rear part 54.2, wider than the front part 54.1, at the level of which a ventilation grille 58 is positioned. On the structural level, the front fairing 50 comprises a chassis 60 (also called substructure) and a cover 62 shaped according to the aerodynamic surface S50 of the front fairing 50, said cover 62 being supported by the chassis 60.
    According to an embodiment illustrated by FIGS. 7 and 8, the chassis 60 comprises:
    a base 64, substantially horizontal, which extends from the right lateral zone 56.1 to the left lateral zone 56.2 and which has a right rim 64.1 parallel to the right lateral zone 56.1 and a left rim 64.2 parallel to the left lateral zone 56.2, right and left supports 66, 68, substantially vertical, which each extend from the base 64 to the upper zone 54. Thus, each right or left support 66, 68 comprises a lower end 66.1, 68.1, connected at the base 64, and an upper end 66.2, 68.2 configured to receive the cap 62.
    According to one embodiment, the upper end 66.2, 68.2 of the right support 66 (respectively left 68) comprises a right rim 70 (respectively left 72) which has a first right part 70a (respectively left 72a), parallel to the upper zone 54, and a second right part 70b (respectively left 72b) parallel to the right lateral zone 56.1 (respectively left 56.2).
    The right edge 64.1 of the base 64 and the second part 70b of the right edge 70 of the right support 66 are spaced apart to allow access to the interior of the front fairing 50. In the same way, the left edge 64.2 of the base 64 and the second part 72b of the left edge 72 of the left support 68 are spaced apart to allow access to the interior of the front fairing 50.
    The cover 62 is a single piece, produced in one piece, in the form of a wall 74 which comprises a front portion 74.1, an upper portion 74.2, a right side portion 74.3 and a left side portion 74.4 (visible on the FIG. 8) respectively shaped like the curved front zone 52, the upper zone 54 and the two right and left lateral zones 56.1, 56.2 of the aerodynamic surface S50 of the front fairing 50. The cover 62 extends over almost the entire aerodynamic surface S50 of the front fairing 50 in the closed position.
    The cover 62 has a peripheral edge 76 which has a front edge 76.1, a rear edge 76.2, a right side edge 76.3 and a left side edge 76.4 (visible in Figures 7 and 8).
    The cover 62 is configured to occupy a closed position, visible in FIG. 6, in which the peripheral edge 76 of the cover 62 and a peripheral edge 78 of the front fairing 50 and / or of the nacelle 46 are joined, and an open position , visible in FIGS. 9 and 10, in which the peripheral edge 76 of the cover 62 is, at least partially, spaced from the peripheral edge 78 of the front fairing 50 and / or of the nacelle 46, thus allowing access to the interior of the mast.
    In addition to the cover 62, the front fairing 50 comprises at least one locking system 80 for holding the cover 62 in the closed position.
    According to a first embodiment visible in FIG. 9, the cover 62 is, in the open position, completely detached from the chassis 60. According to this first variant, in the open position, the peripheral edge 76 of the cover 62 is spaced from the peripheral edge of the front fairing 50 and / or nacelle 46 over its entire length.
    According to this first embodiment, the locking system 80 comprises a plurality of removable fasteners 82 connecting the cover 62 and the frame 60 to maintain the cover 62 in the closed position.
    The removable fasteners 82 are distributed over the peripheral edge 76 of the cover 62.
    According to a second embodiment visible in FIG. 10, the front fairing 50 comprises at least one articulation 84 permanently connecting the cover 62 and the frame 60, said articulation 84 being configured to rotate the cover 62 relative to the frame 60 around a pivot axis A84 between the closed and open positions.
    The cap 62 being always connected to the frame 60, even in the open position, the risks of loss of the cap 62 when it is dismantled are eliminated.
    According to one configuration, the pivot axis A84 is oriented in a horizontal direction, approximately perpendicular to the longitudinal direction. The pivot axis A84 is positioned near the rear edge 76.2 of the cover 62. Thus, in the open position (as illustrated in FIG. 10), the peripheral edge 76 is spaced from the peripheral edge 78 of the front fairing 50 and / or of the nacelle 46 over part of its length (corresponding to the front edge 76.1, to the right and left lateral edges 76.3 and 76.4).
    According to this second embodiment, the front fairing 50 comprises two articulations 84 positioned on the rear edge 76.2 of the cover 62 at the level of the right and left lateral portions 74.3 and 74.4.
    According to this second embodiment, the locking system 80 comprises at least one removable fixing 86, connecting the cover 62 and the frame 60, to keep it in the closed position.
    According to one configuration, the locking system 80 comprises at least a first removable fastener 86 near the front edge 76.1, at least a second removable fastener 86 'near the right side edge 76.3 and at least a third removable fastener 86 ”(visible in Figure 8) near the left side edge 76.4. The second and third removable fasteners 86 'and 86 ”are positioned approximately equidistant from the front and rear edges 76.1 and 76.2.
    According to one configuration, the upper portion 74.2 of the cover 62 includes an opening 88 in line with the ventilation grille 58.
    According to this configuration, the front fairing 50 comprises an upper panel 90, independent of the cover 62, which has the ventilation grille 58 and which is fixed to the chassis 60 by fixings 92.
    This upper panel 90 has forms cooperating with the opening 88 of the cover 62 so that when the cover 62 is in the closed position, the peripheral edge 92 of the upper panel 90 is covered by the peripheral edge 94 of the opening 88 of the cover 62 so as to ensure continuity between the cover 62 and the upper panel 90.
    To maintain the peripheral edge 94 of the opening 88 of the cover 62 pressed against the peripheral edge 92 of the upper panel 90, the front fairing 50 comprises at least one removable fixing 96 positioned at the peripheral edge 94 of the opening 88 of the cover 62. Several removable fasteners 96 (visible in FIG. 6) can be provided, distributed over the peripheral edge 94 of the opening 88.
    According to this configuration, the upper panel 90 is always secured to the chassis 60 when the cover 62 is in the open position. Thus, the duct opening at the level of the ventilation grille 58 is always closed by the ventilation grille 58, even when the cover 62 is in the open position.
    According to one embodiment, the removable fasteners 82, 86, 86 ', 86 ”and 96 are screws. However, the invention is not limited to this embodiment. Other solutions can be envisaged for the locking system 80 making it possible to maintain the cap 62 in the closed position.
    The invention provides the following advantages:
    Providing a single piece instead of a multitude of panels improves aerodynamics.
    This also makes it possible to reduce the number of attachments and therefore the intervention time to access the equipment positioned under the front fairing 50.
    Finally, this solution provides better accessibility to the equipment positioned under the front fairing 50 when the cover 62 is removed.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1. Front fairing (50) of an aircraft mast, having an aerodynamic surface (S50) which extends between a nacelle (46) and a wing (48) of the aircraft, in front of the 'wing (48), and which comprises a curved front zone (52), an upper zone (54) in the extension of the curved front zone (52) and two right and left lateral zones (56.1, 56.2) arranged in part and on the other side of the upper zone (54), said front fairing (50) comprising a frame (60) and a cover (62), characterized in that the cover (62) is a single piece, produced in one piece , in the form of a wall (74) which comprises a front portion (74.1), an upper portion (74.2), a right side portion (74.3) and a left side portion (74.4) shaped respectively as the curved front area ( 52), the upper zone (54) and the two right and left lateral zones (56.1, 56.2) of the aerodynamic surface (S50) of the front fairing (50), in that the cover (62) is c configured to occupy a closed position in which a peripheral edge (76) of the cover (62) and a peripheral edge (78) of the front fairing (50) and / or of the nacelle (46) are joined and an open position in which the peripheral edge (76) of the cover (62) is at least partially spaced from the peripheral edge (78) of the front fairing (50) and / or of the nacelle (46) and in that the front fairing (50) comprises at at least one locking system (80) for holding the cover (62) in the closed position.
    [2" id="c-fr-0002]
    2. Front fairing of an mast of an aircraft according to claim 1, characterized in that the upper portion (74.2) of the cover (62) comprises an opening (88) and in that the front fairing (50) comprises an upper panel (90), independent of the cover (62), integral with the frame (60), having a ventilation grille (58), the upper panel (90) and the cover (62) having shapes which cooperate so as to ensure continuity between the cover (62) and the upper panel (90) when the cover (62) is in the closed position.
    [3" id="c-fr-0003]
    3. Front fairing of an aircraft mast according to claim 1 or 2, characterized in that the cover (62) is configured to be completely detached from the chassis (60) in the open position.
    [4" id="c-fr-0004]
    4. Front fairing of an aircraft mast according to claim 1 or 2, characterized in that the front fairing (50) comprises at least one articulation (84) permanently connecting the cover (62) and the chassis (60 ), said articulation (84) being configured to pivot the cover (62) relative to the frame (60) about a pivot axis (A84) between the closed and open positions.
    [5" id="c-fr-0005]
    5. Front fairing of an mast of an aircraft according to the preceding claim, characterized in that the pivot axis (A84) is oriented in a horizontal direction,
    5 approximately perpendicular to a longitudinal direction.
    [6" id="c-fr-0006]
    6. Front fairing of an aircraft mast according to claim 4 and 5, characterized in that the pivot axis (A84) is positioned near a rear edge (76.2) of the cover (62).
    [7" id="c-fr-0007]
    7. Front fairing of an aircraft mast according to one of the preceding claims, characterized in that the locking system (80) comprises a plurality of removable fasteners (82) connecting the cover (62) and the chassis (60) to maintain the cap (62) in the closed position.
    [8" id="c-fr-0008]
    8. An aircraft comprising a front fairing (50) of a mast according to one of the preceding claims.
    类似技术:
    公开号 | 公开日 | 专利标题
    EP2500268B1|2013-10-16|Engine pylon for an aircraft
    EP3543140A1|2019-09-25|Front fairing of an aircraft pylon comprising a movable cap and aircraft equipped with said front fairing
    EP2038176B1|2010-09-15|Engine assembly for aircraft comprising an aerodynamic coupling fairing mounted on two separate elements
    EP2200851B1|2012-06-13|Motor vehicle front end module
    EP2139768B1|2011-11-30|Aircraft engine attachment pylon that has an engine rear attachment fitted with a barrel nut
    CA2652317C|2014-07-08|Device for attaching an aircraft engine
    EP2072397B1|2015-02-11|Intermediate casing extension for an aircraft jet engine, comprising a sectorised annular groove for receiving nacelle covers
    EP2038175B1|2009-11-18|Engine assembly for an aircraft comprising a support cradle for a fan shroud mounted on two separate elements
    EP2554478A1|2013-02-06|Articulated fairing for nacelle members supported by these nacelle members in a closed position
    WO2009147341A2|2009-12-10|Engine mounting pylon including means for attaching spars and panels arranged outside the inner space of the box
    FR2887851A1|2007-01-05|ENGINE ATTACHING MAT FOR AN AIRCRAFT
    FR3020347A1|2015-10-30|METHOD FOR ASSEMBLING A REAR AIRCRAFT PART
    EP3505439A1|2019-07-03|Assembly for aircraft comprising a mounting strut primary structure attached to a wing box by compact fasteners in the leading edge area
    EP3487763B1|2020-07-01|Cradle for a turbopropeller engine with integrated air inlet duct
    FR3085351A1|2020-03-06|CENTRAL FAIRING OF AN AIRCRAFT MAST COMPRISING AT LEAST ONE ARTICULATED PANEL AND AIRCRAFT EQUIPPED WITH SAID CENTRAL FAIRING
    EP3683149B1|2021-05-26|Method for mounting a mast of an aircraft
    FR3079216A1|2019-09-27|FRONT FITTING OF AN AIRCRAFT MAT COMPRISING AT LEAST ONE ARTICULATED PANEL AND AN AIRCRAFT EQUIPPED WITH SAID FRONT FITTING
    EP3585677B1|2021-04-07|Motor vehicle body understructure
    EP2352674B1|2013-01-16|Aircraft engine assembly including a rigid modular structure for a mounting pylon3
    EP3670350B1|2021-03-24|Propulsion assembly of an aircraft comprising a connecting fairing between a nacelle and a pylon of the aircraft provided with a removable cover and aircraft provided with said propulsion assembly
    FR3020338A1|2015-10-30|REAR AIRCRAFT PART PROVIDED WITH SUPPORT STRUCTURE OF OPTIMIZED SHAPE ENGINES
    EP3647202B1|2021-06-16|Aircraft turbine engine assembly comprising a hinged cover
    EP3620388A1|2020-03-11|Aircraft turbine engine assembly comprising a hinged cover
    EP3656676A1|2020-05-27|Aircraft nacelle comprising a cover with two hinged flaps
    FR2909639A1|2008-06-13|Aircraft assembly, has panel retaining unit with arm connected on panels and retained by stop during displacement of nacelle cowling from open position so as to cause relative displacement of panels with respect to nacelle cowling
    同族专利:
    公开号 | 公开日
    EP3543140A1|2019-09-25|
    US11034458B2|2021-06-15|
    FR3079215B1|2020-11-20|
    US20190291882A1|2019-09-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4574325A|1984-02-09|1986-03-04|The Boeing Company|Lightning protection electrical circuit path for coupling between aircraft structures|
    EP1535840A1|2003-10-22|2005-06-01|Airbus France|Device for mounting a fairing between a nacelle of an aircraft engine and a pylon|
    FR2902406A1|2006-06-20|2007-12-21|Airbus France Sas|FITTING FOR SUSPENSION MAT FROM A TURBOMOTEUR TO AN AIRCRAFT WING|
    WO2008006826A1|2006-07-11|2008-01-17|Airbus France|Engine assembly for aircraft comprising an aerodynamic coupling fairing mounted on two separate elements|
    US20110127367A1|2009-11-27|2011-06-02|Rohr, Inc.|Fan cowl support for a turbofan engine|
    US20150251768A1|2014-03-04|2015-09-10|Mra Systems, Inc.|Engine pylon structure|
    FR2291091B1|1974-11-13|1977-10-21|Snecma|
    US4474346A|1982-07-02|1984-10-02|The Boeing Company|Collapsible cowl structure for gas-turbine engine strut|
    FR2862944B1|2003-12-01|2006-02-24|Airbus France|DEVICE FOR ATTACHING A TURBOPROPULSER UNDER AN AIRCRAFT VESSEL|
    FR2862945B1|2003-12-01|2006-04-28|Airbus France|DEVICE FOR ATTACHING A TURBOPROPULSER UNDER AN AIRCRAFT VESSEL.|
    FR2878229B1|2004-11-23|2008-04-18|Airbus France Sas|SYSTEM FOR ATTACHING A MOTOR MAT TO THE WING OF AN AIRCRAFT|
    FR2891803B1|2005-10-07|2007-11-30|Airbus France Sas|RIGID STRUCTURE FOR AN AIRCRAFT ENGINE HANDLING MACHINE, AND MATT COMPRISING SUCH A STRUCTURE|
    US9027875B2|2010-10-28|2015-05-12|Spirit Aerosystems, Inc.|Pylon arrangement for open structure|FR3085353A1|2018-09-04|2020-03-06|Airbus Operations|AIRCRAFT TURBOMACHINE ASSEMBLY WITH ARTICULATED HOOD|
    FR3111332A1|2020-06-10|2021-12-17|Airbus Operations |Aircraft mast comprising at least one seal interposed between a fixed structure and a removable panel of a fairing|
    法律状态:
    2019-03-22| PLFP| Fee payment|Year of fee payment: 2 |
    2019-09-27| PLSC| Search report ready|Effective date: 20190927 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 3 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1852459A|FR3079215B1|2018-03-22|2018-03-22|FRONT FAIRING OF AN AIRCRAFT MAST CONSISTING OF A MOBILE COWL AND AIRCRAFT EQUIPPED WITH DUDIT FRONT FAIRING|
    FR1852459|2018-03-22|FR1852459A| FR3079215B1|2018-03-22|2018-03-22|FRONT FAIRING OF AN AIRCRAFT MAST CONSISTING OF A MOBILE COWL AND AIRCRAFT EQUIPPED WITH DUDIT FRONT FAIRING|
    EP19159401.9A| EP3543140A1|2018-03-22|2019-02-26|Front fairing of an aircraft pylon comprising a movable cap and aircraft equipped with said front fairing|
    US16/293,939| US11034458B2|2018-03-22|2019-03-06|Front fairing of an aircraft pylon comprising a mobile shroud and aircraft equipped with said front fairing|
    [返回顶部]