• 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 rotorcraft equipped at its top with a fairing (3) formed below the wing of a main rotor with a substantially vertical axis of the rotorcraft, by wrapping a mechanism for maneuvering the blades of the rotor wing. main. The aerodynamic profile of the fairing (3) is longitudinally shaped truncated water drop at its rear part. The truncation (6) of the waterdrop profile of the shroud (3) forms the rear wall of the shroud (3) and is provided with a boss (7) transversely median. Said boss (7) is provided with protruding reliefs (9) arranged in a longitudinal succession of waves extending along the side walls of the fairing (3) and the truncation (6) is arranged in an inclined plane towards the rear of the rotorcraft.
    公开号:FR3013677A1
    申请号:FR1302743
    申请日:2013-11-27
    公开日:2015-05-29
    发明作者:David Alfano
    申请人:Eurocopter France SA；
    IPC主号:
    专利说明:

    [0001] Ridge fairing of a rotorcraft having a truncated water drop profile with a disturbed surface boss. The present invention is in the field of means for influencing the air flow on the outer surfaces of rotorcraft. The present invention relates more particularly to a fairing conventionally provided at the top of a rotorcraft being disposed under the rotary wing of a main rotor with a substantially vertical axis and in raising a hood surrounding a motorization group of the rotorcraft. A rotorcraft is a rotary wing aircraft (s) comprising one or more rotors, including at least one main rotor with a substantially vertical axis disposed at the top of the rotorcraft. The main rotor provides at least the lift of the rotorcraft, or even in the specific case of a helicopter its propulsion and / or its guidance along any axes of progression. A rotorcraft is also potentially equipped with at least one annex rotor with a substantially horizontal axis. Conventionally, such an auxiliary rotor can be installed at the end of a tail boom to control the attitude of the rotorcraft in yaw. Such an ancillary rotor can also be used to form a propeller propeller of the rotorcraft in translation. The rotor or rotors equipping a rotorcraft are conventionally rotated by a motorization unit comprising at least one combustion engine, including a turbine engine. The motorization group 25 is typically located in the upper part of the rotorcraft below the main rotor wing. A hood is provided around the motorization unit to direct the air flow towards the rear of the rotorcraft and to favor the aerodynamic characteristics of the rotorcraft.
    [0002] Such a hood is commonly enhanced by a fairing enveloping a mechanism for maneuvering the blades of the main rotor wing according to flight commands generated by a pilot of the rotorcraft.
    [0003] For example, such a mechanism for maneuvering the blades of the wing of the main rotor is commonly formed of a pair of trays mounted movably on a mast carrying the wing. The trays are maneuverable by a pilot of the rotorcraft according to various control lines to vary collectively and / or cyclically the pitch of the blades of the wing of the main rotor to change the attitude of the rotorcraft. The hood and the fairing which enhances it extend mainly along a longitudinal dimension extending along the longitudinal extension direction of the rotorcraft 15 conventionally considered between the front and the rear of the rotorcraft on the ground. Of course, the notions of "top", "top", "lower", "bottom" or "up", for example, are commonly understood with respect to the vertical orientation of the rotorcraft on the ground. Similarly, the notions of "vertical plane" 20 and "horizontal plane" of the rotorcraft are commonly accepted with respect to the general vertical and horizontal orientations respectively defining the extension of the rotorcraft considered ground. In this context, it is appropriate to arrange the fairing to best allow it to reduce its aerodynamic drag and to limit the wake that it generates. The arrangement of the fairing must in particular promote the adherence of the air flow along its surface by influencing the swirling phenomena that form at the rear of the fairing. Indeed, vortices form at the rear of the fairing by being a source of drag and causing structural excitations of the outer walls of the rotorcraft and the tail boom extending to the rear of the rotorcraft.
    [0004] A common solution consists in conforming in drop of water the profile of the fairing considered in a horizontal plane of the rotorcraft. However, it appeared that such a solution was not entirely satisfactory for optimizing the stabilization of the rotorcraft in the event of lateral wind, lateral flight and / or in case of skidding of the rotorcraft, particularly with regard to light rotorcraft for which it is sought to promote their maneuverability in flight. More particularly among the constraints relating to the arrangement of the fairing, the flight quality of the rotorcraft must be preserved. In particular, it is necessary to prevent the flow of air along the fairing causing instability of handling and / or disturbing the control of the yaw attitude of the rotorcraft. The noise generated by the flow of air along the outer surfaces of the rotorcraft must also be at best limited.
    [0005] It appears that when the air flows surrounding the rotorcraft comprise a significant lateral vector component, the regularity of the flow of said swirls towards the rear of the fairing is disturbed and consequently the stability of the attitude of the rotorcraft in yaw in is affected.
    [0006] More particularly, the vortices generated at the rear end of the fairing tend to move along the tail boom with a random frequency and direction of flow. Such instability of vortex flow, favored in the event of lateral wind, lateral flight and / or in the event of skidding of the rotorcraft, has the effect of producing undesirable vibrations with respect to the mechanical strength of the rotorcraft. and vis-à-vis the comfort of passengers. In addition, this situation also leads to an increase in noise nuisance and tends to destabilize the yaw behavior of the rotorcraft.
    [0007] To overcome these disadvantages, it is known to truncate transversely the water drop profile of the fairing at its rear end. These provisions are such that in case of side wind, lateral flight and / or slip yaw, the regularity of the vortex flow is improved. However, such a development of the trailing edge of the fairing tends to increase its aerodynamic drag, which is undesirable. Finally, it appears that various specific arrangements of the fairing conformation to improve the flow of air for some cases of theft are unsuitable for other cases of theft. It appears that compromises must be found between various arrangements of the fairing to provide at best a satisfactory air flow whatever the case of flight of the rotorcraft. Furthermore it is known to arrange in an inclined plane, with respect to the horizontal plane of the rotorcraft, the rear wall of the fairing formed by the truncation of its water drop profile. Such provisions are intended to promote guidance of the airflow along the downward fairing of the rotorcraft, recalling that the rotation of the main rotor itself generates a powerful airflow directed towards the aircraft. of the rotorcraft and complex aerodynamic phenomena disturbing the stability of the rotorcraft's behavior in flight. Accordingly, it is desirable that the overall arrangement and specific arrangements of the fairing with respect to airflow along its surfaces also take into account the blast generated by the main rotor. As minor as they may be, the various arrangements of the fairing intended to influence the flow of air along its surfaces and consequently along the organs arranged at the rear of the rotorcraft, interfere in combination with each other on the global conditions of the aircraft. such flow and its effects.
    [0008] Accordingly, choices must be made with respect to the isolated and / or joint operation of the various fairing arrangements to provide airflow to the rear of the rotorcraft deemed to be at best satisfactory.
    [0009] In addition, it is desirable that the arrangement of the fairing is exploitable without major modification regardless of the general configuration of the rotorcraft, to avoid developing a specific conformation of the fairing according to the general structure of the rotorcraft which varies between various families of rotorcraft.
    [0010] It follows a constant search for a fairing conformation favoring an air flow along its outer surface providing results at best satisfactory vis-à-vis the various constraints and requirements mentioned above. Thus, the choice of specific aerodynamic arrangements of the outer surfaces of the fairing must be made in isolation while taking into account the effects produced when they are combined with each other. The present invention is part of such a research and aims to propose a rotorcraft comprising a fairing of the type referred to above at the top of the rotorcraft, the overall arrangement and specific aerodynamic arrangements it provides provide a flow of air towards the rear of the rotorcraft responding satisfactorily to the various problems mentioned above. The rotorcraft of the present invention is provided at its apex with a longitudinally extended fairing along the longitudinal orientation of the rotorcraft. Said fairing envelops a maneuvering mechanism by a pilot of the rotorcraft of the blades of a main rotor with a substantially vertical axis. Such a fairing is conventionally provided below the main rotor wing and enhances a hood surrounding a motorization group of the rotorcraft.
    [0011] The fairing equipping the rotorcraft of the present invention is more specifically selected comprising, considered in a horizontal plane of the rotorcraft, an aerodynamic profile shaped drop of water whose rear end is transversely truncated.
    [0012] According to the present invention, such a fairing equipping the rotorcraft is mainly recognizable in that the truncation formed at the rear of the water drop profile of the fairing comprises a boss disposed in the transversely median zone of the truncation. Such a global organization of the fairing choice not only reduces its aerodynamic drag and limit its wake but also allows to obtain a steady and stable displacement of the eddies generated at the rear end of the fairing, and this including when the airflows surrounding the rotorcraft have a significant lateral vector component. The aerodynamic drag of the fairing is limited by reducing the size of the average detachment of the flow of air flowing along the fairing. The expansion of the swirl zone at the rear of the fairing is reduced and the vortex flow frequency at the rear of the hood is increased with the effect of promoting their dissipation. According to an advantageous embodiment, at least said boss further comprises protruding projections protruding transversely, as arranged in transverse waves arranged successively along the boss. Such reliefs make it possible to disturb the flow of swirling air generating said vortices at the rear of the fairing, to finally further promote the dissipation of the vortices generated. The aerodynamic drag of the fairing is limited.
    [0013] The protruding reliefs are preferably evenly distributed along the boss. However, the localized density of the projections protruding from the boss may be variable according to the overall arrangement of the fairing and the desired effects on the disturbance of said vortex air flow. As an indication, the protruding reliefs are potentially in number between 5 and 15, preferably being formed with a separation pitch between two adjacent protruding reliefs between 0.01 and 3 times the transverse dimension of the fairing considered in the zone. truncation of his profile in drop of water. According to one embodiment, effective results are observed when the transverse dimension of the boss is between 0.2 and 0.4 times the transverse dimension of the truncation. In addition, it appeared that a height of the boss between 0.05 and 0.25 times the longitudinal extension dimension of the fairing gives satisfactory results. According to one embodiment, the boss connection areas at the lateral edges of the truncation are shaped as concave arches with sharp edges at the lateral edges of the truncation. According to another choice of embodiment, the zones of connection of the boss to the lateral edges of the truncation are each double-inflected, said connection areas being successively shaped in concave arc and convex arc leaving rounded edges 25 at the lateral edges of the truncation. More particularly, the boss connection areas at the lateral edges of the truncation preferably each extend for the most part, considered between the concave arches and the lateral edges of the truncation, along a convex arc defined by a truncation. circle centered on the transversely median axis of the truncation.
    [0014] Said circle is preferably chosen with a diameter slightly greater than the transverse dimension of the truncation. According to a preferred embodiment, the rear wall of the fairing, formed by said truncation of the water drop profile of the shroud, is arranged in an inclined plane forming the trailing edge of the fairing. Said inclined plane is advantageously tapered towards the base of the truncation to drain towards the boss the flow of air flowing along the hood. Moreover, the maximum transverse dimension of the truncation is preferably chosen between 0.6 and 0.95 times the maximum transverse dimension of the fairing. According to a preferred embodiment, the protruding reliefs of the boss extend at least along the areas of the truncation laterally bordering the boss, and preferably along the side walls of the fairing. According to a particular embodiment promoting the desired guiding of the air flow along the fairing surfaces, the dimension of the protruding reliefs gradually wears out according to their protruding extension along the zones of the truncation laterally bordering the boss. Then the dimension of the protruding protrusions along their protruding extension increases progressively towards the side walls of the fairing along which the protruding reliefs extend until their dimension following their projecting extension progressively fades towards the front. of the fairing. Embodiments of the present invention will be described in connection with the figures of the attached plates, in which: - Fig.1 is an illustration in side view of the silhouette of a rotorcraft fitted at its top a fairing according to the present invention. - Fig.2 is a top view of a fairing equipping a rotorcraft such as the rotorcraft shown in Fig.1. - Fig.3 is an illustration in rear view of the fairing shown in Fig.2. - Fig.4 is an illustration of the side of the fairing shown in Fig.2 and Fig.3. FIGS. 5 and 6 are diagrammatic illustrations in plan view of fairings in accordance with the present invention, respectively illustrating various variants relating to the connection modalities between a boss and the lateral edges of the rear wall that the fairing comprises. FIGS. 7 and 8 are illustrations of another embodiment of a fairing according to the present invention, respectively in rear perspective for FIG. 7 and in rear perspective view for FIG. . In FIG. 1, a rotorcraft 1 is conventionally equipped with a main rotor 2 with a substantially vertical axis providing at least the lift of the rotorcraft 1, or even its propulsion and / or its guidance along any axes of progression. The rotorcraft 1 20 is also equipped in the upper part with respect to its vertical orientation V of general extension, of a motorization group operated at least for the rotational drive of the main rotor 2. A fairing 3 of protection of a The operating mechanism of the blades of the wing of the main rotor 2 is conventionally arranged in extension of a cover 4 for protecting the power unit. Said fairing 3 is disposed below the wing of the main rotor 2 extending longitudinally along the longitudinal extension direction L1 of the rotorcraft 1, conventionally considered between the front and the rear of the rotorcraft 1 on the ground.
    [0015] The aerodynamic profile of the fairing 3 considered in a horizontal plane P of extension of the rotorcraft 1 is arranged in truncated water drop at its rear end facing the rear of the rotorcraft 1. It follows that the rear wall of the fairing 3 is formed by the truncation 6 formed at the rear of the waterdrop profile of the fairing 3, said truncation 6 extending transversely in the transverse orientation Tg of the rotorcraft 1. In the illustrated embodiment, said truncation 6 is arranged in a plane inclined in a said horizontal plane P of extension of the rotorcraft 1.
    [0016] In fig.2 to fig.8, the truncation 6 of the fairing 3 is provided with a boss 7 transversely median extending in the orientation of the longitudinal extension L2 of the fairing 3. More particularly in FIG. the transverse dimension T1 of the boss 7 is substantially equivalent to the transverse dimensions T2 of the zones 8 of the truncation 6 bordering the boss 7. In the chosen case as illustrated where the truncation 6 is tapered towards its base, the boss 7 is tapered next In these conditions, it is obvious that the relative transverse dimensions T1, T2 between the boss 7 and the zones 8 of the truncation 6 which border it must be considered locally with respect to the truncation. 'other. More particularly for a given transverse dimension T of the truncation 6, the transverse dimension T1 of the boss 7 and the individual transverse dimension T2 of the zones 8 of the truncation 6 which surround it are substantially equivalent and each correspond substantially to one third of the transverse dimension T 6. Furthermore, in FIGS. 2 to 8, at least the boss 7 is provided with protruding reliefs 9 extending in the transverse extension direction Tg of the fairing 3 corresponding to the orientation. of transverse extension of the rotorcraft.
    [0017] Such protruding reliefs 9 disturb the outer surface of the boss 7, in particular being arranged in waves longitudinally successive, as particularly visible in Fig.4. It will be noted that according to the effects specifically provided by the projecting reliefs 9, the wave conformation of the protruding relief profile 9 can be adapted into similar conformations with more or less broken lines. In the exemplary embodiment illustrated, the projecting reliefs 9 are in number between eight and ten being regularly distributed along the boss 7 and being respectively equivalent depths. However, the number, the density, the regularity of the shape of the profile, the regularity of the succession and / or the size of the protruding reliefs 9 may be variable according to the results specifically obtained for fairings whose dimensions vary considerably from one to another. one to another. In FIGS. 5 and 6, the maximum transverse dimension TPmax of the truncation 6 is between 0.6 and 0.95 times the maximum transverse dimension TCmax of the fairing 3. In addition, the height H of the boss 7 is substantially between 0.05 and 0.25 times the longitudinal extension dimension LC of the shroud 3. Furthermore, the connection zones 10a, 10b of the boss 7 at the side edges 11a, 11b of the truncation 6 are potentially differently arranged according to the optimization of the results obtained with respect to the conformation and / or the overall dimensions of the fairing 3.
    [0018] For example in FIG. 5, said connecting zones 10a, 10b are each shaped as a concave arc 12 leaving substantially sharp edges at the lateral edges 11a1b of the truncation 6, so that the rupture of the shape of the rear end fairing 3 formed by the truncation is optimized. For example again in FIG. 6, said connecting zones 10a, 10b are each double-inflated, each being successively concave arc 12 and convex arc 13, so that the edges of the lateral edges 11a, 11b of truncation 6 are significantly rounded. These provisions are such that the breakage of the rear end of the fairing 3 formed by the truncation 6 is softened. More particularly, a major part of each of said connection zones 10a, 10b extends between the concave arc 12 and the lateral edge 11a, 11b of the truncation 6 along a convex arc 13. Said convex arc 13 is defined by a circle C centered, like the boss 7, along the transversely median axis A of the truncation 6. The diameter D of said circle C is slightly greater than the transverse dimension T of the truncation 6.
    [0019] In FIGS. 7 and 8, the protruding reliefs 9 that the boss 7 comprises extend along the zones 8 of the truncation 9 bordering laterally the boss 7, then along the lateral walls 5 of the fairing 3. The dimension projecting reliefs 9 progressively fade along their protruding extension along the zones of the truncation 9 laterally bordering the boss 7. Then the dimension of the projecting reliefs 9 according to their protruding extension increases progressively towards the side walls 5 of the fairing 3 along which protruding reliefs 9 extend until their dimension along their protruding extension progressively fades towards the front of the fairing 3.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. Giravion (1) provided at its apex with a fairing (3) longitudinally extended according to the longitudinal direction (L) of the rotorcraft (1), said fairing (3) enveloping a maneuvering mechanism by a pilot of the rotorcraft (1) blades of a main rotor (2) with a substantially vertical axis being formed below the main rotor blade (2) and raises a hood (4) surrounding a motorization group of the rotorcraft (1), the profile of the fairing (3) considered in a horizontal plane (P) of the rotorcraft (1) being shaped like a drop of water whose rear end is transversely truncated (6), characterized in that the truncation (6) provided in the rear of said profile water drop fairing (3) comprises a boss (7) disposed in transversely median region of the truncation (6).
    [0002]
    2. Giravion according to claim 1, characterized in that at least said boss (7) comprises projecting reliefs (9) transversely extended arranged transverse waves formed successively along the boss (7).
    [0003]
    3. Giravion according to claim 2, characterized in that the projecting reliefs (9) are regularly distributed along the boss (7).
    [0004]
    4. Giravion according to any one of claims 2 and 3, characterized in that the projecting reliefs (9) are formed with a separation step between two projections protruding (9) neighbors between 0.01 and 3 times the transverse dimension (T) of the fairing (3) considered in the truncation zone (5 ') of its droplet profile.
    [0005]
    5. Giravion according to any one of claims 1 to 4, characterized in that the transverse dimension (T1) of the boss (7) is between 0.2 and 0.4 times the transverse dimension (T) of the truncation ( 6).
    [0006]
    6. Giravion according to any one of claims 1 to 5, characterized in that the height (H) of the boss (7) is between 0.05 and 0.25 times the longitudinal extension dimension (LC) of the fairing (3).
    [0007]
    7. Giravion according to any one of claims 1 to 6, characterized in that the connection areas (10a, 10b) of the boss (7) at the side edges (11a, 11b) of the truncation (6) are shaped into arches concave members (12) providing sharp edges at the side edges (11a, 11b) of the truncation (6).
    [0008]
    8. Giravion according to any one of claims 1 to 6, characterized in that the connection areas (10a, 10b) of the boss (7) at the side edges (11a, 11b) of the truncation (6) are each double inflection each being successively shaped concave arc (12) and convex arc (13) providing rounded edges to the side edges (11a, 1 lb) of the truncation (6).
    [0009]
    9. Giravion according to claim 8, characterized in that the connection areas (10a, 10b) of the boss (7) at the side edges (11a, 11b) of the truncation (6) each extend for the most part, considered between the concave arches (12) and the lateral edges (11a, 11b) of the truncation (6), along a convex arc (13) defined by a circle (C) centered on the axis (A) transversely median of the truncation (6), said circle (C) being of a diameter (D) slightly greater than the transverse dimension (T) of the truncation (6).
    [0010]
    10.The rotorcraft according to any one of claims 1 to 9, characterized in that the rear wall of the fairing (3) formed by the truncation (6) of the water drop profile of the shroud (3), is arranged in a inclined plane (6) providing the trailing edge of the fairing (3).
    [0011]
    11. Giravion according to claim 10, characterized in that said inclined plane is tapered towards the base of the truncation (6), the maximum transverse dimension (TPmax) of the truncation (6) being between 0.6 and 0.95 times the maximum transverse dimension (TCmax) of the fairing (3). 10
    [0012]
    12. Giravion according to any one of claims 2 to 11, characterized in that protruding reliefs (9) that comprises the boss (7) extend along the zones (8) of the truncation (6) bordering laterally the boss (7) then along the side walls (5) of the fairing (3). 15
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    同族专利:
    公开号 | 公开日
    PL2878531T3|2016-12-30|
    FR3013677B1|2015-12-04|
    KR20150061581A|2015-06-04|
    EP2878531A1|2015-06-03|
    CN104670505B|2016-08-24|
    CN104670505A|2015-06-03|
    US20150147177A1|2015-05-28|
    KR101731002B1|2017-04-27|
    US9694899B2|2017-07-04|
    EP2878531B1|2016-06-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE1114394B|1956-12-31|1961-09-28|United Aircraft Corp|Low-resistance casing for the rotor shaft or the gearbox between a helicopter fuselage and the rotor head|
    US3331444A|1966-12-28|1967-07-18|Piasecki Aircraft Corp|Fairing assembly|
    US20060269411A1|2005-05-31|2006-11-30|Bertolotti Fabio P|Rotor hub fairing system for a counter-rotating, coaxial rotor system|
    US20110036954A1|2009-08-14|2011-02-17|Piasecki Frederick W|Compound Aircraft with Autorotation|
    US20120104157A1|2010-11-02|2012-05-03|Groen Brothers Aviation, Inc|Rotor driven auxiliary power apparatus and method|
    US2755038A|1952-10-21|1956-07-17|United Aircraft Corp|Helicopter-airplane with engines mounted on fixed wings|
    US3741285A|1968-07-09|1973-06-26|A Kuethe|Boundary layer control of flow separation and heat exchange|
    IT8553439V0|1985-05-30|1985-05-30|Agusta Aeronaut Costr|HELICOPTER|
    US20050151001A1|2003-07-02|2005-07-14|Loper Arthur W.|Compound helicopter|
    EP2238018A2|2008-01-02|2010-10-13|Sikorsky Aircraft Corporation|Planetary de-rotation system for a shaft fairing system|
    KR101016010B1|2009-04-08|2011-02-23|건국대학교 산학협력단|Rotor blade for rotary wing aircraft having deformable protrusions to reduce BVI Noiseblade vortex interaction noise|
    FR2968272B1|2010-12-06|2013-07-12|Eurocopter France|IMPROVED STRUCTURE ELEMENT OF A GIRAVION TO DECREASE AERODYNAMIC TRAINING.|
    CN102642613B|2012-05-11|2014-12-10|中国航空工业集团公司西安飞机设计研究所|Low-resistance fairing of corrugate sheath|US20150048212A1|2013-08-19|2015-02-19|The Boeing Company|Unsteady aerodynamics mitigation for multi-body aerospace apparatus|
    EP3141473B1|2015-09-11|2020-04-15|Sikorsky Aircraft Corporation|Drag reduction of high speed aircraft with a coaxial-rotor system|
    US20170174326A1|2015-12-18|2017-06-22|Sikorsky Aircraft Corporation|Vortex generators and method of creating vortices on an aircraft|
    US10220939B2|2015-12-18|2019-03-05|Sikorsky Aircraft Corporation|Active airflow system and method of reducing drag for aircraft|
    US10232929B2|2015-12-18|2019-03-19|Sikorsky Aircraft Corporation|Plate member for reducing drag on a fairing of an aircraft|
    US10604246B2|2016-01-21|2020-03-31|Sikorsky Aircraft Corporation|Rotorcraft rotor assemblies|
    法律状态:
    2015-11-19| PLFP| Fee payment|Year of fee payment: 3 |
    2016-01-29| CD| Change of name or company name|Owner name: AIRBUS HELICOPTERS, FR Effective date: 20151229 |
    2016-11-18| PLFP| Fee payment|Year of fee payment: 4 |
    2018-08-31| ST| Notification of lapse|Effective date: 20180731 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1302743A|FR3013677B1|2013-11-27|2013-11-27|GIRAVION TOP SIDE COMPRISING A TRUNK WATER DROP PROFILE HAVING A SURFACE SURFACE MISFEED|FR1302743A| FR3013677B1|2013-11-27|2013-11-27|GIRAVION TOP SIDE COMPRISING A TRUNK WATER DROP PROFILE HAVING A SURFACE SURFACE MISFEED|
    PL14003657.5T| PL2878531T3|2013-11-27|2014-10-29|Top fairing of a rotorcraft comprising a truncated teardrop profile having a boss with disrupted surface|
    EP14003657.5A| EP2878531B1|2013-11-27|2014-10-29|Top fairing of a rotorcraft comprising a truncated teardrop profile having a boss with disrupted surface|
    US14/547,586| US9694899B2|2013-11-27|2014-11-19|Rotorcraft top fairing having a profile in the shape of a truncated drop of water that is provided with a hump of uneven surface|
    KR1020140163615A| KR101731002B1|2013-11-27|2014-11-21|A rotorcraft having a top fairing|
    CN201410695780.6A| CN104670505B|2013-11-27|2014-11-26|There is the rotor craft of top commutation cover|
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