• 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 present invention relates to a lift assembly (10) removably attached to a fuselage (5) of a rotorcraft (1). This lift assembly (10) comprises a wing (20) comprising at least two longitudinal members (24, 25). A power transmission (30) passing through a lumen (40) of the extrados (27) of a central box (22) of the wing so that its bottom (31) is attached to a suspension system (50). ) resilient disposed at the intrados (26) of the central box (22), a top (32) of the power transmission gear projecting from said central box (22) and being fixed to at least one spar (24, 25). ) by at least three suspension bars (70). A reversible fastening system (80) provided with a plurality of fastening means (81) reversibly secures said central box (22) at a plurality of fuselage attachment points (5).
    公开号:FR3019522A1
    申请号:FR1400836
    申请日:2014-04-07
    公开日:2015-10-09
    发明作者:Bruno Cacciaguerra
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    [0001] Removable lift set of a rotorcraft and rotorcraft. The present invention relates to a removable lift system of a rotorcraft and a rotorcraft provided with such a lift assembly.
    [0002] A rotorcraft has at least one rotor sometimes referred to as "main rotor" which at least partially ensures the lift of the rotorcraft, or even its propulsion. Such a main rotor can be rotated by a power plant comprising at least one motor and a power transmission box. The gearbox is connected to a hub of the main rotor by a rotor mast and at least one motor by a power transmission kinematic chain. Thus, the engine sets in motion the power transmission gearbox, this power transmission gearbox rotating the main rotor. The power transmission and the engine of a power plant are based on a floor of the aircraft sometimes called "mechanical floor". For example, the power transmission box 20 includes a housing extending in elevation from a bottom to a top. The top can be connected to the mechanical floor through at least three bars sometimes called "suspension bars". In addition, a suspension system may extend between the mechanical floor and the bottom of the power transmission.
    [0003] Such a suspension system may comprise a bar extending between two ends. A laminated damper is disposed between each end of the bar and the power transmission. In addition, a laminated damper is disposed between each end of the bar and the mechanical floor. The shape of the bar explains the familiar name sometimes given to this suspension system, namely "dog bone". Document FR 1507306 describes another suspension system provided with a plate provided with slots. This particular form explains the familiar name sometimes given to this suspension system, namely "barbecue". The mechanical floor can be found at the base of the master-couple of the fuselage of the rotorcraft which tends to degrade the drag of the rotorcraft. Thus, the mechanical floor can also be at least partially integrated in this master-torque to minimize the drag of the rotorcraft. However, this arrangement reduces the ground clearance of the main rotor blades. It may then be difficult to arrange under the main rotor of the rotorcraft propellers involved in particular in the propulsion of the rotorcraft and / or in the control of the yaw movement of the rotorcraft on a rotorcraft equipped with both a rotor and propellers . Indeed, a rotorcraft may be provided with a rotor and propellers 25 arranged on a wing to achieve high forward speeds. Nevertheless, it is understood that the presence of a wing carrying the propellers can be constraining in terms of size, during a transport of the rotorcraft in a ship for example.
    [0004] For example, US 2002/0011539 discloses a rotorcraft with a main rotor and two propellers. These two propellers are respectively fixed on the trailing edge of two half-wings extending transversely on either side of a fuselage. The rotor mast is then very long to avoid contact between the main rotor blades and the propeller blades. Such an arrangement may have a negative impact on the drag generated by the rotorcraft in forward flight.
    [0005] In addition, a wing is usually fixed to the fuselage in a non-removable manner. Document US 2011/0266398 discloses a system for fastening a wing to a fuselage, this fastening system being provided with a plurality of fixing means.
    [0006] RU 2448866 discloses a device for connecting a wing to a fuselage. Document FR 2 935 351 is far removed from the specific technical field of rotorcraft and provides no teaching for this technical field.
    [0007] This document FR 2 935 351 describes an aircraft equipped with a fuselage suspended under a wing carrying a set of empennages and reactors. This architecture aims to improve the situation of transport aircraft vis-à-vis problems of centering and wedging of the wing.
    [0008] This document therefore does not belong to the technical field of the invention, namely the technical field of rotorcraft with high movement speeds.
    [0009] The object of the present invention is therefore to propose a lift assembly intended for such a rotorcraft and capable of having a removable character. According to the invention, a lift assembly of a rotorcraft, intended to be removably attached to a fuselage of a rotorcraft, comprises: a fixed wing comprising successively in a transverse direction a left lift section, a central box for to be attached to a fuselage and a right lift section, said wing comprising at least two longitudinal members extending from the left lift section to the right lift section, said wing extending in elevation from an intrados to an extrados and longitudinally of a leading edge to a trailing edge, a power transmission box extending in elevation from a bottom to an apex, said power transmission box including a mast for rotating a lift rotor, said power transmission box passing through a lumen of the extrados of the central box so that said bottom of said power transmission box is attached a resilient suspension system disposed at the intrados of the central box, said projecting top of said central box, said top being fixed to at least one spar by at least three suspension bars, - a reversible fastening system provided with a plurality of securing means for reversibly securing said central box to a plurality of fuselage attachment points.
    [0010] The lift assembly thus represents a complete module of an aircraft including a wing including a power transmission gearbox adapted to rotate a rotary wing.
    [0011] This lift assembly can be attached to a fuselage using the reversible fastening system. Such a lift assembly makes it possible to design a modular rotorcraft, this rotorcraft having a module comprising a fuselage and a module comprising the lift assembly.
    [0012] This modular design facilitates the transport of the aircraft, particularly by plane or boat. In addition, this design can facilitate the maintenance of the rotorcraft. It is in particular possible to dismantle a lift assembly having failing elements to replace it with another non-defective lift assembly for example. Finally, this design can also tend to optimize the assembly time of a rotorcraft. The lift assembly may further include one or more of the following features.
    [0013] Thus, the wing may comprise for example a leading edge spar and a trailing edge spar. The lift assembly may comprise at least two front suspension bars each fixed by a bracket to the leading edge spar and at least two rear suspension bars each fixed by a fitting to the trailing edge spar. This device aims to optimize the maintenance of the power transmission box to the wing.
    [0014] On the other hand, the central box extending for example transversely from a left side beam to a right side beam, each side beam extending longitudinally from a leading edge spar to a trailing edge spar, each beam lateral member being secured to a reinforcement extending between the lateral beam and one of said leading edge and trailing edge sill members so that the central box delimits a hollow internal space accommodating the bottom of said power transmission box, each said fittings are attached to a spar as well as to a reinforcement and to an intrados panel of the central box. This architecture provides a resistant central box and able to maintain the power transmission box in the required position. In addition, the elastic suspension system may comprise a frame extending longitudinally from a leading edge spar to a trailing edge spar, said elastic suspension system comprising an elastic suspension means interposed between said frame and said background. Thus, the bottom of the power transmission case is carried by a frame, this frame being secured to two longitudinal members to form a strong structure adapted to carry the power transmission box. According to one variant, the elastic suspension means comprises a connecting bar and a support which is fixed to the bottom of the power transmission box, this connecting bar extending between two ends, a laminated damper being disposed between each end and this support as well as between each end and the frame of the elastic suspension system.
    [0015] The elastic suspension means may therefore be a "dog bone". According to another variant, the elastic suspension means comprises a plate provided with slots, the plate being connected to the chassis and the bottom of the power transmission box. The elastic suspension means can be a "barbecue". In addition, the fastening system may comprise at least one pair before fastening means integral with a leading edge spar and at least one rear pair of fastening means integral with a trailing edge spar, each pair having: - a first fixing means for transmitting the forces experienced by said lift assembly following an elevational translation, a transverse translation, a rotation about a longitudinal axis, a rotation about a transverse axis and a rotation around an axis in elevation - a second fastening means for transmitting the forces experienced by said lift assembly following an elevational translation, a rotation about a longitudinal axis, a rotation about a transverse axis and a rotation around it of an axis in elevation. These pairs of fastening means make it possible to secure the wing to a fuselage in translation in two directions and in rotation in three directions. However, the principles of these fasteners and the use of ball joints make it possible to give freedom of movement to the wing relative to the fuselage to allow a slight deformation of the wing under the effect of aerodynamic forces or expansion. thermal for example.
    [0016] Furthermore, the first pair of attachment means may comprise a bracket provided with two upper orifices for fixing it to a spar, and a lower orifice for fixing it to a fuselage, these two upper orifices being aligned in one direction. transverse, an upper orifice being in line with a lower orifice, each orifice cooperating with a ball joint. The second fixing means may comprise an elevated connecting rod provided with an upper bore for attachment to a spar, and a lower piercing for attachment to a fuselage, the upper piercing being in line with the lower piercing, each drilling cooperating with a ball joint. The attachment means of a pair are optionally arranged in the same plane.
    [0017] In addition, the fastening system may comprise at least two longitudinal fasteners, each longitudinal fastener having at least one longitudinal connecting rod for transmitting the forces experienced by said lift assembly following a longitudinal translation, each longitudinal rod being provided with a first passage for its attachment to the central box and a second passage for attachment to a fuselage, each passage cooperating with a ball joint. The longitudinal rods are used to secure the wing to a fuselage in translation in a longitudinal direction.
    [0018] In addition, the lift assembly may comprise a rotor secured to said mast. In particular, the hub of the rotor can be secured to the protruding mast of the power transmission gearbox.
    [0019] The lift assembly may also include means for controlling the rotor blades, such as a set of cyclic trays for example. In addition, the lift assembly may comprise at least one main transmission shaft which is connected to the power transmission gearbox and intended to be rotated by a motor. To connect the power transmission to a motor, it is then sufficient to fix the main transmission shaft to the engine. In addition, the lift assembly may comprise at least one propeller carried by a lift section of the wing, a kinematic chain of secondary transmission connecting the propeller to the power transmission box. This lift assembly can then be arranged on a high speed aircraft. For example, each lift section is equipped with a propeller. In addition, the torque generated by the propellers is advantageously taken up by the wing and not by a fuselage. In addition, each lift section of the wing may comprise at least one rolling means of an undercarriage adapted to rest on a floor. A rolling means may be provided with at least one wheel. Such rolling means favor the stability of a rotorcraft on the ground. The invention also relates to a rotorcraft equipped with a fuselage as well as a fixed wing and a lift rotor, the lift rotor being rotated. by a power transmission gearbox connected to at least one engine.
    [0020] This rotorcraft then has a lift assembly as described above, the lift assembly comprising a wing and a power transmission box and said lift rotor, the lift assembly being fixed to the fuselage reversibly by the fastening system.
    [0021] This lift assembly can be attached to the fuselage using the reversible attachment system described above. Following this assembly, the underside can be in the master-torque of the fuselage to minimize the drag of the rotorcraft. Therefore, the rotorcraft can have a reduced drag.
    [0022] This rotorcraft may include one or more of the following features. This rotorcraft comprises for example at least two longitudinal retaining beams, the central box being in line with the retaining beams and being fixed to the retaining beams respectively by two longitudinal rods. The rotorcraft may comprise at least two support frames extending in elevation, two longitudinal members of the lift assembly being respectively reversibly fixed to the two frames, each beam being fixed to a frame by a pair of fastening means. The invention and its advantages will appear in more detail in the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1, an exploded view of a rotorcraft equipped with a 2, an isometric view showing an elastic suspension means; FIG. 3 an isometric view showing suspension bars; FIG. 4, a diagram showing various members of a lift assembly; FIG. 5, a diagram explaining the fixing of a lift assembly to frames of a fuselage, FIG. 6, a diagram showing a fuselage able to accommodate a lift assembly, FIG. 7, a diagram showing a lift assembly attached to a fuselage, - Figure 8, a view of a rotorcraft according to a first variant, and - Figures 9 and 10, views of a rotorcraft according to a second variant. The elements present in several separate figures are assigned a single reference. Note that three directions X, Y and Z orthogonal to each other are shown in some figures.
    [0023] The first direction X is called longitudinal. The term "longitudinal" is relative to any direction parallel to the first direction X. The second direction Y is said to be transverse. The term "transverse" is relative to any direction parallel to the second direction Y. Finally, the third direction Z is said to be in elevation. The expression "in elevation" relates to any direction parallel to the third direction Z.
    [0024] Figure 1 shows an exploded view of a rotorcraft 1. This rotorcraft 1 comprises a fuselage 5 extending longitudinally from a nose 6 to a rear end 7 carrying empennages and / or fins. In addition, the rotorcraft 1 is provided with a lift assembly 10 that can be reversibly attached to the fuselage 5. This lift assembly includes a wing and a rotor 35 that can at least partially provide lift and / or propulsion of the rotorcraft 1. The wing is described as "fixed" as opposed to the rotor which in essence performs a rotary motion.
    [0025] The wing then extends between two free ends in a transverse direction. More precisely, the wing comprises successively, in this transverse direction, a left lifting section 21, a central box 22 to be fixed to the fuselage 5 and then a right lifting section 23.
    [0026] The wing 20 also extends in elevation from a lower surface 26 to an upper surface 27, and longitudinally from a leading edge 28 to a trailing edge 29.
    [0027] In addition, this wing 20 comprises at least two longitudinal members not visible in Figure 1 which extend from the left lift section 21 to the right lift section 23. For example, the wing has a spar located at its leading edge. referred to as convenience "leading edge spar", and a spar located at its trailing edge called for convenience "trailing edge spar". To put in motion a rotor 35, the lift assembly 10 includes a power transmission gearbox 30 arranged partially in the wing 20, partially projecting from this wing 20. In fact, the gearbox 30 s extends in elevation of a bottom 31 located in the central box 22 to a top 32 protruding in elevation of the central box 22. A mast 33 then protrudes from the top 22 to be secured to a hub 36 carrying a plurality of blades 37. The power transmission gearbox 30 thus rotates the rotor 35 through the mast 33. To attach the power transmission gearbox 30 to the wing 20, the lift assembly 10 includes a plurality of suspension rods 70 and an elastic suspension system 50. Therefore, the suspension system 50 is interposed between the intrados of the central box 22 of the wing 20 and the bottom 31 of the power transmission box 30. FIG. 2 illustrates such a suspension system 50. 2, the central box 22 is delimited longitudinally by a leading edge spar 24 and a trailing edge spar 25, transversely by a left lateral beam 74 and a right lateral beam 75, and in elevation by a panel of FIG. intrados 200 comprising a light. It is noted that ribs of the lift sections can extend from the lateral beams.
    [0028] This central box is open against the upper surface of the wing to be traversed by the power transmission box 30. This central box therefore comprises a light 40. In addition, the central box 22 defines an internal space 10 hollow. This central box 22 may comprise reinforcements 76 giving this internal space a hexagonal cylinder shape. Indeed, the central box may comprise four reinforcements 76. Each reinforcement 76 then extends between a side beam and a spar. As a result: a first reinforcement is fixed to the left lateral beam and the leading edge spar, a second reinforcement is fixed to the left lateral beam and the trailing edge spar, a third reinforcement is fixed to the right side beam and the leading edge spar, a fourth reinforcement is attached to the right side beam and the trailing edge spar, Thus, the elastic suspension system 50 comprises a frame 51.
    [0029] This frame 51 can extend at the level of the intrados under the intrados panel 200. This frame is adapted to carry a fixing means for fixing the lift assembly to the fuselage. In particular, this frame 51 may comprise two longitudinal beams 52 extending longitudinally from the leading edge spar 24 to the trailing edge spar 25, and two transverse beams 54 extending transversely between the longitudinal beams 52. The elastic suspension system 50 comprises an elastic suspension means 55 opposite the light of the intrados panel. This elastic suspension means 55 is thus interposed between the frame 51 and the bottom 31 of the power transmission gearbox. According to the variant of Figure 2, the elastic suspension means 55 is of the "dog bone" type. Thus, the elastic suspension means 55 comprises a connecting bar 56 and a support 59 which is fixed to the bottom 31 of the power transmission box. Therefore, the connecting bar 56 extends between two ends 57. A laminated damper 58 is then disposed between each end 57 and the support 59, and between each end 57 and the frame 51. Nevertheless, the suspension means can also be a "barbecue" with a relaxed plate with slots. The plate is then connected to the chassis 51 and to the bottom 31 of the power transmission box 30. With reference to FIG. 1, the lift assembly 10 also comprises a plurality of suspension bars 70. to connect the top 32 of the power transmission gearbox 30 to the wing 20.
    [0030] Referring to Figure 3, each suspension bar 70 can be fixed by a bracket 73 to a spar, or even to a reinforcement 76 and a panel intrados. Thus, each fitting may comprise a horizontal intrados face secured to the intrados panel, a first elevation face secured to a reinforcement 76, a second elevation face secured to a spar, and a third elevation face connected directly or indirectly to a suspension bar 70.
    [0031] For example, two front suspension bars 71 are each fixed by a bracket 73 to the leading edge spar 24 and at least two rear suspension bars 72 are each fixed by a bracket 73 to the trailing edge spar 25. Referring in Figure 4, the lift assembly may comprise at least one propeller 62 carried by a lift section of the wing. For example, two propellers 62 may be carried respectively by the left lift section 21 and the right lift section 23. At least one propeller may be disposed at the trailing edge of the wing according to the representation in solid lines, or at the level the leading edge of the wing according to the dotted line representation. Therefore, the lift assembly may comprise at least one main transmission shaft 60 connected to the power transmission box 30. Each power transmission shaft may protrude from the wing, and favorably from its trailing edge, to be secured to a motor 61 secured to the fuselage of the rotorcraft.
    [0032] In addition, the power transmission gearbox 30 can drive each propeller through a secondary transmission kinematic chain 620 connecting each propeller 62 to the power transmission gearbox 30. For example, each secondary drivetrain drive chain 620 passes through a lateral beam 74, 75 of the central box 22 to reach the power transmission box 30. With reference to Figure 1, the lift assembly may also include at least one rolling means 65 of a landing gear.
    [0033] For example, each lifting section 21, 23 of the wing 20 comprises at least one rolling means 65. In addition, the lift assembly is provided with a fastening system 80 for reversibly securing the lift assembly 10 to the fuselage 5.
    [0034] Such a fastening system 80 is then provided with a plurality of fixing means 81 fixing the central box 22 at several attachment points 100 of a fuselage 5, for example by means of ball joints. With reference to FIG. 3, the fastening system 80 has, for example, two pairs of fixing means 81 fastened respectively to two longitudinal members. Thus, a front pair 82 of securing means 81 is integral with a leading edge spar 24, and a rear pair 83 of securing means is integral with a leak edge spar 25. Each pair includes a first fixing means 84 for transmitting to the fuselage the forces experienced by the lift assembly following an elevational translation, a transverse translation, a rotation about a longitudinal axis, a rotation about a transverse axis and a rotation around a longitudinal axis; an axis in elevation. This first fixing means 84 is then for example provided with a square. This bracket is thus provided with two upper orifices 86 each connected to the same spar by a ball joint. The two upper ports 86 are aligned in a transverse direction. In addition, the bracket is provided with a lower orifice 87 fixed to a point of attachment of a support frame 8 of a fuselage 5 by a ball joint for example. An upper orifice 86 is in line with a lower orifice 87 in a direction in elevation called "direction of elevation". In addition, each pair of attachment means comprises a second attachment means 85 for transmitting to the fuselage the forces exerted by the lift assembly as a result of an elevational translation, a rotation about a longitudinal axis, a rotation about a transverse axis and a rotation about an axis in elevation. This second fixing means 85 comprises an elevated connecting rod provided with an upper bore 88 to be fixed to a spar by means of a ball joint for example. In addition, the lift rod has a lower bore 89 to be attached to a point of attachment of a support frame 8 of a fuselage 5 for example. The upper bore 88 is in line with the lower bore 89 in a direction in elevation parallel to the direction of attachment in elevation.
    [0035] With reference to FIG. 5, the fixing means 81 of a pair are arranged in the same plane P1, P2, this plane extending in a direction in elevation and a transverse direction. two longitudinal fasteners, each longitudinal attachment having at least one longitudinal connecting rod 90 for transmitting to the fuselage the forces experienced by the lift assembly as a result of a longitudinal translation, each longitudinal connecting rod is provided with a first passage for attachment to the central box, for example The first passage may be connected to a fitting of a chassis carrying the suspension system of the power transmission gearbox, and each longitudinal link is provided with a second passage for be fixed to a point of attachment of a support beam 9 of a fuselage 5, for example by a ball joint, such a support beam can connect two retaining frames 8. From then on, the intrados of the central box can rest above these retaining beams.
    [0036] With reference to FIG. 6, the aircraft can comprise two pairs before 82 of fastening means 81. Therefore, two first fastening means before 84 can grip a fitting of a front frame 8 'of the fuselage and a fitting of a front spar of the wing.
    [0037] Similarly, two first rear fastening means 84 can enclose a fitting of a rear frame 8 "of the fuselage and a fitting of a rear spar of the wing.
    [0038] In addition, two second front attachment means 85 may enclose a fitting of a front frame 8 'of the fuselage and a fitting of a front spar of the wing. Referring to FIG. 6, two second rear attachment means 85 may enclose a fitting of a rear frame 8 "of the fuselage and a fitting of a rear spar of the wing, and each longitudinal attachment may comprise two longitudinal rods 90. FIG. 7 shows a lift assembly thus fixed to the fuselage 5. More specifically, FIG. 7 partially presents the lift assembly and the fuselage so as not to weigh down this FIG. 7, and to reveal certain means of attachment. FIG. 8 shows a view of a rotorcraft according to a first variant, according to this first variant, the central box is not contained in the master torque of the fuselage, the intrados of the central box forming a mechanical floor is in this case located Figure 8 further demonstrates the presence of hoods 20 on the lift assembly, and Figures 9 and 10 show views of a rotorcraft according to a second According to this second variant, the central box is contained in the master torque of the fuselage to minimize the drag of the rotorcraft. Consequently, the power transmission gearbox, the engines, and the central casing of the fixed wing are installed substantially in the geometrical casing of the fuselage, which makes it possible to minimize the master-torque of the engine hoods. Regardless of the variant, the rotorcraft undercarriage may be sized to ensure the presence of an acceptable ground clearance between the propellers and the ground, and an acceptable rotor guard 300 between the rotor and the propellers. Thus, the main rotor is favorably installed as close as possible to the ground, while respecting the constraints of guard to the rotor and ground clearance, to optimize the drag of the rotorcraft. This undercarriage may comprise the bearing means of the lift assembly, and conventional means carrying the fuselage. These rolling means are favorably arranged, if necessary, under the nacelles of the propellers of the lift assembly. For example, the introduction of a tricycle train on the fuselage and two rolling means on the wing makes it possible to confer on the rotorcraft a high lateral stability, or even to make accessible the floor of a cabin for the operations of the aircraft. help. The undercarriage can also include a tandem train 20 arranged under the fuselage, such a train comprising a front gear and a main gear which are aligned. Whatever the variant, the rotorcraft is stable laterally on the ground, and can land on a sloping ground in a crosswind. In addition, the propeller propellers are installed on the wing to ensure, for example, control of the yaw movement of the rotorcraft and participate in the propulsion of the aircraft.
    [0039] Their position can be determined to favor winching operations and lateral access to a cabin on the ground. In particular, the arrangement of a propeller at the trailing edge of the wing seems well suited to meet this need.
    [0040] In addition, this position at the rear of the wing avoids the air flow of the propellers to disrupt the flow of air around the wing, and thus reduces the drag of the wing. In addition, the noise radiated by the propellers to the cabin can be reduced. In addition, the cabin may be away from ice projections and / or debris created by the propellers. Moreover, such a rotorcraft may exhibit good performance during hovering flight, since the main rotor can thus have a large diameter. In addition, the architecture of the rotorcraft seems not very complex 15 compared to aircraft equipped with tilting rotors, for example, which may tend to limit its cost. Naturally, the present invention is subject to many variations as to its implementation. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (18)
    [0001]
    REVENDICATIONS1. Lift assembly (10) of a rotorcraft (1) intended to be removably attached to a fuselage (5) of a rotorcraft (1), characterized in that the lift assembly (10) comprises: - a wing (20) ) comprising successively in a transverse direction a left lift section (21), a central box (22) intended to be fixed to a fuselage (5) and a right lift section (23), said wing (20) comprising at least two spars (24, 25) extending from the left lift section (21) to the right lift section (23), said wing (20) extending in elevation from a lower surface (26) to an upper surface (27) and longitudinally of a leading edge (28) to a trailing edge (29), - a power transmission box (30) extending from a bottom (31) to a top (32), said box power transmission (30) comprising a mast (33) for rotating a lift rotor (35), said power transmission gearbox ance (30) passing through a lumen (40) of the extrados (27) of the central box (22) so that said bottom (31) of said power transmission box (30) is attached to a suspension system (50) resilient disposed at the intrados (26) of the central box (22), said top (32) projecting from said central box (22), said top being fixed to at least one spar (24, 25) by at least three bars suspension system (70); - a reversible fastening system (80) provided with a plurality of fastening means (81) for reversibly securing said central box (22) at a plurality of fuselage attachment points (100); ).
    [0002]
    2. A lift assembly according to claim 1, characterized in that said flange (20) comprising a leading edge spar (24) and a trailing edge spar (25), said lift assembly (10) comprises at least two front suspension bars (71) each secured by a bracket (73) to the leading edge spar (24) and at least two rear suspension bars (72) each secured by a bracket (73) to the trailing edge spar (25).
    [0003]
    3. A lift assembly according to claim 2, characterized in that said central box (22) extending transversely from a left side beam (74) to a right side beam (75), each side beam (74, 75) s extending longitudinally from a leading edge spar (24) to a trailing edge spar (25), each lateral beam (74, 75) being integral with a reinforcement (76) extending between the lateral beam (74, 75) and one of said leading edge (28) and trailing edge (29) longitudinal members for the central box (22) delimits a hollow internal space accommodating the bottom (31) of said transmission box. power (30), each of said fittings (73) being attached to a spar (24, 25) as well as a reinforcement (76) and a lower panel (26) of the central box (22).
    [0004]
    4. Lift assembly according to any one of claims 1 to 3, characterized in that said elastic suspension system (50) comprises a frame (51) extending longitudinally of a leading edge spar (24) to a trailing edge spar (25), said elastic suspension system (50) comprising an elastic suspension means (55) interposed between said frame (51) and said bottom (31).
    [0005]
    5. lift assembly according to claim 4, characterized in that said elastic suspension means (55) comprises a connecting bar (56) and a support (59) which is fixed to said bottom (31), said connecting bar (56). ) extending between two ends (57), a laminated damper (58) being disposed between each end (57) and said support (59) and between each end (57) and said frame (51).
    [0006]
    6. Lift system according to claim 4, characterized in that said elastic suspension means (55) comprises a plate provided with slots, the plate being connected to said frame (51) and said bottom (31).
    [0007]
    7. A lift assembly according to any one of claims 1 to 6, characterized in that said fastening system (80) comprises at least one front pair (82) of fastening means (81) integral with an edge sill (24) and at least one rear pair (83) of fastening means integral with a trailing edge sill (25), each pair having: - a first fastening means (84) for transmitting the forces experienced by said lift assembly (10) following an elevational translation, a transverse translation, a rotation about a longitudinal axis, a rotation about a transverse axis and a rotation about an axis in elevation - a second fixing means (85) for transmitting the forces experienced by said lift assembly following an elevational translation, a rotation about a longitudinal axis, a rotation about a transverse axis and a rotation about an axis in elevation.
    [0008]
    8. A lift assembly according to claim 7, characterized in that the first attachment means (84) of a pair comprises a bracket provided with two upper holes (86) for attachment to a spar (24, 25), and a lower port (87) for attachment to a fuselage (5), said two upper ports (86) being aligned in a transverse direction, an upper port (86) being in line with a lower port (87) each orifice (86, 87) cooperating with a ball joint.
    [0009]
    9. Lift system according to any one of claims 7 to 8, characterized in that the second fastening means (85) comprises an elevated connecting rod provided with an upper bore (88) for attachment to a spar (24, 25), and a lower bore (89) for attachment to a fuselage (5), the upper bore (88) being in line with the lower bore (89), each bore (88, 89) cooperating with a ball joint.
    [0010]
    10. A lift assembly according to any one of claims 7 to 9, characterized in that the fastening means (81) of a pair are arranged in the same plane (P1, P2).
    [0011]
    11. lift system according to any one of claims 7 to 10, characterized in that said fastening system (80) comprises at least two longitudinal fasteners, each longitudinal attachment 25 having at least one longitudinal rod (90) for transmitting the forces suffered by said lift assembly following a longitudinal translation, each longitudinal rod being provided with a first passage for its attachment to the central box, and a second passage for attachment to a fuselage, each passage cooperating with a ball joint.
    [0012]
    12. A lift assembly according to any one of claims 1 to 11, characterized in that said lift assembly (10) comprises a rotor (35) secured to said mast (33).
    [0013]
    Load-bearing assembly according to any one of claims 1 to 12, characterized in that said lift assembly (10) comprises at least one main transmission shaft (60) which is connected to the power transmission gearbox (30) and intended to be rotated by a motor (61).
    [0014]
    14. A lift assembly according to any one of claims 1 to 13, characterized in that said lift assembly (10) comprises at least one propeller (62) carried by a lift section (21, 23) of the wing (20). a secondary transmission kinematic chain (620) connecting said propeller (62) to the power transmission gearbox (30).
    [0015]
    15. Lift assembly according to any one of claims 1 to 14, characterized in that each lifting section (21, 23) of the wing (20) comprises at least one rolling means (65) of a landing gear adapted to rest on a floor.
    [0016]
    16. Giravion (1) provided with a fuselage (5) and a fixed wing (20) and a lift rotor (35), said destilentation rotor (35) being rotated by a gearbox power unit (30) connected to at least one motor (61), characterized in that said rotorcraft (1) comprises a lift assembly (10) according to any one of claims 1 to 15, said lift assembly (10) comprising said wing (20) and said power transmission box (30) and said lift rotor, said lift assembly (10) being fixed to said fuselage (5) reversibly by said attachment system (80).
    [0017]
    17. Giravion according to claim 16, characterized in that said rotorcraft (1) comprises at least two longitudinal retaining beams (9), said central box (22) being in line with said retaining beams (9) and being fixed said support beams (9) respectively by two longitudinal rods (90).
    [0018]
    18. Giravion according to any one of claims 16 to 17, characterized in that said rotorcraft (1) comprises at least two retaining frames (8) extending in elevation, two longitudinal members 20 (24, 25) of said lift assembly. (10) being respectively reversibly attached to the two support frames (8), each spar (24, 25) being attached to a support frame by a pair of fastening means.
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    同族专利:
    公开号 | 公开日
    FR3019522B1|2016-05-20|
    US20150284076A1|2015-10-08|
    US9738379B2|2017-08-22|
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    法律状态:
    2015-03-19| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-21| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-19| PLFP| Fee payment|Year of fee payment: 4 |
    2018-04-20| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-18| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1400836A|FR3019522B1|2014-04-07|2014-04-07|REMOVABLE SUSTAINABLE ASSEMBLY OF A GIRAVION AND GIRAVION|FR1400836A| FR3019522B1|2014-04-07|2014-04-07|REMOVABLE SUSTAINABLE ASSEMBLY OF A GIRAVION AND GIRAVION|
    US14/675,985| US9738379B2|2014-04-07|2015-04-01|Removable lift assembly for a rotorcraft, and a rotorcraft|
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