• 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 spreader (1) comprises an actuating assembly comprising two actuating assemblies (6A, 6B) each provided with two pedals (12AD, 12AG, 12BD, 12BG), each actuating assembly (6A, 6B) having a frame (14) provided with two rails (15, 16) arranged on either side of said frame (14) and having a concave curve shape, and associated with each of said rails (15, 16), a movable carriage (17 ), each of said mobile carriages (17) carrying one of said pedals (12AD, 12AG, 12BD, 12BG), each of said movable carriages (17) being configured to be movable on the associated rail (15, 16), for a steering control, under an action exerted by at least one foot of a pilot on at least one of said pedals (1 2AD, 12AG, 1 2BD, 12BG).
    公开号:FR3045006A1
    申请号:FR1562207
    申请日:2015-12-11
    公开日:2017-06-16
    发明作者:Bernard Guering；Laurent Saint-Marc
    申请人:Airbus Operations SAS；
    IPC主号:
    专利说明:

    TECHNICAL AREA
    The present invention relates to a so-called curvilinear beam for an aircraft, in particular for a transport aircraft, and an aircraft comprising such a curvilinear lifter.
    On an aircraft, a rudder is a mechanical device that allows the pilot and co-pilot to control the rudder and the wheel brakes.
    The lifter includes pedals and a set of moving parts which, depending on the types of movements that are applied to the pedals by the pilot (s), control the rudder or the brakes of the aircraft.
    STATE OF THE ART
    The rudders used on aircraft, are mainly on the lifter air line integrated into the cockpit floor and even through it. The rudder is said posed because it rests on the floor of the cockpit.
    Attachment of the rudder and the transmission of rudder controls to the rudder and / or brakes are carried out under the floor of the cockpit. This architecture is the consequence of a choice to communicate, in the case of a lifter mechanically connected to the elements to be controlled (in particular the control surface), by the zone under floor (links by connecting rods, rotating sectors and cables), this which is more easily achievable on an aircraft.
    For its operation, the spreader must include a large number of parts (joints, rods, pivots, ...).
    Such a standard lifter, particularly because of this high number of parts, is complex and is not optimal especially in terms of size, weight and cost.
    This usual solution is not completely satisfactory. STATEMENT OF THE INVENTION
    The present invention provides a new rudder architecture that overcomes this disadvantage. It relates to a lifter for an aircraft, said lifter comprising at least one actuator assembly provided with two pedals.
    According to the invention, said actuation assembly comprises: at least one chassis, said chassis being provided with two rails, each of said rails having a concave curve shape; and - associated with each of said rails a movable carriage, each of said mobile carriages carrying one of said pedals, each of said mobile carriages being configured to be movable on the associated rail, for steering control, under an action exerted by at least a foot of a pilot on at least one of said pedals.
    Thus, thanks to the invention, and in particular to this frame provided with curved (or curvilinear) rails on which the movable carriages carrying the pedals can be moved, a simplified architecture with a reduced number of parts is obtained, as specified below. . This architecture has advantages in particular in terms of size, weight and cost, which overcomes the aforementioned drawback.
    Preferably, said frame has a generally elongate shape, and / or is provided with structural tubes, preferably of carbon-based composite material.
    In addition, advantageously, each of said mobile carriages is connected to a jack arranged along (and preferably above) the associated rail.
    In one embodiment, each of said mobile carriages is provided with a set of rollers rotatably mounted and configured to be able to move on the associated rail.
    Furthermore, advantageously, said actuation assembly includes an adjustment assembly that is configured to allow an operator to modify the neutral positions of the pedals.
    In addition, advantageously, said actuation assembly also comprises a hydraulic hose reel.
    In addition, advantageously, said frame is provided with a fixing assembly, said fixing assembly comprising two connecting rods orthogonally fixed to each other at one end, said front end of the frame, and a connecting fitting provided with a stiffening rod, attached to the other end, said rear end of the frame.
    In addition, in a particular embodiment, each of said pedals is rotatably mounted on the associated mobile carriage for brake control. Advantageously, each of said pedals is connected to a hydraulic cylinder and a connecting arm forming an articulated triangle.
    Furthermore, advantageously, said actuation assembly comprises hydraulic fluid transfer devices, for at least one of the following commands: a steering control and a brake control.
    In a preferred embodiment, for an aircraft capable of being piloted by two pilots, the lifter comprises two actuation assemblies, one being intended for a first pilot and the other for a second pilot, the two sets being actuators being connected together at least by conjugating means.
    The present invention also relates to an aircraft, in particular a transport aircraft, which is provided with a spreader such as that specified above.
    In a preferred embodiment, for an aircraft comprising a cockpit equipped with a floor, said chassis is positioned so that its rear end, located rearward with respect to the direction of flight of the aircraft, overhangs the floor of the cockpit.
    In addition, advantageously, said frame is fixed at its front end via two connecting rods arranged orthogonally with respect to each other to at least one support element, and at its front end via a connecting fitting to a cross-member of the floor of the cockpit, the connecting fitting being provided with a stiffening rod.
    BRIEF DESCRIPTION OF THE FIGURES
    The appended figures will make it clear how the invention can be realized. In these figures, identical references designate similar elements. More particularly: FIG. 1 shows a plane on the ground which comprises a spreader according to one embodiment of the invention; FIGS. 2 and 3 are two perspective views, looking respectively from the rear and from the front, of a cockpit of an aircraft provided with a rudder according to one embodiment of the invention ; - Figure 4 schematically shows different possible adjustment positions of a pedal of a rudder; - Figures 5 and 6 are perspective views, respectively in a mounted position and in an exploded position, an actuator assembly of a spreader; and FIGS. 7A and 7B are two views, respectively in perspective and in plan, of a curvilinear beam.
    DETAILED DESCRIPTION
    Figure 1 shows an aircraft AC, in this case a transport aircraft, which comprises a cockpit 2, in which is arranged a spreader 1 according to the invention (as shown very schematically in this Figure 1). The aircraft AC also includes a rudder 3 and brakes 4 at the wheels 5 of a main landing gear of the aircraft AC.
    Figures 2 and 3 show a spreader 1 according to a preferred embodiment of the invention, which is arranged in the cockpit 2 of the aircraft AC (shown very partially).
    More specifically, there is shown in Figures 2 and 3, schematically and stripped, a dashboard 7 provided with a support structure 8 and a set of 9 screens or displays 10A, 10B, 10C and 10D usual of the cockpit 2.
    In the context of the present invention, the "back" and "forward" directions are defined with respect to the longitudinal direction of the aircraft AC, namely for "forward" as illustrated in FIG. 3 by an arrow E1 towards the front of the aircraft AC (in the direction of an arrow E2 in Figure 1) and for "rear" as shown in Figure 2 by the arrow E3 to the rear of the aircraft AC.
    Moreover, in the context of the present description, the terms "lower", "upper" and "high" are defined in a vertical direction Z which is orthogonal to a horizontal plane of the aircraft defined by the floor 13 (FIG. 2).
    Moreover, to facilitate the description, there is shown in Figures 2 and 7A a reference R (XYZ) having: - a longitudinal direction X along the longitudinal axis of the aircraft; the vertical direction Z, the vertical direction Z forming, with the horizontal direction X, a plane XZ which is parallel to a vertical plane of symmetry of the aircraft; and a lateral direction Y orthogonal to said directions X and Z, the lateral direction Y forming, with the direction X, an XY plane which is parallel to the floor 13 of the control cabin 2 (FIG. 2).
    The rudder 1 shown in Figures 2 and 3, which is intended for a conventional transport aircraft, is likely to be controlled by two pilots, a main pilot and a co-pilot.
    To do this, the lifter 1 comprises two pairs of pedals 11A and 11B, respectively part of actuating assemblies 6A and 6B.
    A first pair of pedals 11A (of the actuating assembly 6A) arranged to the left looking forward, is for the pilot of the aircraft. This pair 11A comprises two pedals 12AD and 12AG intended to be actuated by the two feet, respectively right and left, of the pilot.
    The second pair of pedals 11B (of the actuating assembly 6B) arranged on the right is for the co-pilot of the aircraft. This pair 11B includes two pedals 12BD and 12BG to be operated by the two feet, respectively right and left, of the co-pilot.
    The lifter 1 therefore comprises two actuating assemblies 6A and 6B. Each of said actuating units 6A and 6B, one of which is therefore intended for the pilot of the aircraft and the other is intended for the co-pilot, is thus provided with a pair 11A, 11B of pedals.
    According to the invention, each of said actuating assemblies 6A and 6B further comprises, as shown in Figures 2 and 3: - at least one frame 14. The frame 14 is provided with two rails 15 and 16 arranged on both sides. another of said frame 14, each of said rails 15 and 16 having a concave curve shape; and - associated with each of said rails 15 and 16, a movable carriage 17. Each of said movable carriages 17 carries one of said pedals 12AG, 12AD, 12BG, 12BD. In addition, each of said movable carriages 17 is configured to be movable on the associated rail 15, 16, for steering control, under an action exerted by a foot of a pilot on the associated pedal, as specified below.
    Thus, thanks in particular to this chassis 14 of the curved (or curvilinear) type, on which the two mobile carriages 17 carrying the pedals of an actuating assembly 6A, 6B can move, we obtain a simplified pedals 1 architecture with a reduced number of pieces, as specified below. This architecture has advantages in particular in terms of size, mass and cost.
    In a preferred embodiment, the entire frame 14 is elongated and has a generally concave curve shape.
    To do this, each frame 14 is fixed in the XZ plane by presenting a general direction along X while being curved (or curved) concavely in the XZ plane so that the rear end 14B of the frame 14 (overlooking the floor 13 placed on the usual structural elements 41 (Figure 2)) deviates from said floor 13 vertically upwards in the direction Z.
    This curvature has the advantage of being able to position the most ergonomically possible pedals according to the size of the drivers. Indeed, in a cockpit, the position of the pilots is defined vis-à-vis the ice frame (external visibility) and vis-à-vis the dashboards (angles of internal visibility). As a result, a large pilot has a lower seat-sitting position as well as more depressed pedal positions and, from an ergonomic point of view, these pedals need to be positioned more vertically than for a small pilot. way to ensure a natural angle between the legs and the feet. Conversely, a small pilot is positioned higher on the seat and the pedals require to be positioned more horizontally. A pilot of average size, meanwhile, need pedals positioned between the extreme values. In a conventional articulated mechanical lifter, these different positions are obtained precisely by a complex kinematic positioning of the pedals via a deformable parallelogram recaling the pedals precisely according to the ergonomics (the size mainly) pilots. This usually complex function is performed very simply in the curvilinear rudder: it is the simple curvature of the curvilinear rudder which ergonomically positions the mobile set of pedals in a manner adapted to the users.
    In addition, as shown in Figure 5, the frame 14 is provided with structural tubes 18 and 19, preferably of carbon composite, which thus have a reduced mass and a high mechanical strength.
    In the particular embodiment shown in Figure 5, the frame 14 comprises two structural tubes 18 and 19 of square or rectangular cross section, which are fixed longitudinally (in the plane XZ) against each other.
    The frame 14 also comprises longitudinally, on either side, structural tubes 18 and 19 a side plate 20, 21 serving as a support for the guide rail 15, 16.
    This chassis 14 of the curvilinear type has a high mechanical strength and an ability to cash in large forces, due to the presence of structural tubes of high carbon composite section, and especially to the absence of lever arm effect. The forces are in fact exerted in direct action near the connecting or guiding elements, as opposed to a conventional pendulum (or articulated) type architecture.
    In the preferred embodiment described above, the two rails intended for a pilot are carried by a single frame. Alternatively, it is also possible to provide a chassis per rail.
    In this particular embodiment, each of said mobile carriages 17 comprises a structure 22 of rectangular or square type, provided with four rollers 23 arranged at the corners of this structure 22, for example at the corners 24 as shown in FIG.
    These rollers 23 are rotatably mounted and configured to be able to move on the associated rail 15, 16. The four rollers 23 are mounted so as to be able to roll on the chassis 14, namely two rollers on the upper face and two rollers on the lower face. The rollers 23 are held on the frame 17 via the side plate 20, 21 which projects relative to the upper part and to the lower part of the associated structural tube 18, 19.
    The frame 14 thus comprises rolling rollers 23 and rails 15, 16 with a guide flange, preferably made of metal, for example aluminum with a hard metal rolling zone.
    The guidance by rollers, including the carriage 17, provides accurate and reliable guidance, with a game adjustment. The actuating assembly 6A, 6B further comprises, associated with each movable carriage 17, an auxiliary structure 25 which has a similar structure (to the structure 22) provided with four rollers 23. The auxiliary structure 25 is connected to the movable carriage 17 via a hydraulic cylinder 26, as shown in Figure 5 (or Figure 6 which is an exploded view of Figure 5). The auxiliary structure 25 is arranged at the front end of the rail.
    The hydraulic jack 26 is arranged along the rail 15, 16, and more precisely, along and above the corresponding structural tube 18, 19 of the rail 15, 16. The hydraulic cylinder 26 is thus connected by one of its ends to the auxiliary structure 25 (at the front of the rail). The hydraulic cylinder 26 is further linked, by the other of its ends, to an axis of rotation 30 of the pedal, specified below. This contributes in particular to the simplicity and compactness of the actuation assembly. The actuation of a pedal, for example 12AG, in the direction illustrated by an arrow F1 in FIG. 3, under the action of a pressure exerted by the pilot via his foot, causes the moving carriage 17 to move relative to to the auxiliary structure 25, in the direction indicated by an arrow F2. This displacement towards the auxiliary structure 25 generates a compression of the associated hydraulic cylinder 26, as illustrated by an arrow F3. The amplitude of this compression is used to determine the direction control order.
    Conversely, a release of the action generated by the foot of the driver, causes a displacement of the movable carriage 17 in the opposite direction to the direction illustrated by the arrow F1, under the action of the jack 26 if it was previously compressed.
    The two hydraulic cylinders 26 of an actuating assembly 6A, 6B are connected together via a hydraulic transmission (not shown) so that the movement of a movable carriage 17 in one direction, for example forward for that carrying the 12AG pedal as shown by the arrow F1 in Figure 3, causes the movement of the other carriage in the other direction, for example rearward for the movable carriage 17 carrying the pedal 12AD as illustrated by an arrow F4 on the FIG. 3. Actuation of the movable carriage 17 carrying the pedal 12AG according to the arrow F1, illustrating a steering control action, thus generates an opposite operation of the movable carriage 17 carrying the pedal 12AD according to the arrow F4, due to an extension of the corresponding hydraulic cylinder 26, as illustrated by an arrow F5 in FIG.
    Moreover, in the example shown in FIGS. 2 and 3, for an aircraft piloted by two pilots, the four hydraulic cylinders 26 (namely a hydraulic cylinder 26 associated with each of said four pedals 12AG, 12AD, 12BG, 12BD) intended at the steering control, are linked together so that: - the two pedals of each pair of pedals are controlled in the aforementioned manner, in the opposite direction; and the two pairs of pedals are controlled, in a symmetrical manner, so that the pedals intended for one of the pilots, the co-pilot, for example, are always in the same position as those intended for the other pilot.
    Thus, the displacement of the mobile carriages of an actuating assembly, for example the actuating assembly 6A, under the action of the pair of associated pedals, generates the same displacement of the mobile carriages of the other set of actuators. actuation (actuating assembly 6B in this example), resulting in a similar displacement of the other pair of pedals.
    Furthermore, each actuating assembly 6A, 6B includes an adjustment assembly (not shown), which preferably comprises an adjustment and locking rack, and which is configured to allow an operator to change the neutral position (not actuated). ) 12DA, 12GA, 12DB, 12GB pedals on their respective chassis.
    The neutral position of a pedal is the position of the pedal when the driver does not press it.
    This set of adjustment allows to approach or move the pedals of the pilot seat to adapt this set to the size of the driver, who will use it.
    FIG. 4 shows three different positions P1, P2 and P3 of a pilot leg that can correspond to three drivers of different sizes. The actuation assembly can be positioned by the adjustment assembly so that the neutral position of the pedals adapts to the feet for each of these positions P1, P2 and P3. To do this, the mobile assembly comprising in particular the movable carriage 17 and the auxiliary structure 25 can be moved, in one or the other of the directions illustrated by the double arrow H.
    The curvilinear yoke 1 which has a curved concave type, is favorable to a small pilot, as opposed to a convex type of rudder, because the curvature at its rear end 14B is naturally approaching its feet (away from the floor as indicated above).
    In addition, said actuating assembly 6A, 6B also comprises a winder 27 (shown very schematically, in FIG. 3 in particular) of hydraulic hose (s), for winding and unwinding a variable length of hose ( s) hydraulic (s), to adapt this or these to the position of the actuating assembly, in particular when changing the position as mentioned above. These hydraulic hoses are used for hydraulic transmission, for steering or braking control.
    On the other hand, as further illustrated by way of illustration for the pedal 12AG in FIG. 5, each pedal is rotatably mounted at a lower end 29 about the axis of rotation 30 for braking control.
    Thus, when the pilot presses with his foot on the pedal 12AG at the upper end 31 as shown by an arrow G1 in Figure 5, the pedal 12AG pivots about the axis 30 as shown by an arrow G2, and generates a compression of a hydraulic cylinder 32 associated as shown by an arrow G3. This hydraulic cylinder 32 associated is mounted in an articulated manner, firstly to the upper part 31 of the pedal 12AG, and secondly to a connecting arm 34. The linkage arm 34 is mounted, articulated, d firstly to the axis 30 and secondly to the lower end of the hydraulic cylinder 32. The link arm 34, the hydraulic cylinder 32 and the pedal 12AG thus form a triangle whose vertices are articulated, which allows in particular to simplify the whole. The braking order is determined by the displacement of the axis of the hydraulic cylinder 32 (linear inductive sensor for example), generated by the actuation of the pedal 12AG. In addition, a transfer of fluid, generated by this actuation, is used to conjugate in the same position the equivalent pedal of the second pilot, in order to indicate in real time to the second pilot the braking tendency, to avoid that the In case of assistance, it does not slow down in opposition.
    In a preferred embodiment, the braking and steering functions are thus implemented by hydraulic fluid transfer devices.
    Alternatively, the braking and steering functions can also be implemented by conventional means articulated rods and other joints.
    Furthermore, said frame 14 is provided with a fixing assembly 35 comprising at least two connecting rods 36 and 37 and a connecting fitting 38.
    In the particular embodiment shown in FIGS. 7A and 7B, each chassis 14 is fixed to the front 14A via the two connecting rods 36 and 37 which are connected to structural elements of the aircraft (not shown). , preferably being positioned at right angles. The rod 36 is positioned in the vertical direction Z and the rod 37 is positioned in the lateral direction Y, as can be seen in FIG. 7A in particular.
    In addition, the frame 14 is fixed towards its rear end 14B through the connecting fitting 38 which is connected, for example, to a cross member 39 (shown schematically) of the floor. This connecting fitting 38 is arranged at a distance from the rear end 14B of the frame 14. The fixing assembly 35 is furthermore provided with a stiffening rod 40. One 40A of the ends 40A and 40B of the stiffening rod 40 is fixed under the frame 14 and the other end 40B is connected to the connecting fitting 38. This stiffening connecting rod 40 allows, in particular mechanically reinforcing the frame 14. It allows in association with the fitting of link 38 to block the movements of the assembly of the rudder in the longitudinal direction X.
    This produces a semi-aerial isostatic mounting. FIGS. 7A and 7B show, by arrows, the reactions at the level of the structural recoveries, namely: a reaction FX in the direction X, at the level of the connecting fitting 38; - FY1 and FY2 reactions in the Y direction, respectively at the connecting rod 37 and the connecting fitting 38; and - reactions FZ1, as well as FZ2 and FZ3, in the direction Z, respectively at the connecting rod 36 and the connecting fitting 38.
    The lifter 1 also comprises usual means (not shown) to implement the usual functions of a lifter relating to the following parameters: control, conjugation, sensors, signals.
    The lifter 1 thus comprises in particular common means for generating the command corresponding to the actuation of the pedals. In particular, the lifter may comprise a steering sensor (not shown) which is configured to measure the direction and amplitude of the pedal movement of an actuation assembly, following a pilot action on the pedals. The steering sensor conventionally transforms the mechanical control representative of the movement of the mobile carriages into an electrical signal. This electrical signal is then routinely transmitted to a steering system (not shown) of the rudder 3 (Figure 1) to control the direction of the aircraft.
    The lifter also includes a transmission assembly that is configured to transmit a displacement, when a pedal is rotated about the axis of rotation 30 (Figure 5). For this purpose, the transmission assembly is connected to a brake control unit (not shown). When the transmission assembly is controlled, it transmits a mechanical control to the brake control unit which converts this mechanical control into an electrical signal, which electrical signal is then transmitted to an activation system (not shown) configured to activate the brakes 5 of the aircraft AC (Figure 1). The motion transmission assembly for controlling the braking may comprise means of different types, such as an inductive linear sensor or a rotary articulated arm sensor for example.
    The description above, which has been made mainly with reference to a single pedal, applies to each of the pedals of the rudder 1 and their associated means.
    The rudder 1, as described above, thus has a simplified architecture. This architecture does not include articulated elements. The movements are obtained by rolling on a curvilinear rail. This architecture is simple and light, and it allows to increase the race without real limitation, while offering us a strong mechanical resistance. In addition, this lifter can be installed on any aircraft, particularly because of its simple positioning. In addition, it retains the same features as a conventional lifter.
    The operation of the rudder 1, as described above, to control the direction of the aircraft is as follows.
    When a driver's foot moves the pedal 12AG from a neutral position, as illustrated by the arrow F1 in FIG. 3, the movement of the pedal 12AG and the mobile carriage 17 on which it is mounted causes the compression of the jack 26 (illustrated by the arrow F3).
    The compression of the jack 26 is transmitted to the direction sensor. The direction sensor transforms the detected mechanical control into an electrical signal that is transmitted to the rudder steering system to control the direction of the aircraft.
    Compared to a conventional lifter, the lifter 1 has substantially identical ergonomics and functionalities.
    Alternatively, more conventional architectures are feasible on a curvilinear type of chassis as described above, but the fluid transfer architectures have the greatest simplicity of integration. The architecture of the rudder 1, as described above, has many advantages. In particular: this architecture frees the floor from the specific constraints of the lifter, ensuring a simplification of the floor, as well as the possibility of making a module of the whole of it, and it includes an integration generating a large volume gain; - it has a simplified implementation and uses fewer parts. This gives a gain in mass and a significant simplification; - It also has a facilitated integration of the rudder and associated elements, especially in a semi-overhead mode with a rear portion slightly overhanging the floor; it has a small footprint, and a reduced cost; it retains substantially the same functionalities and ergonomics as a conventional lifter; - the pedal stroke is adaptable and more important, and it is concave, which favors a small pilot, without penalizing a great driver; it has a discrete number of connection points (isostatic mounting); and - it generates evolutionary trajectories (because it is not linked mechanically to a pendulum effect around a point of rotation).
    权利要求:
    Claims (13)
    [1" id="c-fr-0001]
    1. Lifter for an aircraft, said spreader (1) comprising at least one actuating assembly (6A, 6B) provided with two pedals (12AD, 12AG, 12BD, 12BG), characterized in that said actuating assembly (6A , 6B) comprises: - at least one frame (14), said frame (14) being provided with two rails (15, 16), each of said rails (15, 16) having a concave curve shape; and - associated with each of said rails (15, 16) a movable carriage (17), each of said mobile carriages (17) carrying one of said pedals (12AD, 12AG, 12BD, 12BG), each of said mobile carriages (17) being configured to be movable on the associated rail (15, 16) for steering control under an action of at least one foot of a pilot on at least one of said pedals (12AD, 12AG, 12BD, 12BG ).
    [2" id="c-fr-0002]
    2. Lifter according to claim 1, characterized in that said frame (17) has a generally elongate shape.
    [3" id="c-fr-0003]
    3. Lifter according to one of claims 1 and 2, characterized in that each of said mobile carriages (17) is connected to a jack (26) arranged along the associated rail (15, 16).
    [4" id="c-fr-0004]
    4. beam according to any one of the preceding claims, characterized in that each of said movable carriages (17) is provided with a set of rollers (23) rotatably mounted and configured to be movable on the rail (15, 16). associated.
    [5" id="c-fr-0005]
    5. Lifter according to any one of the preceding claims, characterized in that said frame (17) is provided with structural tubes (18, 19).
    [6" id="c-fr-0006]
    A lifter according to any one of the preceding claims, characterized in that said actuating assembly (6A, 6B) includes an adjustment assembly which is configured to allow an operator to modify the neutral positions of the pedals (12DA, 12GA , 12DB, 12GB).
    [7" id="c-fr-0007]
    7. beam according to any one of the preceding claims, characterized in that said frame (14) is provided with a fixing assembly (35), said fixing assembly (35) comprising two connecting rods (36, 37) fixed orthogonally relative to one another to one (14A) of the ends, said front end, of the frame (14), and a connecting fitting (38) provided with a stiffening rod (40), fixed to the other end, said rear end (14B) of the frame (14).
    [8" id="c-fr-0008]
    8. Lifter according to any one of the preceding claims, characterized in that each of said pedals (12DA, 12GA, 12DB, 12GB) is rotatably mounted on the associated carriage (17) for a brake control.
    [9" id="c-fr-0009]
    9. Lifter according to claim 8, characterized in that each of said pedals (12DA, 12GA, 12DB, 12GB) is connected to a hydraulic cylinder (32) and a connecting arm (34) forming an articulated triangle.
    [10" id="c-fr-0010]
    10. Lifter according to any one of the preceding claims, characterized in that said actuating assembly (6A, 6B) comprises hydraulic fluid transfer devices, for at least one of the following commands: a steering control and a braking command.
    [11" id="c-fr-0011]
    11. Aircraft, characterized in that it comprises a spreader (1) such as that specified in any one of claims 1 to 10.
    [12" id="c-fr-0012]
    12. Aircraft according to claim 11, comprising a cockpit (2) provided with a floor (13), characterized in that said frame (14) is positioned so that its rear end (14B), located towards the rearward relative to the direction of flight (E2) of the aircraft (AC), overlooking the floor (13) of the cockpit (2).
    [13" id="c-fr-0013]
    13. Lifter according to claim 12, characterized in that said frame (14) is fixed at its front end (14A) via two rods (36, 37) arranged orthogonally relative to each other to at least one element of structure, and at its rear end (14B) via a connecting fitting (38) to a crossbar (39) of the floor (13) of the driving cabin (2), the connecting fitting (38) being provided with a stiffening rod (40).
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    EP0923017A1|1999-06-16|Foot-controlled device for a system such as a braking assistance system of a vehicle
    同族专利:
    公开号 | 公开日
    CN107031821B|2021-11-09|
    US10399667B2|2019-09-03|
    US20170166296A1|2017-06-15|
    CN107031821A|2017-08-11|
    FR3045006B1|2018-01-12|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3359821A|1965-10-11|1967-12-26|Lockheed Aircraft Corp|Connecting mechanism between a control lever and multiple controlled members|
    US5056742A|1987-11-13|1991-10-15|The Boeing Company|Modular rudder pedal and brake control assembly for aircraft|
    EP1918195A1|2006-11-06|2008-05-07|Honeywell International Inc.|Rudder pedal assembly with non-parallel slide rails|
    WO2014138014A1|2013-03-08|2014-09-12|Woodward, Inc.|Multiple degrees of translational adjustment pedals|EP3572320A1|2018-05-22|2019-11-27|Airbus Operations SAS|Rudder bar with single-piece mobile main module on a curved supporting frame|US1333535A|1918-07-06|1920-03-09|Bopp Charles William|Clutch-lever-lock device|
    US2420528A|1944-10-24|1947-05-13|Curtiss Wright Corp|Rudder pedal assembly|
    US3576302A|1968-07-10|1971-04-27|Bendix Corp|Solid-state position sensor for sensing an adjusted position of a control element|
    US4484722A|1982-06-30|1984-11-27|The United States Of America As Represented By The Secretary Of The Air Force|Translating rudder pedal system|
    DE3638820C2|1986-09-12|1989-03-16|Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De|
    FR2721120B1|1994-06-10|1996-08-23|Guillaume Pierre Vincent Feral|Vehicle of the motor vehicle or airplane type capable of being driven or piloted by a handicapped person of the lower limbs.|
    US5878981A|1997-04-14|1999-03-09|Dewey; Daniel L.|Flight console for radio controlled aircraft|
    US8353484B2|2009-11-10|2013-01-15|Textron Innovations, Inc.|Cockpit rudder control mechanism for an aircraft|
    FR2956756B1|2010-02-23|2012-08-24|Airbus Operations Sas|PERFECTED RESISTIVE TORQUE GENERATING DEVICE|
    CN103303462B|2012-03-09|2015-08-05|陕西飞机工业（集团）有限公司|A kind of Vertical spindle foot control system|
    US20140131523A1|2012-11-09|2014-05-15|Mason Electric Co.|Above-the-floor rudder and brake control system|
    CN103587679B|2013-11-28|2015-11-18|江西洪都航空工业集团有限责任公司|Mechanical type airplane tread regulating mechanism|
    US9581226B2|2015-05-26|2017-02-28|Woodward Mpc, Inc.|Barrel cam rudder pedal system|
    FR3039505B1|2015-07-27|2018-05-04|Airbus Helicopters|ADJUSTABLE AND ROTARY ROTARY FOR A ROTATING AIRCRAFT|
    FR3042776B1|2015-10-23|2019-05-17|Airbus Operations|SUSPENDED PALONNIER FOR AIRCRAFT AND AIRCRAFT COMPRISING SUCH A SUSPENDED PALONNIER.|
    US10017242B2|2016-01-29|2018-07-10|The Boeing Company|Aircraft rudder pedal lockout assemblies systems and methods|
    FR3049573B1|2016-04-05|2019-05-10|Airbus Operations|AIRCRAFT CONTROL COMPRISING AN IMPROVED PEDAL|FR3039505B1|2015-07-27|2018-05-04|Airbus Helicopters|ADJUSTABLE AND ROTARY ROTARY FOR A ROTATING AIRCRAFT|
    FR3081438A1|2018-05-22|2019-11-29|Airbus Operations|MONOBLOC AND REMOVABLE PEDAL MODULE FOR AIRCRAFT SPOILER.|
    FR3081437A1|2018-05-22|2019-11-29|Airbus Operations|PALLET FOR AIRCRAFT WITH MAIN MONOBLOCK AND REMOVABLE MODULE.|
    CN109229345B|2018-09-25|2021-11-02|陕西飞机工业（集团）有限公司|Airplane foot control mechanism for preventing false braking|
    CN113460288B|2021-09-03|2021-12-10|中国商用飞机有限责任公司|Active rudder foot pedal assembly for controlling aircraft and aircraft|
    法律状态:
    2016-12-22| PLFP| Fee payment|Year of fee payment: 2 |
    2017-06-16| PLSC| Publication of the preliminary search report|Effective date: 20170616 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 3 |
    2018-12-19| PLFP| Fee payment|Year of fee payment: 4 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |
    2020-12-23| PLFP| Fee payment|Year of fee payment: 6 |
    2021-12-24| PLFP| Fee payment|Year of fee payment: 7 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1562207A|FR3045006B1|2015-12-11|2015-12-11|CURVILIGNE PALONNIER FOR AIRCRAFT AND AIRCRAFT COMPRISING SUCH A CURVILIGNE PALONNIER.|
    FR1562207|2015-12-11|FR1562207A| FR3045006B1|2015-12-11|2015-12-11|CURVILIGNE PALONNIER FOR AIRCRAFT AND AIRCRAFT COMPRISING SUCH A CURVILIGNE PALONNIER.|
    US15/370,037| US10399667B2|2015-12-11|2016-12-06|Curvilinear rudder bar for an aircraft and aircraft comprising such a curvilinear rudder bar|
    CN201611129142.3A| CN107031821B|2015-12-11|2016-12-09|Curved rudder foot peg for aircraft and aircraft comprising same|
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