• 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:
    - Suspended lifter for aircraft and aircraft comprising such a suspended lifter. - The spreader (1) comprises a set of so-called primary joints (15) comprising pedals (12), a set of so-called secondary joints (17) comprising control and synchronization means and various equipment, and a set ( 25) generating functional and structural links between the set of primary joints (15) and the set of secondary joints (17), said set of primary joints (15) being configured to be suspended at least one structure support member (8) of the flight cockpit of the aircraft, and said set of secondary joints (17) being configured to be suspended from at least one structural member of an area located at the 'before the cockpit.
    公开号:FR3042776A1
    申请号:FR1560116
    申请日:2015-10-23
    公开日:2017-04-28
    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 suspended lifter for an aircraft, in particular for a transport aircraft, and an aircraft comprising such a suspended 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 pedals used on aircraft, are pedals integrated into the floor of the cockpit and passing 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.
    Once the location of the spreader is established (spreader mounted), it is necessary to integrate the own volume of the pedals which is important, leaving in the cockpit only features specific to the ergonomics of pilots.
    This conventional lifter architecture, poses a strong constraint for the structural floor of the front part of the cockpit with a large footprint, and it leads to a complex floor, due in particular to the presence of the housing required for the rudder, this which is particularly incompatible with a modular type structure.
    This 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 spreader for an aircraft comprising a cockpit equipped with a dashboard and a so-called forward zone which is located at the front with respect to the cockpit, the dashboard comprising a support structure, said lifter comprising a set of so-called primary joints comprising pedals, a set of so-called secondary joints, and an assembly generating functional and structural links between the set of primary joints and the set of secondary joints.
    According to the invention, said pedals are configured to be suspended and are configured to be able to be suspended at least at the support structure of the cockpit control panel, and at least some of the secondary links of said set of secondary joints are configured to be suspended and are configured to be capable of being suspended from at least one structural element of the front zone.
    Preferably, said set of primary joints is configured to be suspended and is configured to be able to be suspended at least from the support structure of the cockpit control panel, and said set of secondary links is configured to be suspended and is configured to be able to be suspended at least said structural element of the front zone.
    Thus, thanks to the invention, instead of being fixed on the floor, the lifter is suspended, that is to say without contact with the floor, and this in front of the cockpit. The lifter thus has no relationship with the floor, while having the same functionality as a conventional lifter as specified below. This architecture generates a saving of space on the floor of the cockpit and facilitates in particular the establishment of a modular structure, which overcomes the aforementioned drawback.
    In a particular embodiment, said set of primary joints comprises, for each pedal, a pedal arm to which the pedal is connected, the pedal arm being rotatably mounted on a structural element, said structural element being configured to be suspended, and it is configured to be able to be suspended at least to the support structure of the dashboard of the cockpit.
    In addition, advantageously, said set of secondary joints comprises a steering shaft mounted for rotation about a steering axis, the steering shaft being connected via at least one link to a steering position sensor.
    Furthermore, advantageously, said set of functional and structural link generation comprises: for each pedal, a connecting rod, the connecting rod being connected by one of its ends, in an articulated manner, to one end of an arm of pedal and the other of its ends, in an articulated manner, at one end of a steering shaft; and / or - at least one fixed structural link.
    In addition, advantageously, the spreader is provided with two pairs of pedals and a steering torque rod, the steering torque rod being configured to transmit an actuation of a pair of pedals to the other pair of pedals. Preferably, the steering torque rod is hingedly connected to the two transmission shafts associated with the two pairs of pedals, respectively.
    In addition, in a particular embodiment, each of said pedals is mounted on a pedal arm and each of said pedal arms is in the form of a shell.
    Furthermore, advantageously, the lifter comprises a set of adjustment which is configured to allow an operator to change the positions and strokes of the pedals.
    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, said set of primary joints is suspended at least from the support structure of the cockpit of the cockpit of the aircraft, and said set of secondary joints is suspended at least one element. structural aspect of the front zone.
    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. 2A and 2B are two views, respectively in perspective and in lateral view, of a front structure of an aircraft, provided with a spreader according to one embodiment of the invention; - Figure 3 is a schematic plan view of a lifter suspended from a dashboard; - Figure 4 shows a side view of a spreader according to one embodiment of the invention; - Figure 5 is a partial view, in perspective, of a spreader according to one embodiment of the invention; - Figure 6 shows a side view similar to that of Figure 4 to show effects of a pedal operation; - Figure 7 schematically shows different possible adjustment positions of a pedal and a pedal arm of a rudder; and - Figures 8 and 9 show, respectively, left and right parts of a rudder for explaining actions generated by the actuation of a pedal.
    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.
    FIGS. 2A and 2B show an integration of a spreader 1 according to a preferred embodiment of the invention, in the cockpit 2 of the aircraft AC and in a front zone 6 (which is situated in front of the aircraft AC relative to the cockpit 2).
    These FIGS. 2A and 2B show schematically and stripped part of the structure of the cockpit 2 and the front zone 6.
    FIGS. 2A and 2B show an instrument panel 7 provided with a support structure 8 and a set 9 of screens or displays 10A, 10B, 10C and 10D which are customary (FIG. 3) of FIG. cockpit 2, which are arranged at the rear of the support structure 8 of the dashboard 7.
    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. 2B by an arrow E1 towards the front of the aircraft AC and for "rear" as illustrated by the arrow E2 towards the rear of the aircraft AC.
    The lifter 1 shown in Figure 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 11 B.
    A first pair of pedals 11A arranged to the left looking forward, is for the pilot of the aircraft. This pair 11A comprises two pedals 12DA and 12GA intended to be actuated by the two feet, respectively right and left, of the pilot.
    The second pair of pedals 11B arranged on the right is for the co-pilot of the aircraft. This pair 11B comprises two 12DB and 12GB pedals intended to be operated by the two feet, respectively right and left, of the co-pilot.
    The spreader 1 is fixed, suspended, above the floor 14 of the cockpit 2, being secured to a part of the support structure 8 of the dashboard 7 and secondly to minus one structural element 16 of the front zone 6 (FIG. 2B).
    To do this, the lifter 1 comprises a first set of so-called primary joints 15, which includes in particular the two pairs of pedals 11A and 11B, one of which is intended for the pilot of the aircraft and the other is intended for to the co-pilot.
    This set of primary joints 15 is configured to be suspended from the support structure 7 of the dashboard 8.
    The lifter 1 also comprises a second set of joints 17 said secondary, comprising control and synchronization means, and various equipment, as specified below.
    This set of secondary joints 17 is configured to be suspended, in particular, to the structural element 16 of the front zone 6.
    The two sets of joints 15 and 17 are connected together, as specified below, through a transmission assembly 25 (Figure 4) specified below.
    The rudder 1 thus comprises: - the set of primary joints 15 (pedals and adjustment means), which is mounted on the support structure 8 of the dashboard 7; the set of secondary joints 17 (controls, synchronization, equipment), which is mounted on a rear face of a flat structural waterproof bottom of the front zone 6; and - the transmission assembly 25 which forms functional and structural links between two sets 15 and 17.
    This architecture, with a fixation of all the elements of the rudder 1 above the floor 14 of the cockpit, frees up space and facilitates its installation, compared to a conventional architecture type lifter type.
    The lifter 1 is suspended type (or hung), thus being partially integrated into the support structure 8 of the dashboard 7, and the functions of the rudder are distributed in two areas: the dashboard and the front zone provided with a structural background. All functions are retained, as specified below.
    The rudder uses a new space created on modern aircraft and untapped. Indeed, the new generation of instruments and dashboard display, through the passage of cathode-ray tubes to flat screens, releases a large volume on the other side of the dashboard at the zone level. before 6 (FIGS. 2A and 2B). This space is difficult to exploit by another system. It allows, on the other hand, to integrate the rudder which thus uses an available space.
    As shown in FIG. 4, the set of primary joints 15 comprises, for each pedal 12 (for example the pedal 12GA), a pedal arm 19, to which the pedal 12 is connected.
    For steering control, this pedal arm 19 is rotatably mounted on a structural element 20 (FIG. 5) about an axis of rotation 21.
    The pedal arm 19, of elongate shape, is in the form of a shell. It has a lower end 22 and an upper end 23 which extend, substantially vertically, on either side of the axis of rotation 21. The lower end 22 is oriented towards the floor relative to the axis of rotation. rotation 21.
    In the context of the present description, the terms "lower", "upper", "high" and "low" are defined in a vertical direction which is orthogonal to a horizontal plane defined by the floor.
    Furthermore, in a usual manner, for a braking command, the pedal 19 is rotatably mounted on the lower end 22 about an axis of rotation 24. This axis of rotation 24 is parallel to the axis of rotation 21 , and it is spread from the latter down towards the floor. The transmission assembly 25 of the rudder 1 is configured to in particular transmit a displacement, from the set of primary joints 15 to the set of secondary joints 17, when the pedal arm 19 pivots about the axis of rotation 21.
    As shown in FIG. 5, the upper end 26 of the lever arm 19 is hingedly connected to a first end 27 of a connecting rod 28. This connecting rod 28 is connected by its other end 29 in an articulated manner to an upper end 31 of a steering shaft 32.
    As shown in Figure 8, the steering shaft 32 is rotatably mounted about a steering axis 33 which is vertical. The steering shaft 32 is mounted in its upper part 31 in a structural bearing 34 specified below. This structural bearing 34 is fixed to the structural element 16 of the front zone 6 of the aircraft (FIG. 2B). The end 29 of the connecting rod 28 is mounted, in an articulated manner, to a hinge member 35 which is fixed to the upper end 31 of the steering shaft 32 and which accompanies it in its rotation, as shown in FIG. FIG. 8. This articulating element 35 comprises two brackets 36 and 37 extending on either side of the rotation shaft 32 in a (horizontal) plane substantially perpendicular to the axis of rotation 33. In each stirrups 36 and 37 are mounted, rotatably, the end 29 of a connecting rod 28, one of which is associated with one of the two pedals of a pair of pedals and the other of which is associated with the other pedal of this pair of pedals.
    Furthermore, the structural bearing 34 comprises two parallel plates 38 and 39 (Figures 5 and 8), positioned substantially horizontally and intended to be fixed on the structural element 16 of the front zone 6 (Figure 2B).
    Furthermore, the steering shaft 32 is mounted in its lower portion 40 in a bearing not shown.
    In addition, this steering shaft 32 is connected via a rod 41 to a steering position sensor 42. This rod 41 is arranged substantially orthogonal to the steering axis 33.
    In the example shown, the rod 41 is mounted, in an articulated manner, at one end on a projecting portion 43 integral with the steering shaft 32 and at the other end with a connecting means 44, for example in the form of stirrup, which is integral with the steering position sensor 42, as can be seen in particular in FIG. 8.
    The steering position sensor 42 is configured to measure the direction and the amplitude of the rotation of the steering shaft 32. This rotation is generated by an action of a pilot on a pedal.
    More specifically, the transmission assembly 25 allows: - the rotation of the pedal arm 19 around the axis of rotation 21 (by the actuation of the pedal 12) in one direction, causes the rotation of the rotation shaft direction 32 in a first sense; and - the rotation of the pedal arm 19 about the axis of rotation 21 (by the actuation of the pedal 12) in the opposite direction, causes the rotation of the steering shaft in a second direction opposite to said first direction.
    The steering position sensor 42 transforms, in the usual way, the mechanical control representative of the rotation of the steering shaft 32 into an electrical signal. This electrical signal is then routinely transmitted to a steering system (not shown) of the rudder to control the direction of the aircraft.
    In addition, the pedal arm 19 is connected to a braking link 46, as shown in FIG.
    The lifter 1 also comprises a transmission assembly not shown and arranged in part at a localized area by an arrow 45 in Figure 4. This transmission assembly is configured to transmit a displacement when the pedal 12 pivots around the rotation axis 24. For this purpose, the transmission assembly is connected to a brake control unit (not shown). When the transmission assembly is maneuvered, it transmits a mechanical command to the brake control unit which converts this mechanical control into an electrical signal, this electrical signal then being transmitted to an activation system (not shown) configured to activate the brakes 5 of the aircraft AC (Figure 1).
    The description above, which has been made with reference to a single pedal, applies to each of the pedals of the rudder 1 and their associated means.
    The rudder 1 further comprises, between the rods 28 associated respectively with the two pedals of the same pair of pedals, a fixed structural rod 48, as shown in FIG. 5. This structural rod 48 contributes to the holding of the strut structure. support 8 and the maintenance of the spreader 1. The support structure 8 comprises a plurality of support plates 49, for example of generally triangular shape, which have articulations that are coaxial with an axis of rotation 30. These support plates 49 are fixed in such a way protruding perpendicularly to the support structure 8 towards the front of the aircraft. They serve to support the set of primary joints 15 on the support structure 8.
    The operation of the rudder 1, as described above, to control the direction of the aircraft is as follows.
    When a driver's foot depresses the pedal 12 from a neutral position, as illustrated by an arrow F1 in FIG. 6, the movement of the pedal 12 causes the pedal arm 19 (illustrated by an arrow F2) to rotate around it. of the axis of rotation 21. The neutral position is the position of the pedal 12 when the driver does not press on said pedal 12.
    The rotation of the pedal arm 19 generates a lateral displacement of the connecting rod 28 (as illustrated by an arrow F3) which, when moving, drives the steering shaft 32 in rotation, via the articulation element 35 (which turns as shown by an arrow F4 in Figure 8). The rotation of the steering shaft 32 (illustrated by an arrow F5) is transmitted to the direction detection sensor 42, via the rod 41 which moves in the direction of an arrow F6. The direction sensor 42 transforms the detected mechanical control into an electrical signal that is transmitted to the rudder steering system to control the direction of the aircraft.
    Furthermore, the spreader bar 1 also comprises an adjustment assembly 50 which makes it possible to move the pedal arm 19 at the articulation (provided with the axis of rotation 21), as represented in FIG. 4, and thus approaching or removing the pedals from the pilot's seat.
    This adjustment element 50, which preferably comprises a manual screw jack or an electric jack 51, thus makes it possible to modify the positions and the strokes of the pedals and to adapt them to the pilot. In FIG. 7, three different positions P1, P2 and P3 are represented (with the corresponding axes of rotation 21, 24 and 55).
    Compared to a conventional lifter, the lifter 1 has substantially identical ergonomics and functionalities.
    Furthermore, the spreader 1 which is provided with two pairs of pedals and associated means, also comprises a rod 53 (steering conjugation) which allows to transmit an actuation of a pair of pedals (pilot or co-pilot) to the other pair of pedals, as shown in Figures 8 and 9, being hingedly connected to the transmission shafts 32 respectively associated with these pairs.
    This connecting rod 53 is articulated at both ends, each time, to a support member 54 in the form of a stirrup. Each support element 54 is integral with a steering shaft 32.
    Thus, the rotation of a steering shaft 32 under the action of the pair of associated pedals, generates, via the connecting rod 53, the same rotation of the other steering shaft, resulting in a similar displacement of the other pair of pedals.
    More specifically, the rotation of a steering shaft 32 under the action of the pair of associated pedals (generating the displacements F3 and F3A of the connecting rods 28 of FIG. 8) around the steering axis 33 as illustrated by FIG. arrow F5 (FIG. 8), generates the displacement of the connecting rod 53 in the direction illustrated by an arrow F7 in FIGS. 8 and 9. This displacement rotates the other steering shaft 32 as illustrated by an arrow F8 in FIG. 9. This rotation F8 generates the displacement of the rods 28 associated with this steering shaft 32, in opposite directions illustrated by arrows F9A and F9B, which causes the rotation of the corresponding pedal arms and the movement of the pedals, illustrated by arrows F1 OA and F1OB.
    Moreover, the set of secondary joints 17 of the spreader 1 also comprises, as represented in FIG. 5: a member 55 of the type PDFU relating to a dynamic brake; and an element 56 of the PFTU type provided with a law of effort. The architecture of the rudder 1, as described above, has many advantages. In particular: - this architecture completely 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 significant volume gain ; it does not require a structural casing because of the multifunctionality of the structural parts of the dashboard, the front structural base and the rudder; - it has a simplified implementation and uses fewer parts. This gives a gain in mass and a significant simplification; - it has a reduced cost; it retains substantially the same functionalities and ergonomics as a conventional lifter; - The main elements are made in the form of shell, namely the pedal arm and the hinge parts on the dashboard. These elements can in particular be manufactured by 3D printing; - the pedal stroke is adaptable; and braking functions can be performed in the usual manner. However, they are preferably carried out by fluid transfer, which ensures significant gains.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Lifter for an aircraft, said aircraft (AC) comprising a cockpit (2) provided with a dashboard (7) and a so-called forward zone (6) located in front of the cockpit (2), the dashboard (7) comprising a support structure (8), said spreader (1) comprising a set of so-called primary joints (15) comprising pedals (12), a set of so-called secondary joints (17), and an assembly (25) generating functional and structural links between the primary joint assembly (15) and the secondary joint assembly (17), characterized in that said pedals (12) are configured to be suspended and configured to be capable of being suspended from at least the support structure (8) of the cockpit control panel (7), and at least some of the secondary joints said set of secondary joints (17) are configured to be re suspended and are configured to be able to be suspended on at least one structural element (16) of the front zone (6).
    [2" id="c-fr-0002]
    2. Lifter according to claim 1 characterized in that said set of primary joints (15) is configured to be suspended and is configured to be able to be suspended at least to the support structure (8) of the dashboard ( 7) of the cockpit (2), and in that said set of secondary joints (17) is configured to be suspended and is configured to be able to be suspended at least said structural element (16) of the zone before (6).
    [3" id="c-fr-0003]
    3. Lifter according to one of claims 1 and 2, characterized in that said set of primary joints (15) comprises, for each pedal (12), a pedal arm (19) which is connected to the pedal (12) , the pedal arm (19) being rotatably mounted on a structural member (20), and in that said structural member (20) is configured to be suspended and is configured to be able to be suspended at least to the support structure (8) of the dashboard (7) of the cockpit (2).
    [4" id="c-fr-0004]
    4. beam according to one of claims 1 to 3, characterized in that said set of secondary joints (17) comprises a steering shaft (32) rotatably mounted about a steering axis (33), l steering shaft (32) being connected via at least one link (41) to a steering position sensor (42).
    [5" id="c-fr-0005]
    5. Lifter according to any one of the preceding claims, characterized in that said assembly (25) for generating functional and structural links comprises, for each pedal (12), a connecting rod (28), the connecting rod (28) being linked by one (27) of its ends (27, 29), in an articulated manner, at one end (26) of a pedal arm (19) and at the other (29) of its ends (27, 29). ), in an articulated manner, at one end (31) of a steering shaft (32).
    [6" id="c-fr-0006]
    6. beam according to any one of the preceding claims, characterized in that said assembly (25) for generating functional and structural links comprises at least one fixed structural rod (48).
    [7" id="c-fr-0007]
    7. Lifter according to any one of the preceding claims, characterized in that the lifter (1) is provided with two pairs (11 A, 11 B) of pedals and a connecting rod of steering (53), the connecting rod steering conjugation device (53) being configured to transmit an actuation of one pair (11 A) of pedals to the other pair (11 B) of pedals.
    [8" id="c-fr-0008]
    8. Spreader according to claim 7, characterized in that the steering torque rod (53) is hingedly connected to the two transmission shafts (32) associated respectively with the two pairs (11 A, 11 B). of pedals.
    [9" id="c-fr-0009]
    9. Lifter according to any one of the preceding claims, characterized in that each of said pedals (12DA, 12GA, 12DB, 12GB) is mounted on a pedal arm (19), and in that each of said pedal arms (19 ) is in the form of a shell.
    [10" id="c-fr-0010]
    10. Lifter according to any one of the preceding claims, characterized in that it comprises a set of adjustment (50) which is configured to allow an operator to change the positions and strokes of the pedals (12DA, 12GA, 12DB, 12GB).
    [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]
    Aircraft according to claim 11, comprising a flight deck (2) and a front area (6) separated from the flight deck (2) by at least one dashboard support structure (8) (7), characterized in that said set of primary joints (15) is suspended at least from the supporting structure (8) of the dashboard (7) of the cockpit (2), and in that said set of joints secondary (17) is suspended at least one structural element (16) of the front zone (6).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20170113784A1|2017-04-27|
    CN106995051A|2017-08-01|
    US10737767B2|2020-08-11|
    FR3042776B1|2019-05-17|
    CN106995051B|2021-10-29|
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    法律状态:
    2016-10-20| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-28| PLSC| Publication of the preliminary search report|Effective date: 20170428 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1560116A|FR3042776B1|2015-10-23|2015-10-23|SUSPENDED PALONNIER FOR AIRCRAFT AND AIRCRAFT COMPRISING SUCH A SUSPENDED PALONNIER.|
    FR1560116|2015-10-23|FR1560116A| FR3042776B1|2015-10-23|2015-10-23|SUSPENDED PALONNIER FOR AIRCRAFT AND AIRCRAFT COMPRISING SUCH A SUSPENDED PALONNIER.|
    CN201610918887.1A| CN106995051B|2015-10-23|2016-10-21|Suspended rudder link for aircraft and aircraft comprising such rudder link|
    US15/332,247| US10737767B2|2015-10-23|2016-10-24|Aircraft rudder bar suspended over flight deck floor|
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