Integral and removable pedal module for aircraft rudder pedals

Abstract

The invention relates to an integral and removable pedal module for an aircraft rudder pedal. The pedal module (10A, 10B) intended for a rudder pedal (1) comprises a pedal (8A, 8B) and at least one integrated adjustment system and a connection device (12) enabling a removable connection of the pedal module (10A, 10B), the pedal module (10A, 10B) further being integral in order to simplify and facilitate its replacement, in particular by means of a removable connection obtained by means of the connection device (12).

Description

Technical Field

[0001] The invention relates to a pedal module for a rudder bar of an aircraft, in particular a transport aircraft, and to a rudder bar comprising at least one such pedal module.

[0002] On an aircraft, the rudder pedals are mechanical devices that allow the pilot and / or co-pilot to control the rudder unit and the brakes of the wheels.

[0003] The rudder pedals comprise an assembly of pedals and several moving parts that control the rudder unit or brakes of the aircraft depending on the type of movement applied to the pedals by the pilot(s). Background Art

[0004] The rudder pedals used on aircraft (mainly passenger aircraft) are rudder pedals integrated into the floor of the cockpit. The rudder pedals are said to be placed because they rest on the floor of the cockpit.

[0005] The rudder pedal must include a large number of components (hinges, connecting rods, pivots, etc.) for its operation, in particular for the function of the pedal connected to the steering control and for the function of the pedal connected to the braking system.

[0006] This conventional rudder pedal is complicated in particular because of this large number of components. This conventional rudder pedal is not optimal in particular in terms of space requirement, quality and cost. In addition, this complexity makes intervention and maintenance operations on the pedal and the associated components difficult, in particular because of the large number of connections between the components.

[0007] Therefore, this conventional solution is not entirely satisfactory. Summary of the invention

[0008] The invention relates to a pedal module for an aircraft rudder pedal. The pedal module comprises a pedal.

[0009] According to the invention, the step module is unitary and it also comprises at least one integrated adjustment system and a connection device enabling a removable connection of the step module to be produced.

[0010] In this way, as a result of the invention, the functionality of the pedal is integrated in a single module that is integral, referred to as the pedal module. In the context of the invention, an "integral module" is intended to be understood as a module in single part or complete form, ie it comprises a single object.

[0011] Furthermore, the pedal module can be removably connected to the rest of the rudder pedal. Thus, each pedal obtains a single pedal module, and the single pedal module can be easily disconnected from the rudder pedal. This makes it possible to simplify and facilitate the replacement of this pedal module and thus makes it possible to overcome the above-mentioned disadvantages.

[0012] In a preferred embodiment, the pedal module further comprises an integrated braking system.Thus, the pedal module integrates all functions associated with a corresponding pedal.

[0013] Advantageously, the braking system comprises a position sensor configured to measure a rotation of the pedal during a braking action.Preferably, the position sensor is mounted in a first housing, said first housing being arranged in a lower part of the pedal.

[0014] Furthermore, advantageously, the adjustment system can be controlled and is configured such that the inclination angle of the pedal can be adjusted. To this end, the adjustment system advantageously comprises a controllable geared motor.

[0015] In a specific embodiment, the adjustment system also includes a screw capable of being rotated by a gear-driven motor, the screw acting on a nut, the nut being configured to tilt the crank during rotation of the screw, the crank being provided with a roller, the roller being arranged to contact a roller track formed on the pedal and to push the pedal when the crank is tilted so as to modify its inclination.

[0016] Preferably, the geared motor is mounted in a second housing, which is arranged in a lower part of the pedal.

[0017] Furthermore, in a particular embodiment, the pedal is provided with at least one access hatch providing access to at least one of the first and second housings, said access hatch being arranged on a support surface of the pedal intended to act as a support for the pilot's feet.

[0018] In this particular embodiment, the step module preferably comprises at least one automatic extraction system which is configured to automatically extract an element (eg a position sensor or a geared motor) mounted in the (first or second) housing if an access hatch of this housing is opened.

[0019] Furthermore, the step module advantageously comprises a hollow integral carrier structure on which the step is rotatably mounted.

[0020] Furthermore, the step module advantageously comprises a protective bellows which is arranged between the step and the carrier structure.

[0021] The invention also relates to a rudder pedal comprising at least one pedal module as described in detail above.

[0022] In a preferred embodiment, the rudder pedals comprise at least one central module and two such pedal modules, which are arranged at one side and at the other side of the central module, each of the pedal modules being arranged on an associated lateral face of the central module.

[0023] Furthermore, in a particular embodiment, the central module is provided with a guide rail on each of these lateral faces, said guide rail being configured to cooperate with a recirculating ball bearing track fixed to the associated pedal module and forming part of the connection device.

[0024] Furthermore, advantageously, the central module is provided with an arm on each of said lateral faces, each of said arms being connected in an articulated manner to a push rod of a corresponding pedal module, said arms and push rods being configured to ensure the transmission of the movement of the pedals of the pedal modules.

[0025] The invention also relates to an aircraft, in particular a transport aircraft, provided with at least one pedal module and / or at least one rudder pedal as described in detail above. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The accompanying drawings will provide a good understanding of how the present invention may be performed. In these drawings, the same reference numerals refer to similar elements. More specifically:

[0027] - Figure 1 is a side view of an aircraft on the ground including rudder pedals according to an embodiment of the present invention;

[0028] - Figure 2 It is a perspective view of the rudder pedals facing forward;

[0029] - Figure 3 and Figure 4 A perspective view of the rudder pedals facing rearward and forward, with the pedal modules separated by a central module;

[0030] - Figure 5 is similar to Figure 2 , in which the wall is shown transparently in order to show the elements arranged inside the rudder pedals;

[0031] - Figure 6 and Figure 7 is a perspective view showing a pedal provided with a brake system;

[0032] - Figure 8 is a lateral schematic view of a pedal module enabling the possible inclination of an associated pedal to be displayed;

[0033] - Fig. 9 and Fig.10is a perspective view showing the main elements of the adjustment system displayed on a partially shown pedal;

[0034] - Fig.11 and Fig.12 are a side view and a perspective view, respectively, of a pedal provided with an adjustment system; and

[0035] - Fig.13 and Fig.14 A perspective view, facing rearwards and forwards respectively, showing the pedal provided with both the braking system and the regulating system. DETAILED DESCRIPTION

[0036] Figure 1 An aircraft AC is shown, in this case a transport aircraft, comprising a cockpit 2 (as in this case) in which the rudder pedals 1 according to the invention are arranged. Figure 1 The aircraft AC also comprises a rudder unit 3 and a brake 4 in the region of a wheel 5 of the main landing gear of the aircraft AC.

[0037] Figure 2 A preferred embodiment of the rudder pedal 1 is shown.

[0038] This rudder pedal 1 is intended to be integrated in the floor (not shown) of a cockpit 2 of an aircraft AC.

[0039] In the context of the present invention, the directions "rear" and "forward" are defined relative to the longitudinal direction of the aircraft AC, i.e., "forward" (e.g. Figure 2 In the figure, the arrow E1 is shown in the figure) along the flight (or movement) direction of the aircraft AC toward the front of the aircraft AC (along the Figure 1 direction of arrow E2), and “rear” (such as Figure 2 In the figure, the aircraft AC is moving in a direction opposite to the flight (or movement) direction of the aircraft AC (indicated by arrow E3).

[0040] Furthermore, in the context of the present invention, the terms "lower", "upper", "low" and "high" are defined in a vertical direction Z orthogonal to a horizontal plane P of the aircraft (defined by a direction called longitudinal and a direction called lateral), the plane P being parallel to the floor of the cockpit (not shown), e.g. Figure 2 Shown in.

[0041] More specifically:

[0042] - a longitudinal direction is defined along the longitudinal axis of the aircraft;

[0043] - the vertical direction Z forms with the longitudinal direction a plane called vertical and parallel to the vertical plane of symmetry of the aircraft; and

[0044] The lateral direction is orthogonal to the longitudinal direction and to the vertical direction, the lateral direction and the longitudinal direction forming a plane P which is parallel to the floor of the cockpit 2 .

[0045] In conventional manner, the rudder pedals 1 of an aircraft AC are control members which enable the pilot to control the rudder unit 3 ( Figure 1 ) in order to act on the yaw axis of the aircraft AC during flight and also to ensure braking of the aircraft AC when it moves on the ground, as explained below.

[0046] The rudder pedal 1, intended for use in a conventional transport aircraft, comprises an actuation assembly 6 (shown in Figure 2 ), the actuation assembly 6 can be actuated by a pilot (e.g., the primary pilot or the co-pilot of the aircraft). To this end, the rudder pedal 1 comprises a pair of pedals. This pair of pedals 7 comprises two pedals 8A and 8B intended to be actuated by the two (left and right) feet of the pilot, respectively.

[0047] For an aircraft controlled by two pilots, the rudder pedals 1 include two actuation assemblies 6 (such as Figure 2 The invention relates to an actuation assembly of a control panel which is conventionally configured so that pedals intended for one of the pilots (e.g. the co-pilot) are always in the same position as those pedals intended for the other pilot (e.g. the primary pilot).

[0048] Especially Figures 2 to 4 As shown in FIG. 1 , the rudder pedal 1 includes a central module 9 and two pedal modules 10A and 10B, each of which is provided with a single pedal 8A and 8B. The pedal modules 10A and 10B are arranged at one side and the other side of the central module 9. The pedal module 10A (provided with the pedal 8A) is arranged on the lateral surface 13 ( Figure 3 ), and the pedal module 10B (provided with the pedal 8B) is arranged on the lateral surface 14 of the central module 9.

[0049] According to the invention, each of the pedal modules 10A and 10B of the rudder footrest 1 is integral, ie it is produced in a single part and is unitary (corresponds to a single object).

[0050] Furthermore, each of the pedal modules 10A and 10B comprises, in addition to the associated pedal 8A, 8B, an integrated adjustment system 11 ( Figures 9 to 12 ) and a connection device 12 that enables removable fixing of the pedal modules 10A, 10B relative to the central module 9.

[0051] In this way, as explained below, all functions of the pedals 8A, 8B are integrated into a single module (referred to as pedal module 10A, 10B, which is monolithic).

[0052] Furthermore, the pedal modules 10A, 10B can be connected in a removable manner to the rest of the rudder pedal 1 and in particular to the central module 9. Thus, each pedal 8A, 8B obtains a single pedal module 10A, 10B, and the single pedal modules 10A, 10B can be easily disconnected from the rudder pedal 1. This makes it possible in particular to simplify and facilitate the handling and replacement of such pedal modules 10A, 10B.

[0053] In a preferred embodiment, the central module 9 is provided on each of the lateral faces 13 and 14 with two guide rails 15, each provided with a rolling path 16, as in Figure 3 and Figure 4 Specifically shown in.

[0054] These guide rails 15 are arranged parallel to each other on each of the lateral faces 13 and 14 , one at the bottom and the other at the top of the central module 9 .

[0055] The guide rails 15 are configured to cooperate with recirculating ball bearing tracks 17. The tracks 17 are fixed to the associated pedal module 10A, 10B and are configured to be movable along a rolling path 16 of the guide rails 15. The tracks 17 form part of the connection device 12 of the pedal module 10A, 10B.

[0056] exist Figures 2 to 4 In the specific embodiment shown in FIG. 1 , the central module 9 comprises a lower base module 18 and an upper auxiliary module 19. The auxiliary module 19 (or electric module) is preferably arranged on the base module 18 in a removable manner. Figure 5 , which shows in a transparent manner a base module 18 and an auxiliary module 19 of a central module 9 provided with a plurality of components, in particular electronic components, intended for the operation of the rudder pedals 1 and in Figure 5 The reference number 20 is generally used to identify the device.

[0057] Furthermore, the central module 9 is provided with an arm 21 on each of the lateral faces 13 and 14, such as Figure 2 and Figure 4 Each of the arms 21 is connected by a screw 22 ( Figure 2 ) is connected in an articulated manner to a push rod 23 of the corresponding pedal module 10A, 10B. For each pedal module 10A, 10B, the arm 21 and the push rod 23 are configured to ensure the movement (along the pedal) of the pedal module 10A, 10B. Figure 2 The direction indicated by arrow F in the figure is transmitted to the entire rudder pedal 1.

[0058] Since the connection system 24 is formed by the connection device 12 and the cooperating guide rail 15 provided on each pedal module 10A, 10B, each pedal module 10A, 10B can be moved forward or backward (along the direction indicated by arrow B) during actuation of the corresponding pedal 8B by the pilot's foot (not shown) in response to a steering command. Figure 2 10B).

[0059] The pedal module 10B is moved along the arrow F ( Figure 2 ) in one direction or the other, depending on the direction of movement, a partial rotation of the arm 21 between the two end positions 21A and 21B (determined by Figure 4 α is shown in the figure).

[0060] Thus, the arm 21 transmits, by this partial rotation, the steering command movement generated by the actuation of the pedals by the pilot. A sensor or mechanical device converts the mechanical control representative of the rotation of the arm 21 into an electrical signal in a conventional manner. This electrical signal is then transmitted in a conventional manner to the steering system (not shown) of the rudder unit 3 in order to control the steering of the aircraft AC ( Figure 1 ).

[0061] The connection system 24 further enables easy and quick extraction of the step modules 10A, 10B from the central module 9 on which the step modules 10A, 10B are removably mounted.

[0062] This extraction operation may be necessary in particular in order to replace a defective step module 10A, 10B. This operation can also be carried out by accessing the internal components of the central module 9, such as the component 20 ( Figure 5 ).

[0063] For example, the pedal module 10B is Figure 2 This extraction operation of the position shown in is performed in a very simple and quick manner using the following steps:

[0064] - disassembly of the screw 22 connecting the push rod 23 of the pedal module 10B to the arm 21 of the central module 9; and

[0065] - by rolling the step module 10B on the guide rails 15 of the central module 9 along the arrow E3 ( Figure 2 ) direction to pull out the pedal module 10B. The pedal module 10B is fully pulled out. Figure 4 middle.

[0066] Furthermore, each step module 10A, 10B comprises a carrier structure 25 on which the corresponding step 8A, 8B is rotatably mounted. This carrier structure 25 ensures the rotatability of the steps 8A, 8B.

[0067] This carrier structure 25 is integral. Furthermore, it is hollow, which in particular enables its mass to be reduced.

[0068] Furthermore, each step module 10A, 10B is provided with a protective bellows 26 which is arranged between the step 8A, 8B and the carrier structure 25 .

[0069] This protective bellows 26 is intended to protect sensitive components of the pedal modules 10A, 10B from any contamination.

[0070] Furthermore, in a preferred embodiment, each pedal module 10A, 10B also includes an integrated braking system 27 for the pedal 8B, shown in FIG. Figure 6 and Figure 7 The braking system of the pedal 8A is the same as the braking system of the pedal 8B described below.

[0071] For a braking command, pedal 8B is mounted so as to be movable in rotation about a rotation axis 28. This rotation axis 28 is located at the top (close to the lower end 29B of pedal 8B) in the direction of the base plate. In this way, when the pilot presses pedal 8B with his foot in the region of upper end 29A of pedal 8B (arrow H), pedal 8B pivots about rotation axis 28 and produces an action on an associated actuator 30 (or functional connecting rod), shown in FIG. Figure 5 The brake system 27 also includes a force detection spring 31 outside the actuator 30 .

[0072] The brake system 27 also includes a position sensor 32 ( Figure 6 ), position sensor 32 is configured to measure rotation of pedal 8B during braking action.

[0073] The position sensor 32 is a multi-channel rotation sensor (inductive, resistive, etc.) which is designed to determine the rotation of the pedal 8B (about the rotation axis 28 ) during the braking phase and transmit it as a braking command to a regulating system (not shown).

[0074] To this end, the brake system 27 comprises a transmission 33A (shown schematically and transparently in FIG. Figure 6 ), which is associated with the axis of rotation 28 and acts on a transmission 33B (also schematically and transparently shown in Figure 6 ), thereby generating a rotation about the rotation axis 34 which is measured by the position sensor 32.

[0075] Thus, during actuation of pedal 8B in the direction shown by arrow H, pedal 8B rotates about axis 28 . This rotation, transmitted by cooperating transmission assemblies 33A and 33B, is measured by position sensor 32 .

[0076] In a preferred embodiment, the position sensor 32 is mounted in a housing 35 (shown in FIG. Figure 7 ), the housing 35 is disposed in the lower portion (end portion 29B) of the pedal 8B.

[0077] This positioning of the position sensor 32 at the lower part of the pedal 8B enables rapid extraction of this component (via the rear) in the event of failure of this component.

[0078] Furthermore, in certain embodiments, each pedal (such as Figure 7 The pedal 8B shown in FIG. 1 is provided with an access hatch 36. This access hatch 36 enables access to the housing 35. The access hatch 36 is arranged on a rear (support) face 37 of the pedal 8B which is intended to act as a support for the pilot's feet, taking into account the actuation of the pedal 8B.

[0079] In this particular embodiment, the pedal modules 10A, 10B preferably include an automatic extraction system (not shown). This automatic extraction system is configured to automatically extract the position sensor 32 installed in the housing 25 when the access hatch 36 of the housing 25 is opened, for example, through conventional electrical connections present on the frame.

[0080] In this way, once the access hatch 36 is opened, the position sensor 32 is automatically withdrawn from its housing 35, such as Figure 7 The operator then only needs to grab it, for example, in order to replace it with a functional sensor if it is defective.

[0081] Furthermore, each pedal module 10A, 10B of the rudder pedal 1 comprises a regulating system 11, such as Figures 9 to 12 This adjustment system 11 is constructed around point O relative to Figure 8 The inclination shown by the axis 38 in FIG. 8 makes it possible to adjust the inclination angle ß of the corresponding pedals 8A, 8B.

[0082] To this end, the regulating system 11 comprises a geared motor 39 which can be controlled by an electronic control unit 52 (hereinafter referred to as Fig. 9 Detailed description).

[0083] exist Figures 9 to 12 In the specific embodiment shown in FIG. 1 , the adjustment system 11 comprises a screw 40 which can be rotated by a geared motor 39 via an angular transmission 41. The screw 40 acts on a nut 42 which is configured to tilt a bell crank 43 when the screw 40 rotates. The bell crank 43 is provided with a roller 44 which is arranged to contact a roller track 45 formed on a front face 46 of the pedal 8B ( Fig.13 ) and pushes pedal 8B when bell crank 43 is tilted so as to modify its inclination.

[0084] The adjustment system 11 also comprises a return spring (not shown) intended to ensure permanent contact of the roller 44 on the roller track 45 .

[0085] Therefore, this adjustment system 11 can implement the following adjustment methods:

[0086] - The electric adjustment commands generated by the operator via the control unit 52 drive the geared motor 39, which rotates about the axis 47, such as Fig. 9 and as indicated by double-headed arrow 48;

[0087] - the geared motor 39 rotates the screw 40 via an angular transmission 41 , as indicated by the double-headed arrow 49 ;

[0088] - the screw 40 is blocked at the lower part, the rotation of which effects the movement of the nut 42 , which has the effect of tilting the bellcrank 43 , as indicated by the double-headed arrow 50 ;

[0089] - during inclination, the free end of the bellcrank 43 moves along an arc and causes the roller 44 to move relative to the pedal 8B, as indicated by the double-headed arrow 51;

[0090] The rollers 44 run on the roller tracks 45 of the pedal 8B and push the pedal 8B, which causes a rotational movement of the pedal 8B about its axis of rotation 28 .

[0091] The regulating system 11 is an independent electrical system which is directly controlled by the user of the rudder pedals 1 .

[0092] Thus, the adjustment system 11 enables the neutral inclination of the associated pedal to be modified. The neutral inclination of a pedal is the inclination of the pedal when the pilot is not pressing it. Thus, this adjustment system 11 enables the inclination to be adapted to the size of the pilot who will have to use it.

[0093] In the future cockpit architecture, it is envisaged to use touch screens on the dashboard and work ergonomics on these screens according to the pilot's morphology (mainly the length of the arm). So far, the pilot has been positioned at a precise location in the cockpit, regardless of his size. In the future, it is expected that the pilot will be positioned according to his size (at a given distance from the screen in order to ensure good work ergonomics), and his eyes will be positioned along a uniquely determined line. The result of this development is that between a tall pilot and a short pilot, the distance between the positioning of their feet is reduced by half relative to the usual positioning. Therefore, conventional rudder pedals are incompatible with this method of positioning the pilot because they do not ensure the optimal positioning angle of the pedal relative to the user's feet according to the size of the user. This effect is amplified by the fact that the new generation of pilots has a size difference that is even greater than the current generation. As mentioned above, the adjustment system 11 makes it possible to overcome this shortcoming.

[0094] As an illustration, the variation of the inclination angle ß of the pedals 8A, 8B obtained by the adjustment system 11 is approximately (+ / - 5°). If necessary, this value can be greater.

[0095] The main advantages gained are:

[0096] - better comfort due to the greater angle variation of the pedals 8A, 8B; and

[0097] - Possibility of differential adjustment between left pedal 10B and right pedal 10A of rudder pedal 1, if necessary.

[0098] Furthermore, thanks to the motorization of the regulation system 11, preferably by electrical regulation (geared motor 39), the pilot does not have to manually perform the regulation of the position of the pedals. This makes it possible to reduce his / her workload and increase his / her comfort in relation to the pilot station while he / she performs his / her work.

[0099] The regulating system 11 is provided with a control unit 52 which is configured to control a controllable motorization (geared motor 39) of the regulating system 11, such as Fig. 9 The control unit 52 activates the operation of the adjustment system 11 so that it produces a movement of the pedals 8A, 8B in one or another possible direction.

[0100] In a simplified embodiment, the control unit 52 comprises a control element that can be activated by the operator. It can be a button or another mechanical member. The control element can also be a remote control unit that enables remote control of the adjustment system 11, for example when the pilot is sitting in his / her seat in a suitable position particularly in relation to his / her field of vision.

[0101] Furthermore, in a variant or in addition, the control unit 52 may include an automatic adjustment system comprising a memory containing a list of predetermined positions of the pedal. The automatic adjustment system is configured to automatically move the pedal to one of the predetermined positions in the list that has been selected. This selection is made by the pilot by rotating a button or any other selection means or by a remote control unit. In an advantageous variant, the control unit also includes a pilot identification system configured to identify at least one specific pilot. In this case, the automatic adjustment system is configured to move the pedal to a predetermined position associated with the pilot thus identified by the pilot identification system.

[0102] In a preferred embodiment, the geared motor 39 of the adjustment system 11 is mounted in a housing 53 (eg, Fig.14 ), the housing 53 is disposed in the lower portion of the pedal 8B. Fig.13 and Fig.14 In the embodiment of FIG. 5 , the position sensor 32 and the geared motor 39 are mounted in two adjacent housings 35 and 53 .

[0103] This positioning of the geared motor 39 at the lower part of the pedal 8B enables rapid extraction of this component (via the rear) in the event of failure of this component.

[0104] In addition, in a specific embodiment, each pedal button is Fig.14 In the same manner as the pedal 8B shown in FIG, 1 is provided with an access hatch 54. This access hatch 54 provides access to the housing 53. The access hatch 54 is arranged on the rear (support) face 37 of the pedal 8B, which is intended to act as a support for the pilot's feet, taking into account the actuation of the pedal 8B.

[0105] In this particular embodiment, the step modules 10A, 10B preferably include an automatic extraction system (not shown). This automatic extraction system is configured to automatically extract the geared motor 39 mounted in the housing 53 when the access hatch 54 of the housing 53 is opened, for example, through conventional electrical connections present on the frame.

[0106] In this way, once the access hatch 54 is opened, the geared motor 39 is automatically extracted from its housing 53, such as Fig.14 The operator then only has to grab it, for example, in order to replace it with a functional geared motor if it is defective.

[0107] As described above, the pedal modules 10A, 10B particularly have the following features:

[0108] - the mobility of the pedal module assemblies 10A, 10B, which is ensured by a recirculating ball bearing track 17 cooperating with a (short linear) guide rail 15 mounted directly on the central module 9;

[0109] - very quick disassembly of the pedal module assembly 10A, 10B, particularly for maintenance operations;

[0110] - Integration of all braking functions in the pedal modules 10A, 10B;

[0111] - an integral carrier structure 25;

[0112] - protection of sensitive components by means of an antifouling agent protecting the bellows 26 (integral); and

[0113] - Possibility of rapid extraction of components, which requires rapid maintenance capabilities (position sensor 32, geared motor 39).

[0114] As described above, therefore, the pedal modules 10A, 10B and the rudder pedal 1 have many advantages. Specifically:

[0115] - It is compact;

[0116] - It is simple;

[0117] - It is lightweight;

[0118] - The components can be easily maintained in an optimized manner according to their nature;

[0119] - it is robust; and

[0120] - It has reduced cost.

Claims

1. An integrated pedal module for an aircraft rudder pedal, the integrated pedal module being configured to be connected to a central module (9) of the aircraft rudder pedal, the integrated pedal module (10A, 10B) comprising: A single pedal (8A, 8B); at least one integrated adjustment system (11) configured to enable adjustment of the inclination angle (β) of the pedals (8A, 8B); as well as A connection device (12) enables a removable connection of the integrated pedal module (10A, 10B) to the central module (9).

2. The integrated pedal module according to claim 1, wherein: It also includes an integrated braking system (27).

3. The integrated pedal module according to claim 2, wherein: The braking system (27) includes a position sensor (32) configured to measure rotation of the pedal (8A, 8B) during a braking action.

4. The integrated pedal module according to claim 3, wherein: The position sensor (32) is mounted in a first housing (35) which is arranged in a lower portion of the pedals (8A, 8B).

5. The integrated pedal module according to any one of claims 1 to 4, wherein: The regulating system (11) can be controlled.

6. The integrated pedal module according to claim 5, wherein: The regulating system (11) comprises a controllable geared motor (39).

7. The integrated pedal module according to claim 6, wherein: The adjustment system (11) comprises a screw (40) rotatable by the geared motor (39), the screw (40) acting on a nut (42), the nut (42) being configured to tilt a crank (43) during rotation of the screw (40), the crank (43) being provided with a roller (44), the roller (44) being arranged to contact a roller track (45) formed on the pedal (8A) and to push the pedal (8B) when the crank (43) is tilted so as to modify its inclination.

8. The integrated pedal module according to claim 6 or claim 7, wherein: The geared motor (39) is mounted in a second housing (53) which is arranged in a lower portion of the pedal (8B).

9. The integrated pedal module according to claim 4, wherein: The pedal (8B) is provided with at least one access hatch (36, 54) providing access to at least one of the first housing (35) and the second housing (53), the access hatch (36, 54) being arranged on a support surface (37) of the pedal (8B), the pedal (8B) being intended to serve as a support for the pilot's feet.

10. The integrated pedal module according to claim 9, wherein: It comprises at least one automatic extraction system, which is configured to automatically extract a position sensor (32) installed in the first shell (35) or a gear-driven motor (39) installed in the second shell (53) when the access hatches (36, 54) of the first shell (35) and the second shell (53) are opened.

11. The integrated pedal module according to any one of claims 1 to 4, wherein: It comprises a hollow integral carrier structure (25) on which the pedals (8A, 8B) are rotatably mounted.

12. The integrated pedal module according to claim 11, wherein: It comprises a protective bellows (26) arranged between the pedals (8A, 8B) and the carrier structure (25).

13. A rudder pedal for an aircraft, wherein: It comprises at least one integrated pedal module (10A, 10B) as claimed in any one of claims 1 to 12.

14. The rudder pedal according to claim 13, wherein: It comprises at least one central module (9) and two integrated pedal modules (10A, 10B), wherein the integrated pedal modules (10A, 10B) are arranged at one side and the other side of the central module (9), and each of the integrated pedal modules (10A, 10B) is arranged on an associated lateral surface (13, 14) of the central module (9).

15. The rudder pedal according to claim 14, wherein: The central module (9) is provided with a guide rail (15) on each of the lateral faces (13, 14), the guide rail (15) being configured to cooperate with a recirculating ball bearing track (17) fixed to the associated integral pedal module (10A, 10B) and forming part of the connecting device (12).

16. A rudder pedal according to claim 14 or claim 15, wherein: The central module (9) is provided with an arm (21) on each of the lateral surfaces (13, 14), each of the arms (21) being connected in an articulated manner to a push rod (23) of a corresponding integrated pedal module (10A, 10B), the arm (21) and the push rod (23) being configured to ensure the transmission of the movement of the pedals (8A, 8B) of the integrated pedal modules (10A, 10B).

17. An aircraft, wherein: It comprises a rudder pedal (1) as claimed in any one of claims 13 to 16.

Images