Servo control designed to control the position of a moving part of an aircraft

Abstract

Servo control for controlling the position of a moving element of an aircraft. The servo control comprises: - a control device configured to control a power device according to a displacement command, the control device (60) comprising a control unit (62) including: + a set of electronic, mechanical and / or hydraulic accessories (70) in fluidic communication with the hydraulic cylinder; and + a body (72) delimiting a network of tubular cavities (98) fluidically connecting the electronic, mechanical and / or hydraulic accessories (70), the body (72) comprising an external surface (90), at least a first connection portion between the network and a hydraulic cylinder and at least a second connection portion between the network and the hydraulic cylinder, a neutral fiber (100) being defined for each tubular cavity (98). The neutral fiber (100) of at least one tubular cavity (98) is curved. Figure for the abbreviation: Figure 7

Description

Title of the invention: Servo control for controlling the position of a moving part of an aircraft

[0001] The present invention relates to a servo control intended for controlling the position of a moving element of an aircraft.

[0002] The present invention further relates to a control architecture for the position of the moving element, comprising such a servo control and a method for implementing the servo control.

[0003] Aircraft servocontrols are known to be intended for the precise control of the position of a moving element of the aircraft, in particular that of a control surface of the aircraft, in particular a depth or rudder located on the fin, or that of ailerons or flaps located on the wings.

[0004] Such servocontrols comprise a power device mechanically linked to the moving element and a control device receiving flight commands and controlling the power device accordingly. The power device comprises at least one hydraulic cylinder capable of cooperating with the moving element, and the control device comprises at least one control unit connected fluidly, mechanically, and electrically to the hydraulic cylinder.

[0005] Typically, the control unit comprises a body delimiting a network of tubular cavities fluidly connecting electronic, mechanical and / or hydraulic accessories as well as the hydraulic cylinder. In such servocontrols, the tubular cavities are directly machined into the body, notably by machining.

[0006] These known servo drives, however, do not provide complete satisfaction. Indeed, a control unit for such a servo drive usually comprises a complex network of tubular cavities connecting numerous electronic, mechanical, and / or hydraulic accessories, as well as the actuator. In order to accommodate all the numerous tubular cavities required, the body is bulky and therefore has a significant mass. Furthermore, when the cavities are not straight, it is necessary to drill numerous holes to create intersecting linear paths (generally at 90°), which further increases the required body volume.

[0007] However, the weight and size of the servo controls must comply with very strict specifications, particularly with regard to their location within the aircraft. Therefore, there is a need to reduce the size and mass of the servo controls in the prior art.

[0008] One objective of the invention is therefore to provide a servo control whose mass and size are reduced.

[0009] To this end, the invention relates to a servocontrol system for controlling the position of a moving element of an aircraft, comprising:

[0010] - a power device configured to move the moving element, the device power including at least one hydraulic cylinder extending along a cylinder axis; and

[0011] - a control device configured to control the power device in based on a command to move the moving element received from a device that generates the command to move the moving element, the control device comprising at least one control unit including:

[0012] + a set of electronic, mechanical and / or hydraulic accessories in com fluidic communication with the hydraulic cylinder; and

[0013] + a body delimiting a network of tubular cavities fluidly connecting the ac electronic, mechanical and / or hydraulic accessories as well as the hydraulic cylinder, the body comprising an external surface, at least a first connection portion between the network and the hydraulic cylinder and at least a second connection portion between the network and the hydraulic cylinder, a neutral fiber being defined for each tubular cavity;

[0014] in which the neutral fiber of at least one tubular cavity is curved.

[0015] According to particular embodiments of the invention, the servocontrol also has one or more of the following characteristics, taken individually or in any technically possible combination(s):

[0016] - the body of at least one control unit is produced by additive manufacturing;

[0017] - at least a part of the cylinder is made of a first material, the body of the less a piloting unit being made of a second material distinct from the first material;

[0018] - the first material is an aluminum alloy, the second material being a titanium alloy;

[0019] - the radius of curvature of at least one curved neutral fiber is continuously derivable;

[0020] - each tubular cavity is devoid of a sharp edge between its ends;

[0021] - at least one tubular cavity, in particular at least one tubular cavity of which the neutral fiber is curved, and is devoid of bifurcation and / or branching between its ends;

[0022] - each tubular cavity extends between two respective connecting ends has :

[0023] - at least a first portion of connection;

[0024] - at least a second connecting portion; or

[0025] - an electronic, mechanical and / or hydraulic accessory;

[0026] at least one curved neutral fiber extending along the shortest path between its two ends, the shortest path being restricted by the presence of other tubular cavities, electronic, mechanical and / or hydraulic accessories and the external surface;

[0027] - the body comprises at least one shaped portion, the external surface of the portion shaped to conform to the form of at least one electronic, mechanical and / or hydraulic accessory and / or at least one tubular cavity, in particular at least one tubular cavity whose neutral axis is curved; and

[0028] - the shaped portion of the body has a thickness, taken orthogonally by ratio to the external surface of the conformed portion between the external surface and:

[0029] - the nearest tubular cavity; or

[0030] - the nearest electronic, mechanical and / or hydraulic accessory;

[0031] the thickness being between 1 mm and 10 mm, preferably between 1 mm and 5 mm.

[0032] The invention further relates to a position control architecture for a moving element of an aircraft, comprising:

[0033] - a device for generating a command to move the moving element configured to generate a command to move the moving element; and

[0034] - a servo control as defined above, intended for position control of the moving element, depending on the command to move the moving element.

[0035] Also, the invention relates to a method for implementing a servo control as described above, comprising the following steps:

[0036] - formation of at least one hydraulic cylinder of the power device;

[0037] - realization of a rough draft of the body of at least one piloting unit by fa additive brication such that at least one tubular cavity has a curved neutral fiber;

[0038] - realization of the body of at least one piloting unit by machining the blank;

[0039] - formation of at least one control unit of the control device per installation electronic, mechanical and / or hydraulic accessories in the body;

[0040] - assembly of the power device and the control device to form the servo control.

[0041] According to particular embodiments of the invention, the method for implementing the servocontrol also has one or more of the following characteristics, taken individually or in any technically possible combination(s):

[0042] - the step of creating the rough outline of the body of at least one piloting unit is devoid of the use of additive manufacturing support;

[0043] - the body outline extends along a main direction from the back to the front, the the main direction being parallel to the cylinder axis when the power device and The control system is assembled,

[0044] additive manufacturing being carried out in the main direction from back to front during the roughing stage of the body of at least one control unit,

[0045] the body outline having at least a cantilevered portion,

[0046] any surface of at least one cantilevered portion oriented substantially towards the rear relative to the main direction having an angle with the main direction of less than or equal to 45°; and

[0047] - during the fabrication of the body of at least one piloting unit, the surfaces of at least one cantilevered portion oriented substantially towards the rear relative to the main direction are machined to give them their final shape.

[0048] The invention also relates to a servo control system for controlling the position of a moving part of an aircraft, comprising:

[0049] - a power device configured to move the moving element, the device power including at least one hydraulic cylinder extending along a cylinder axis; and

[0050] - a control device configured to control the power device in based on a command to move the moving element received from a device that generates the command to move the moving element, the control device comprising at least one control unit including:

[0051] + a set of electronic, mechanical and / or hydraulic accessories in com fluidic communication with the hydraulic cylinder; and

[0052] + a body delimiting a network of tubular cavities fluidly connecting the ac electronic, mechanical and / or hydraulic accessories as well as the hydraulic cylinder, a neutral fiber being defined for each tubular cavity;

[0053] at least a part of at least one hydraulic cylinder is made of a first material, the body of at least one pilot unit being made of a second material distinct from the first material.

[0054] According to particular embodiments of the invention, the servocontrol also has one or more of the following characteristics, taken individually or in any technically possible combination(s):

[0055] - the neutral fiber of at least one tubular cavity is curved;

[0056] - the body of at least one control unit is produced by additive manufacturing;

[0057] - the first material is an aluminum alloy, the second material being a titanium alloy;

[0058] - a connection device between the power device and the control device, the connection device comprising at least one connecting piece between the network of tubular cavities and the hydraulic cylinder, at least one connecting piece being movable relative to the body of the pilot unit and / or relative to the hydraulic cylinder to allow differential expansion of the body of the pilot unit and the hydraulic cylinder relative to each other;

[0059] - the hydraulic cylinder comprises a cylinder extending along the cylinder axis and limiting a chamber, a rod extending along the axis of the cylinder within the chamber, and a piston mounted on the rod within the chamber,

[0060] at least one between the hydraulic cylinder and the body of the pilot unit comprising a cylindrical connection cavity in fluidic communication with respectively the network of tubular cavities or the chamber of the hydraulic cylinder,

[0061] at least one connecting piece being arranged so as to be movable in translation within the cylindrical connecting cavity during the differential expansion of the body of the pilot unit and the hydraulic cylinder relative to each other;

[0062] - the cylindrical connecting cavity extends along an axis substantially parallel to the axis of the cylinder, at least one connecting piece being movable in translation within the cylindrical connecting cavity along the axis of the cylinder;

[0063] - the cylindrical connecting cavity is delimited by an internal wall,

[0064] at least one connecting piece comprising a cylindrical portion delimiting a connecting conduit and extending into the cylindrical connecting cavity, and at least one annular projection cooperating with the internal wall of the cylindrical connecting cavity to seal the network of tubular cavities of the pilot unit and the hydraulic cylinder; and

[0065] - the power device includes at least one additional hydraulic cylinder identical to the hydraulic cylinder and extending along an additional cylinder axis substantially parallel to the cylinder axis; and

[0066] - the control device includes at least one additional control unit identical to the piloting unit, with at least one additional piloting unit being associated with at least one additional hydraulic cylinder;

[0067] - the curved neutral fiber has a continuously differentiable curvature;

[0068] - at least one tubular cavity whose neutral fiber is curved is devoid sharp edges between its ends;

[0069] - at least one tubular cavity, in particular at least one tubular cavity of which the neutral fiber is curved, and is devoid of bifurcation and / or branching between its ends;

[0070] - the connecting device further comprising at least two screws, the connecting piece further comprises two wings, each formed by a plate including a screw passage hole, the power device and the piloting device each comprising at least two screw passage holes, each screw extending through the passage holes of the power device, the piloting device and the device connecting;

[0071] The invention further relates to a position control architecture for a moving element of an aircraft, comprising:

[0072] - a device for generating a command to move the moving element configured to generate a command to move the moving element; and

[0073] - a servo control as defined above intended for position control of the moving element, depending on the command to move the moving element.

[0074] Also, the invention relates to a method for implementing a servo control as described above, comprising the following steps:

[0075] - forming at least one hydraulic cylinder of the power device by machining of at least one block of the first material;

[0076] - realization of a rough draft of the body of at least one piloting unit by fa additive construction from the second material;

[0077] - realization of the body of at least one piloting unit by machining the blank;

[0078] - formation of at least one steering unit of the steering system by ins installation of electronic, mechanical and / or hydraulic accessories in the body;

[0079] - assembly of the power device and the control device to form the servo control.

[0080] According to particular embodiments of the invention, the method for implementing the servocontrol also has one or more of the following characteristics, taken individually or in any technically possible combination(s):

[0081] - the body blank comprises at least one tubular cavity whose neutral fiber is curve; and

[0082] - the assembly step includes the arrangement of at least one connecting device between the power device and the pilot device, the arrangement of at least one connecting device comprising the arrangement of a connecting piece between the network of tubular cavities and the hydraulic cylinder, the at least one connecting piece being movable relative to the body of the pilot unit and / or relative to the hydraulic cylinder to permit differential expansion of the body of the pilot unit and the hydraulic cylinder relative to each other.

[0083] Furthermore, the invention relates to a series of servo controls as described below:

[0084] - each servo control is intended for controlling the position of a moving element of the aircraft, each servocontrol comprising a power device and a control device, said control device and said power device being capable of being assembled to form, in an assembled configuration, said servocontrol, the series comprising a first servocontrol and a second servo separate control from the first servo control, the power device of the second servo control being identical to the power device of the first servo control, the control device of the second servo control being different from the control device of the first servo control, and / or

[0085] the series comprising a third servo control distinct from the first servo control, the power device of the third servo control being different from the power device of the first servo control, the control device of the third servo control being identical to the control device of the first servo control.

[0086] According to particular embodiments of the invention, the servo control series also has one or more of the following characteristics, taken individually or in any technically possible combination(s):

[0087] - the hydraulic cylinder of each power device comprises a first fixed ball joint in translation along the axis of the cylinder and a second ball joint intended to be fixed to the moving element and movable in translation along the axis of the cylinder, the first ball joint being movable in rotation around a first axis of rotation substantially orthogonal to the axis of the cylinder, the second ball joint being movable in rotation around a second axis of rotation substantially orthogonal to the axis of the cylinder, the first and second axes of rotation being separated along the axis of the cylinder by a center distance, the power device of the first servocontrol having at least one differentiating characteristic compared to the power device of the third servocontrol, the at least one differentiating characteristic being taken from the following list of differentiating characteristics:

[0088] - the diameter of the hydraulic cylinder; and / or

[0089] - the stroke of the hydraulic cylinder;

[0090] - the center distance; and

[0091] - the body of the control unit of the first servo control is identical to the body of the control unit of the second servo control, the set of electronic, mechanical and / or hydraulic accessories of the control unit of the first servo control being distinct from the set of electronic, mechanical and / or hydraulic accessories of the control unit of the second servo control.

[0092] Also, the invention relates to a method for producing a series of servo controls, the series being as described below:

[0093] - provision of a plurality of distinct power devices;

[0094] - provision of a plurality of distinct control devices;

[0095] - assembly of a first combination of a power device from among the plurality of distinct power devices and one control device among the plurality of distinct control devices to form a first servo- order ;

[0096] - assembly of a second combination of a power device from among the plurality of distinct power devices and one control device from among the plurality of distinct control devices to form a second servo control, the second combination being distinct from the first combination.

[0097] Optionally, the method for implementing the servo control series is such that the step of providing a plurality of distinct control devices comprises the following sub-steps:

[0098] - making available a plurality of piloting unit bodies, the bodies being identical;

[0099] - making available a plurality of first sets of electrical accessories tronic, mechanical and / or hydraulic and a plurality of second sets of electronic, mechanical and / or hydraulic accessories, the first sets being distinct from the second sets;

[0100] - formation of a first control unit by installing a first set electronic, mechanical and / or hydraulic accessories in a control unit body and without the installation of a second set of electronic, mechanical and / or hydraulic accessories;

[0101] - formation of a second piloting unit by installing a second set of electronic, mechanical and / or hydraulic accessories in a control unit body.

[0102] Other features and advantages of the invention will become apparent from the following description, given solely by way of example and with reference to the accompanying drawings, in which:

[0103] [Fig-1] [Fig.1] is a schematic top view of an example aircraft comprising a movable element and a control architecture for the position of the movable element, according to the invention;

[0104] [Fig.2] [Fig.2] is a top perspective view of a servocontrol according to the invention, forming part of the control architecture [Fig.1];

[0105] [Fig.3] [Fig.3] is a sectional view along a sectional plane marked III on the [Fig.2];

[0106] [Fig.4] [Fig.4] is an enlarged view of a detail marked IV on [Fig.3];

[0107] [Fig.5] [Fig.5] is a sectional view along a section plane marked V on the [Fig.3];

[0108] [Fig.6] [Fig.6] is a perspective view of a connecting piece of the device servo control connection of the [Fig.2];

[0109] [Fig.7] [Fig.7] is a schematic representation on the left side of a example of a piloting unit body according to the state of the art and on the part right of an example of the body of a servo control unit of the [Fig.2];

[0110] [Fig.8] [Fig.8] is a flowchart illustrating the servo implementation process control of the [Fig.2], according to the invention;

[0111] [Fig.9] [Fig.9] is a perspective view of a rough draft of a one-unit body control of a servo control according to the invention, obtained during the process of making the servo control of [Fig.8];

[0112] [Fig. 10] [Fig. 10] is a perspective view of a body of a servo control unit according to the invention, obtained by machining the blank of [Fig. 9];

[0113] [Fig. 11] [Fig. 11] is a schematic representation of a series of servocontrols, according to the invention;

[0114] [Fig. 12] [Fig. 12] is a logic diagram illustrating the process of making the servo control series of [Fig. 11], according to the invention.

[0115] Fig. 1 illustrates an aircraft 10.

[0116] The aircraft 10 comprises at least one moving element 12 and an architecture 14 for controlling the position of the moving element 12, according to the invention.

[0117] The movable element 12 is for example movable between a plurality of distinct positions.

[0118] The movable element 12 is, for example, a flight control of the aircraft 10. In particular, in the example of [Fig.1], the movable element 12 is an aileron of the aircraft 10 mounted movably on a wing of the aircraft 10.

[0119] According to unillustrated examples, the movable element 12 is an elevator or a rudder of the aircraft 10, movablely mounted on a fin of the aircraft 10.

[0120] According to another unillustrated example, the movable element 12 is a flap of the aircraft 10.

[0121] The control architecture 14 includes a device 16 for generating a movement command for the moving element 12 configured to generate a movement command for the moving element 12 and a servo control 18 for controlling the position of the moving element, according to the movement command for the moving element 12.

[0122] Advantageously, the control architecture 14 further includes a control system 20 suitable for being operated by a pilot to control the position of the moving element 12.

[0123] The control system 20 is notably installed in a cockpit of the aircraft 10.

[0124] For example, the control system 20 includes a flight control lever for the aircraft 10. According to the example in [Fig.1], the control lever is, for example, a control lever for the aileron of the aircraft 10.

[0125] The device 16 is configured to generate the command to move the moving element 12 according to an actuation of the control system 20 by the pilot.

[0126] For example, device 16 is an on-board computer.

[0127] With reference to Figures 2 and 3, the servo control 18 includes a power device 30 configured to move the moving element 12 and a piloting device 60 configured to control the power device 30 according to the command to move the moving element 12 received from the device 16 of the aircraft 10.

[0128] Advantageously, as illustrated in Figures 2 to 4, the servo control 18 further includes a connection device 120 between the power device 30 and the control device 60.

[0129] As illustrated in Figures 2 and 3, the power device 30 includes at least one hydraulic cylinder 32 extending along a cylinder axis A-A'.

[0130] We define in the following:

[0131] - a longitudinal axis L parallel to the cylinder axis A-A';

[0132] - a transverse axis T orthogonal to the longitudinal axis L so that the servo command 18 extends substantially along a plane P comprising the longitudinal axis L and the transverse axis T; and

[0133] - a vertical axis V orthogonal to the longitudinal axis L and to the transverse axis T.

[0134] Advantageously, as can be seen in Figures 2 and 3, the power device 30 includes at least one additional hydraulic cylinder 34 identical to the hydraulic cylinder 32 and extending along an additional cylinder axis B-B' substantially parallel to the cylinder axis A-A'.

[0135] According to the example illustrated in Figures 2 and 3, the power device 30 comprises exactly one hydraulic cylinder 32 and one additional hydraulic cylinder 34, fixed to each other substantially side by side in the plane P.

[0136] In what follows, for the sake of brevity, only one hydraulic cylinder 32 is described.

[0137] At least a part of the hydraulic cylinder 32 is made of a first material. According to a particular example, the entire hydraulic cylinder 32 is made of the first material.

[0138] Advantageously, the first material is an aluminum alloy, in particular an aluminum alloy 2050, 2024 or 7175.

[0139] As illustrated in the example of Figures 2 to 4, the hydraulic cylinder 32 comprises a cylinder 38, a rod 54 and a piston 56.

[0140] Advantageously, the hydraulic cylinder 32 further comprises a first ball joint 57 fixed in translation along the longitudinal axis L and a second ball joint 58 integral with the mobile element 12 and mobile in translation along the longitudinal axis L.

[0141] The cylinder 38 extends along the axis of the cylinder A-A'.

[0142] The cylinder 38 delimits a chamber 39 and includes at least a first portion 40 and at least a second portion 42 of connection between the chamber 52 and a piloting unit 62 of the piloting device 60 (which will be described later).

[0143] Chamber 39 comprises an upstream portion 39A and a downstream portion 39B and is intended to receive a fluid.

[0144] The first 40 and second 42 connecting portions of the cylinder 38 each comprise a cylindrical connecting cavity 44 fluidically connected to the chamber 39 and to the pilot unit 62, in particular to a network 96 of tubular cavities 98 of the pilot unit (which will be described later). The cylindrical connecting cavity 44 of the first connecting portion 40 of the cylinder 38 is shown in [Fig. 4].

[0145] In what follows, for the sake of brevity and as illustrated in the example of Figures 2 to 4, the cylinder 38 is considered to comprise a single first connecting portion 40 and a single second connecting portion 42.

[0146] With reference to [Fig.5], the first connecting portion 40 of the cylinder 38 further comprises two connecting members 46 with the connecting device 120.

[0147] The two organs 46 are arranged on either side of the plane P.

[0148] Each connecting member 46 comprises two plates 48, each extending substantially along a plane parallel to the transverse axis T and the vertical axis V and separated by a receiving space 49 for a wing 132 of a connecting piece 122 of the connecting device 120. In particular, the receiving space 49 is dimensioned so that the spacing between the plates 48 corresponds substantially to the thickness of the wing 132 measured along the longitudinal axis L.

[0149] Each plate 48 includes an orifice 50 for the passage of a screw 140 of the connecting device 120.

[0150] The rod 54 extends along the axis of the cylinder A-A' in the chamber 39.

[0151] The piston 56 is mounted on the rod 54 in the chamber 39. Advantageously, the piston 56 came from material with stem 54.

[0152] The piston 56 separates the upstream portion 39A and the downstream portion 39B of the chamber 39.

[0153] The first ball joint 57 is fixed in translation along the longitudinal axis L and movable in rotation around a first axis of rotation RI substantially parallel to the transverse axis T. In particular, the first ball joint 57 is fixed to the cylinder 38.

[0154] The second ball joint 58 is movable in translation along the longitudinal axis L and movable in rotation around a second axis of rotation R2 substantially parallel to the transverse axis T. In particular, the second ball joint 57 is integral with the piston.

[0155] As can be seen in [Fig.3], the first RI and second R2 axes of rotation are separated along the longitudinal axis L by a center distance EA.

[0156] As illustrated in Figures 2 and 3, the control device 60 comprises at least one control unit 62.

[0157] Advantageously, the piloting device 60 comprises at least one additional piloting unit 64 identical to the piloting unit 62 and associated with at least one additional hydraulic cylinder 34.

[0158] According to the example illustrated in Figures 2 and 3, the piloting device 60 comprises exactly one piloting unit 62 and one additional piloting unit 64.

[0159] The pilot unit 62 is fixed and fluidly, mechanically and electrically connected to the hydraulic cylinder 32 and the additional pilot unit 64 is fixed and fluidly connected to the additional hydraulic cylinder 34.

[0160] In what follows, for the sake of brevity, only one piloting unit 62 is described.

[0161] The control unit 62 comprises a set 68 of electronic, mechanical and / or hydraulic accessories 70 and a body 72.

[0162] Advantageously, the set 68 of accessories 70 depends on specific requirements for controlling the position of the particular moving element 12 controlled by the servo control 18. Thus, for example, for the control of different moving elements 12, it is planned to install sets 68 corresponding to distinct combinations of accessories 70.

[0163] The electronic, mechanical and / or hydraulic accessories 70 are in fluidic communication with the hydraulic cylinder 32, in particular through a network 96 of tubular cavities 98 extending into the body 72.

[0164] Advantageously, the electronic, mechanical and / or hydraulic accessories 70 are arranged in the body 72, in particular in cavities for receiving the accessories 70.

[0165] Accessories 70 are for example pistons, check valves, valves, pressure sensors, flow sensors, temperature sensors, distributors, accumulators.

[0166] As illustrated in Figures 2, 3, 4 and 7, the body 72 delimits the network 96 of tubular cavities 98.

[0167] Advantageously, the body 72 further comprises at least a first portion 76 for connecting the network 96 and the hydraulic cylinder 32, at least a second portion 78 for connecting the network 96 and the hydraulic cylinder 32, at least a shaped portion 88 and an external surface 90.

[0168] The body 72 of the control unit 62 is made of a second material distinct from the first material, advantageously by additive manufacturing.

[0169] Even more advantageously, the second material is a titanium alloy, in particular a TA6V titanium alloy.

[0170] Advantageously, the first 76 and second 78 connecting portions each comprise a cylindrical connecting cavity 80 in fluidic communication with the chamber 39 of the hydraulic cylinder 32. The cylindrical connecting cavity 80 of the first section of fitting 76 is shown on [Fig.4].

[0171] In what follows, for the sake of brevity and as illustrated in the example of Figures 2 to 5, the body 72 is considered to comprise a single first connecting portion 76 and a single second connecting portion 78.

[0172] For example, as illustrated in Figures 2 to 5, the first connecting portion 76 of the body 72 is in fluidic communication with the first connecting portion 40 of the cylinder 38 and the second connecting portion 78 of the body 72 is in fluidic communication with the second connecting portion 42 of the cylinder 38.

[0173] The first 76 and second 78 connecting portions of the body 72, in particular their respective cylindrical connecting cavities 80, are connected by the set 68 of accessories 70.

[0174] With reference to [Fig.5], the first connecting portion 76 of the body 72 further comprises two connecting members 84 with the connecting device 120.

[0175] The cylindrical connecting cavity 80 of the first 76 and / or the second 78 connecting portions of the body 72 extends along an axis C-C' (visible on the [Fig.4]) substantially parallel to the axis of the cylinder A-A'.

[0176] According to the example illustrated in Figures 2 to 5, the cylindrical connecting cavity 80 of the first connecting portion 76 of the body 72 extends along the axis C-C'.

[0177] Each cylindrical connection cavity 80 is delimited by an internal wall 82.

[0178] Each connecting member 84 comprises a plate 85 extending substantially along a plane parallel to the transverse axis T and the vertical axis V, in particular parallel to the extension plane of the plates 48 of the connecting elements 46 of the cylinder 32.

[0179] Each plate 85 includes an orifice 86 for the passage of a screw 140 of the connecting device 120.

[0180] For example, as illustrated in Figures 2 and 7, the body 72 comprises at least one shaped portion 88, of which a portion 91 of corresponding external surface 90 conforms to the shape of at least one mechanical, electronic and / or hydraulic accessory 70 and / or at least one tubular cavity 98, in particular at least one tubular cavity 98 having a curved neutral fiber 100.

[0181] Advantageously, as illustrated on the right-hand side of [Fig.7], the shaped portion 88 has a thickness E taken orthogonally with respect to the portion 91 of external surface 88 corresponding between said portion of external surface 88 and:

[0182] - the nearest tubular cavity 98; or

[0183] - the nearest electronic, mechanical and / or hydraulic accessory 70;

[0184] the thickness E being between 1 mm and 10 mm, preferably between 1 mm and 5 mm.

[0185] As illustrated in [Fig. 7], which compares the invention (right side of [Fig. 7]) and the prior art (left side of [Fig. 7]), the shaped portion 88 allows a mass reduction and pressure loss within the tubular cavity 98. Indeed, the body 72 has less material than the body 7 of the prior art since in the invention the surface 90 conforms to the shape of the accessories 70 and / or the tubular cavities 98. In comparison, in the prior art, the surface 9 of the body 7 is substantially flat and does not conform to the shape of either accessories 8 or tubular cavities 1, 2.

[0186] The network 96 of tubular cavities 98 fluidly connects the accessories 70 to each other and the accessories 70 to the hydraulic cylinder 32. In particular, the network 96 of tubular cavities 98 fluidly connects the cylindrical connecting cavities 80 of the first 76 and second 78 connecting portions and the accessories 70.

[0187] Each tubular cavity 98 extends between two ends 102, 104 respectively of connection to:

[0188] - the first portion of the fitting 76, in particular the cylindrical cavity 80 of the first section of connection 76;

[0189] - the second portion of the fitting 78, in particular the cylindrical cavity 80 of the second section of connection 78; or

[0190] - an electronic, mechanical and / or hydraulic accessory 70.

[0191] Fig. 7 (right-hand part) illustrates an example in which a tubular cavity 98, of which the neutral fiber 100 is curved, extends between an end 102 of connection to a first electronic, mechanical and / or hydraulic accessory 70A and a second end 104 of connection to a second electronic, mechanical and / or hydraulic accessory 70B.

[0192] Each tubular cavity 98 is radially delimited by an internal wall 106.

[0193] Each tubular cavity 98 is devoid of a sharp edge between its ends 102, 104. The left part of [Fig.7] illustrates an example of the prior art in which two tubular cavities 1, 2 have sharp edges between their ends 3, 4.

[0194] At least one tubular cavity 98 is devoid of bifurcation and / or branching between its ends 102, 104. The left part of [Fig.7] illustrates an example of the prior art in which each tubular cavity 1, 2 has bifurcations and branchings 5, 6.

[0195] A neutral fiber 100 is defined for each tubular cavity 98.

[0196] The neutral fiber 100 of a tubular cavity 98 corresponds to a line passing through the center of gravity of the straight sections of said tubular cavity 98.

[0197] Advantageously, as illustrated in [Fig. 7], the neutral fiber 100 of at least one tubular cavity 98 is curved. Such a curved neutral fiber 100 is obtained in particular through the use of additive manufacturing during the process of producing the servo control 18 (detailed later).

[0198] For example, a plurality of tubular cavities 98 have a neutral fiber 100 curve.

[0199] In particular, at least one tubular cavity 98 whose neutral fiber 100 is curved is devoid of a sharp edge between its ends 102, 104 and is devoid of bifurcation and / or branching between its ends 102, 104.

[0200] In what follows, with reference to [Fig. 7], a single tubular cavity 98 whose neutral fiber 100 is curved is described. It is understood, of course, that what follows applies to all tubular cavities 98 whose neutral fiber 100 is curved.

[0201] For example, as illustrated in [Fig.7], the curved neutral fiber 100 extends along the shortest path between its two ends 102, 104, the shortest path being restricted by the presence of the other tubular cavities 98, the accessories 70 and the external surface 90. As illustrated in the example of [Fig.7], the shortest path along which the curved neutral fiber 100 extends is restricted by the presence of the accessory 70C.

[0202] Advantageously, the radius of curvature of the curved neutral fiber 100 is continuously differentiable.

[0203] With reference to Figures 2 to 5, the connecting device 120 includes at least one connecting part 122 between the network 96 of tubular cavities 98 of the pilot unit 62 and the hydraulic cylinder 32.

[0204] Advantageously, the connecting device 120 includes at least one additional connecting piece 124 identical to the connecting piece 122 and connecting the network 96 of tubular cavities 98 of the additional pilot unit 64 and the additional hydraulic cylinder 34.

[0205] According to the example illustrated in Figures 2 to 5, the connecting device 120 comprises exactly one connecting piece 122 and one additional connecting piece 124.

[0206] In what follows, for the sake of brevity, only one connecting piece 122 is described. It is of course understood that what follows applies to all connecting pieces 122, when the connecting device 120 comprises a plurality of connecting pieces 122 and additional connecting pieces 124.

[0207] Advantageously, as seen in [Fig.5], the connecting device 120 further comprises, for each connecting piece 122, two screws 140 and two nuts 142.

[0208] The connecting piece 122 is movable relative to the body 72 of the pilot unit 62 and / or relative to the hydraulic cylinder 32 to allow differential expansion of the body 72 of the pilot unit 62 and of the hydraulic cylinder 32 relative to each other.

[0209] According to the example illustrated in Figures 2 to 5, the connecting piece 122 is arranged so as to be movable in translation in the cylindrical connecting cavity 80 of the first connecting portion 76 during the differential expansion of the body 72 of the pilot unit 62 and the hydraulic cylinder 32 relative to each other.

[0210] In particular, the connecting piece 122 is movable in translation in the cylindrical connecting cavity 80 along the axis of the cylinder A-A'.

[0211] In particular, as illustrated in Figures 4 to 6, the connecting piece 122 comprises a cylindrical portion 128 connecting with the cylindrical cavity 80 of the first connecting portion 76 of the pilot unit 62 and a cylindrical portion 130 connecting with the cylindrical cavity 44 of the first connecting portion 40 of the hydraulic cylinder 32.

[0212] Advantageously, as can be seen in Figures 5 and 6, the connecting piece 122 further comprises two wings 132 extending laterally on either side of the cylindrical portions 128 and 130, in particular on either side of the plane P.

[0213] The cylindrical portion of the connection 128 delimits a connecting conduit 146 and extends into the cylindrical connecting cavity 80.

[0214] During the differential expansion of the body 72 of the pilot unit 62 and the hydraulic cylinder 32 relative to each other, the cylindrical portion of the connection 128 slides in the cylindrical cavity of the connection 80.

[0215] The cylindrical connecting portion 128 further includes at least one annular projection 148 extending radially from the connecting conduit 146 and cooperating with the internal wall 82 delimiting the cylindrical connecting cavity 80, to connect in a sealed manner the network 96 of tubular cavities 98 of the pilot unit 62 and the hydraulic cylinder 32.

[0216] With reference to Figures 5 and 6, each wing 132 is formed by a plate 134 extending substantially along a plane parallel to the transverse axis T and the vertical axis V.

[0217] Each plate 134 includes an orifice 136 for the passage of the screw 140.

[0218] As can be seen in [Fig. 5], each screw 140 extends substantially parallel to the longitudinal axis L through the passage orifices 50 of the connecting members 46 of the cylinder 32, through the passage orifice 86 of the connecting member 84 of the body 72 of the piloting unit 62 and through the passage orifice 136 of the wings 132 of the connecting piece 122.

[0219] Each screw 140 cooperates with a nut 142 to secure the hydraulic cylinder 32, the connecting piece 122 and the pilot unit 62 while allowing translation parallel to the longitudinal axis L of the hydraulic cylinder 32 and the pilot unit 62 relative to each other.

[0220] During the differential expansion of the body 72 of the pilot unit 62 and the hydraulic cylinder 32 relative to each other, the connecting piece 122 of the connecting device 120 and the connecting elements 46, in particular the plates 48, slide together along the screw 140 between the connecting element 84 of the pilot unit 62, in particular the plate 85, and the head of the screw 140.

[0221] Thus, the control device 60 and the power device 30 can be made in materials of different natures and / or characteristics, by assembling one on top of the other. The connecting piece 122 ensures that the differential expansions likely to occur over the aircraft's operating temperature range 10 are compensated.

[0222] The screws 140 thus constitute an element enabling the joining of the cylinder 32, the pilot unit 62 and the connecting piece 122 and the guidance along the longitudinal direction L of the hydraulic cylinder 32 relative to the pilot unit 62 during differential expansion.

[0223] In what follows, with reference to Figures 8 to 10, a method 200 for making a servocontrol 18 as described above is described.

[0224] The process 200 includes a first step 210 of forming the hydraulic cylinder 32 of the power device 30 for example by machining at least one block of the first material.

[0225] The process 200 further includes a second step 220 of producing a rough 71 of the body 72 of the control unit 62 by additive manufacturing in particular from the second material.

[0226] Advantageously, the blank 71 of the body 72 comprises at least one tubular cavity 98 whose neutral fiber 100 is curved. In particular, the second step 220 is carried out such that at least one tubular cavity 98 has a curved neutral fiber 100. In particular, additive manufacturing makes it possible to obtain such a curved neutral fiber 100.

[0227] Advantageously, with reference to [Fig. 9], the second step 220 does not require the use of additive manufacturing supports. "Additive manufacturing supports" means elements dedicated to supporting cantilevered parts of the blank 71. In particular, the blank 71 is self-supporting. "Self-supporting" means that the blank 71 is free of cantilevered parts or that it has cantilevered parts that do not require special supports.

[0228] As illustrated in [Fig.9], the blank 71 of the body 72 extends along a principal direction D from the rear to the front. The principal direction D is parallel to the axis of the cylinder A-A' when the power device 30 and the pilot device 60 are assembled.

[0229] Additive manufacturing is carried out along the main direction D from back to front during the second step 220.

[0230] According to the example illustrated in [Fig.9], the blank 71 of the body 72 has at least one cantilevered portion 160. By "cantilevered" is meant that the portion 160 does not have immediate support below it, i.e. rearward along the principal direction D.

[0231] According to the example illustrated in [Fig.9], any surface of at least one portion 160 Oriented substantially towards the rear along the principal direction D, it presents an angle α with the principal direction D less than or equal to 45°. Such an angle notably allows for the elimination of supports in additive manufacturing.

[0232] A cantilevered portion 160 is shown in the example in [Fig. 9]. This cantilevered portion corresponds to the upper part (front along the principal direction D) of a orifice blank 161. This upper part is cantilevered because it has no immediate support below it. The upper surface of the orifice blank 161, which is oriented substantially rearward along the principal direction D, has an angle α with the principal direction D, as illustrated.

[0233] Again with reference to [Fig.8], the process 200 further includes a third step 230 of realizing the body 72 of the pilot unit 62 by machining the blank 71.

[0234] According to the example illustrated in [Fig. 10], the surfaces of at least one portion 160 oriented substantially towards the rear are machined to give them their final shape.

[0235] [Fig. 10] illustrates an example conforming to that of [Fig. 9], in which the orifice blank 161 of [Fig. 9] has been machined to give it its final shape, i.e. the final shape of orifice 162.

[0236] Again with reference to [Fig.8], the process 200 further includes a fourth step 240 of forming the pilot unit 62 of the pilot device 60 by installing the electronic, mechanical and / or hydraulic accessories 70 in the body 72.

[0237] The method 200 further includes a fifth step 250 of assembling the power device 30 and the control device 60 to form the servocontrol 18.

[0238] Advantageously, the fifth step 250 includes the arrangement of at least one connecting device 120 between the power device 30 and the pilot device 60.

[0239] In particular, the arrangement of at least one connecting device 120 between the power device 30 and the pilot device 60, includes the arrangement of a connecting piece 122 between the network 96 of tubular cavities 98 and the hydraulic cylinder 32.

[0240] In what follows, with reference to [Fig. 11], a series 180 of servocontrols 18A, 18B, 18C, according to the invention, is described.

[0241] The servocontrols 18A, 18B, 18C of the 180 series of servocontrols are as described above.

[0242] Each servo control 18 of the series 180 of servo controls 18A, 18B, 18C is intended for controlling the position of a moving element 12 of the aircraft 10.

[0243] Each servo control 18 of the series 180 of servo controls 18A, 18B, 18C comprises a power device 30 and a control device 60 suitable for being assembled to form, in an assembled configuration, said servo control 18.

[0244] Advantageously, the 180 series of servocontrols 18A, 18B, 18C comprises a first servocontrol 18A and a second servocontrol 18B distinct from the first servocontrol 18A.

[0245] Even more advantageously, the 180 series of servocontrols 18A, 18B, 18C includes a third servocontrol 18C distinct from the first servocontrol 18A.

[0246] According to the example of [Fig.1 1], the third servo control 18C is also distinct from the second servo control 18B.

[0247] For example, the first servo control 18A is intended for controlling the position of a first moving element 12, the second servo control 18B is intended for controlling the position of a second moving element 12 distinct from the first moving element 12 and the third servo control 18C is intended for controlling the position of a third moving element 12 distinct from the first and second moving elements 12.

[0248] Advantageously, the 30X power device of the second servo control 18B is identical to the 30X power device of the first servo control 18A and the 60Y control device of the second servo control 18B is different from the 60X control device of the first servo control 18A.

[0249] In particular, the 62U control unit of the first servo control 18A is separate from the 62V control unit of the second servo control 18B.

[0250] In particular, the body 72 of the control unit 62U of the first servo control 18A is identical to the body 72 of the control unit 62V of the second servo control 18B and the assembly 68U of electronic, mechanical and / or hydraulic accessories 70 of the control unit 62U of the first servo control 18A is distinct from the assembly 68V of electronic, mechanical and / or hydraulic accessories 70 of the control unit 62V of the second servo control 18B.

[0251] In other words, the first 18A and second 18B servocontrols are distinguished by the set 68 of electronic, mechanical and / or hydraulic accessories 70 but include identical bodies 72, and therefore identical networks 96 of tubular cavities 98.

[0252] For example, the power device 30Y of the third servo control 18C is different from the power device 30X of the first servo control 18A and the control device 60X of the third servo control 18C is identical to the control device 60X of the first servo control 18A.

[0253] In particular, the 30X power device of the first 18A servo control presents at least one differentiating characteristic compared to the device of power 30Y of the third servo control 18C.

[0254] Advantageously, at least one differentiating characteristic is taken from the following list of differentiating characteristics:

[0255] - the diameter of the hydraulic cylinder 32;

[0256] - the stroke of the hydraulic cylinder 32; and

[0257] - the center distance EA.

[0258] In particular, the diameter of the hydraulic cylinder 32 corresponds to the diameter of the cylinder 38.

[0259] In what follows, with reference to [Fig. 12], a method 300 for making a series 180 of servocontrols 18A, 18B, 18C as described above is described.

[0260] The method 300 includes a first step 310 of making available a plurality of devices of distinct powers 30X, 30Y.

[0261] The method 300 further includes a second step 320 of making available a plurality of distinct control devices 60X, 60Y.

[0262] Advantageously, with reference to [Fig. 12], the second step 320 comprises a first substep 321 of making available a plurality of bodies 72 of identical piloting units 62.

[0263] The second step 320 further includes a second substep 322 of making available a plurality of first sets 68U of electronic, mechanical and / or hydraulic accessories 70 and a plurality of second sets 68V of electronic, mechanical and / or hydraulic accessories 70. The first sets 68U are distinct from the second sets 68V.

[0264] The second step 320 further includes a third substep 323 of forming a first pilot unit 62U by installing a first set 68U of electronic, mechanical and / or hydraulic accessories 70 in a body 72 of a pilot unit 62 and without installing a second set 68V of electronic, mechanical and / or hydraulic accessories 70.

[0265] The second step 320 further includes a fourth step 324 of forming a second 62V control unit by installing a second 68V set of electronic, mechanical and / or hydraulic accessories 70 in a 62 control unit body 72, for example without installing a first 68U set of electronic, mechanical and / or hydraulic accessories 70.

[0266] Still with reference to [Fig. 12], the method 300 further includes a third step 330 of assembling a first combination of a power device 30 from among the plurality of distinct power devices 30X, 30Y, 30Z and a control device 60 from among the plurality of distinct control devices 60X, 60Y, 60Z to form a first servocontrol 18A.

[0267] The process 300 further comprises a fourth step 340 of assembling a second combination of a power device 30 from the plurality of distinct power devices 30X, 30Y, 30Z and a control device 60 from the plurality of distinct control devices 60X, 60Y, 60Z to form a second servo control 18B. The second combination is distinct from the first combination.

[0268] According to another embodiment, the first material is a steel, in particular a stainless steel or a titanium alloy.

[0269] According to yet another embodiment, the second material is steel, in particular stainless steel, Inconel™ or aluminum alloy.

[0270] According to yet another embodiment, the device 16 for generating the command to move the moving element 12 is a mechanical linkage.

[0271] Thanks to the invention, the servo control 18 offers improved adaptability and modularity depending on the moving element 12 to be controlled by the use of two distinct materials respectively for the hydraulic cylinder 32 and for the pilot unit 62.

[0272] The servo control 18 allows for mass savings and manufacturing cycle time savings (time savings).

[0273] The use of additive manufacturing for the production of the body 72 of the control unit 62, and in particular the fact that the body 72 has at least one tubular cavity 98 whose neutral fiber 100 is curved, makes it possible to make the network 96 of tubular cavities 98 more compact, and therefore to reduce the mass and size of the body 72.

[0274] The fact that the body 72 includes a shaped portion, also obtained through the use of additive manufacturing, further reduces the mass and size of the body 72.

[0275] The use of an aluminium alloy for the hydraulic cylinder 32 and a titanium alloy for the control unit 62 makes it possible to obtain a particularly satisfactory compromise between lightness and reliability (mechanical resistance in particular).

[0276] Thanks to the connecting device 120, in particular thanks to the connecting piece 122, differential expansion of the body 72 of the pilot unit 62 and of the hydraulic cylinder 32 relative to each other is permitted, which reduces the stresses experienced by the servo control 18 and thus extends its service life.

[0277] Finally, the invention makes it easy to implement a multitude of servo drives 18 based on various moving elements 12 to be controlled. The servo drives of the 180 series according to the invention are distinguished by their power device and / or by their control device.

[0278] Using a single identical body 72 for each servo control 18 of the series 180 simplifies the production of the series.

Claims

Demands

1. Servocontrol (18) for controlling the position of a moving element (12) of an aircraft (10), comprising: - a power device (30) configured to move the moving element (12), the power device (30) comprising at least one hydraulic cylinder (32) extending along a cylinder axis (A-A'); and - a control device (60) configured to control the power device (30) according to a command to move the moving element (12) received from a device (16) for generating the command to move the moving element (12), the control device (60) comprising at least one control unit (62) comprising: + a set (68) of electronic, mechanical and / or hydraulic accessories (70) in fluidic communication with the hydraulic cylinder;and + a body (72) delimiting a network (96) of tubular cavities (98) fluidly connecting the electronic, mechanical and / or hydraulic accessories (70) as well as the hydraulic cylinder (32), the body (72) comprising an external surface (90), at least a first connecting portion (76) between the network (96) and the hydraulic cylinder (32) and at least a second connecting portion (78) between the network (96) and the hydraulic cylinder (32), a neutral fiber (100) being defined for each tubular cavity (98); characterized in that the neutral fiber (100) of at least one tubular cavity (98) is curved.;

2. Servocontrol (18) according to claim 1, wherein the body (72) of at least one control unit (62) is made by additive manufacturing.

3. Servocontrol (18) according to claim 1 or 2, wherein at least a part of the cylinder (32) is made of a first material, the body (72) of at least one pilot unit (62) being made of a second material distinct from the first material.

4. Servocontrol (18) according to claim 3, wherein the first material is an aluminum alloy, the second material being a titanium alloy.

5. Servocontrol (18) according to any one of the preceding claims, wherein the radius of curvature of at least one fiber neutral (100) curve is continuously differentiable.

6. Servocontrol (18) according to any one of the preceding claims, wherein each tubular cavity (98) is devoid of a sharp edge between its ends (102, 104).

7. Servocontrol (18) according to any one of the preceding claims, wherein at least one tubular cavity (98), in particular at least one tubular cavity (98) whose neutral fiber is curved, is devoid of bifurcation and / or branching between its ends (102, 104).

8. Servocontrol (18) according to any one of the preceding claims, wherein each tubular cavity (98) extends between two ends (102, 104) respectively of connection to: - at least one first connecting portion (76); - at least one second connecting portion (78); or - an electronic, mechanical and / or hydraulic accessory (70); at least one curved neutral fiber (100) extending along the shortest path between its two ends (102, 104), the shortest path being restricted by the presence of the other tubular cavities (98), the electronic, mechanical and / or hydraulic accessories (70) and the external surface (90).

9. Servocontrol (18) according to any one of the preceding claims, wherein the body (72) comprises at least one shaped portion (88), the external surface (90) of the shaped portion (88) conforming to the shape of at least one electronic, mechanical and / or hydraulic accessory (70) and / or at least one tubular cavity (98), in particular at least one tubular cavity (98) whose neutral fiber (100) is curved.

10. Servocontrol (18) according to claim 9, wherein the shaped portion (88) of the body (72) has a thickness (E), taken orthogonally with respect to the external surface (90) of the shaped portion (88) between the external surface (90) and: - the nearest tubular cavity (98); or - the nearest electronic, mechanical and / or hydraulic accessory (70); the thickness (E) being between 1 mm and 10 mm, preferably between 1 mm and 5 mm.

11. Architecture (14) for controlling the position of a moving element (12) of an aircraft (10), comprising: - a device (16) for generating a movement command for the moving element (12) configured to generate a movement command for the moving element (12); and - a servo control (18) according to any one of the preceding claims, intended for controlling the position of the moving element (12), as a function of the movement command for the moving element (12).

12. A method (200) for producing a servo control (18) according to any one of claims 1 to 10, comprising the following steps: - forming (210) at least one hydraulic cylinder of the power device (30); - producing (220) a blank (71) of the body (72) of at least one control unit (62) by additive manufacturing such that at least one tubular cavity (98) has a curved neutral axis (100); - producing (230) the body (72) of at least one control unit (62) by machining the blank (71); - forming (240) the at least one control unit (62) of the control device (60) by installing the electronic, mechanical and / or hydraulic accessories (70) in the body (72); - assembly (250) of the power device (30) and the control device (60) to form the servo control (18).

13. Method (200) according to claim 12, wherein the step (220) of making the rough (71) of the body (72) of at least one pilot unit (62) is devoid of the use of additive manufacturing support.

14. A method (200) according to claim 13, wherein the blank (71) of the body (72) extends along a principal direction (D) from rear to front, the principal direction (D) being parallel to the cylinder axis (A-A') when the power device (30) and the pilot device (60) are assembled, additive manufacturing being carried out along the principal direction (D) from rear to front during the step (220) of manufacturing the blank (71) of the body (72) of at least one pilot unit (62), the blank (71) of the body (72) having at least one cantilevered portion (160), any surface of the at least one cantilevered portion (160) oriented substantially rearward with respect to the principal direction (D) having an angle (a) with the principal direction (D) less than or equal at 45°.

15. Method (200) according to claim 14, wherein, during the making (230) of the body (72) of at least one pilot unit (62), the surfaces of at least one cantilevered portion (160) oriented substantially towards the rear with respect to the main direction (D) are machined to give them their final shape.

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