Portion of aircraft including a cabin trim panel

Abstract

Aircraft Portion Including a Cabin Panel The aircraft portion (10) comprises: - a fuselage (12) having a ceiling (20) and a fuselage side section (22) delimiting a cabin (14); - at least one technical device (30) mounted on the fuselage side section; - a panel (40) intended to at least partially conceal the at least one technical device from the cabin; the panel being rotatably mounted on the ceiling between: - a paneling position in which the panel at least partially conceals the at least one technical device from the cabin by being retained on the fuselage side section; - a maintenance position in which the panel is arranged away from the fuselage side section in a vertical plane so as to provide access to the at least one technical device. Figure for abbreviation: Figure 3

Description

Title of the invention: Portion of an aircraft comprising a cabin trim panel

[0001] The present invention relates to an aircraft portion comprising a fuselage, at least one technical equipment and at least one trim panel intended to at least partially conceal the at least one technical equipment from the cabin.

[0002] For example, in a known aircraft portion, the technical equipment is mounted on an internal surface of the body panel, the body panel being rotatably mounted around a horizontal axis of rotation on a lateral portion of the fuselage.

[0003] In such a portion of the aircraft, when not undergoing maintenance, the trim panel at least partially conceals the technical equipment from the cabin by being secured to a fuselage ceiling. When maintenance is required, the trim panel is rotated about its horizontal axis of rotation to a maintenance position in which the trim panel is positioned away from the ceiling, so that the internal surface of the trim panel on which the technical equipment is mounted faces substantially towards the interior of the cabin. This allows an operator access to the technical equipment to perform the maintenance operation.

[0004] However, in such a portion of the aircraft, the fact that the equipment is mounted on the fairing panel necessitates long lengths of electrical cables, conduits, and / or mechanical components connected to said equipment. Such an arrangement also requires slack management on these cables, conduits, and / or components.

[0005] Furthermore, with such a section of the aircraft, it is necessary to provide a wedge to hold the fairing panel in the maintenance position so that the operator can properly perform the maintenance operation on the equipment concerned, without the fairing panel swinging around the axis of rotation. This then complicates the fairing panel.

[0006] One object of the invention is therefore to propose a portion of an aircraft allowing a simplified arrangement of technical equipment while allowing easy maintenance operations on said equipment.

[0007] To this end, the invention relates to a portion of an aircraft comprising:

[0008] - a fuselage comprising a roof and a lateral fuselage portion delimiting a cabin;

[0009] - at least one technical equipment mounted on the lateral portion of the fuselage;

[0010] - at least one trim panel intended to at least partially conceal the minus technical equipment in relation to the cabin;

[0011] at least one cladding panel being mounted rotatably around a horizontal axis of rotation on the ceiling between:

[0012] - a cladding position in which the cladding panel hides at least at least one piece of technical equipment vis-à-vis the cabin by being retained on the lateral portion of the fuselage;

[0013] - a maintenance position in which the trim panel is arranged at the gap in the lateral portion of the fuselage in a substantially vertical plane so as to free up access to at least one piece of technical equipment.

[0014] Thanks to the invention, the equipment is mounted on the lateral portion of the fuselage, which, on the one hand, reduces its size and, on the other hand, eliminates the need for a specific device to prevent the panel from swinging during maintenance. This also avoids the need for significant lengths of electrical cables, conduits, and / or mechanical components for connecting to the technical equipment.

[0015] Furthermore, thanks to the invention, the maintenance operation is simplified since, to perform it, the operator only has to move the rotating fairing panel around the horizontal axis of rotation away from the lateral portion of the fuselage and leave the panel suspended from the ceiling. This gives the operator direct access to the equipment, which is fixed in position relative to the side wall.

[0016] According to other advantageous aspects of the invention, the aircraft portion comprises one or more of the following features, taken individually or in all technically possible combinations:

[0017] - the fuselage extends along a fuselage axis and has a median sagittal plane including the fuselage axis, the axis of rotation being substantially parallel to the fuselage axis, the axis of rotation being offset towards the median sagittal plane relative to the lateral portion of the fuselage;

[0018] - the cladding panel includes at least one hinge mounted to rotate around of the rotation axis on the ceiling between the dressing position and the maintenance position;

[0019] - the ceiling includes a rod extending substantially parallel to the axis of rotation, the cladding panel comprising at least one load-bearing element including a hook, the hook cooperating with the rod so that the load-bearing element is suspended from the rod;

[0020] - the cladding panel includes a main wall, at least one hinge articulating the main wall with respect to at least one load-bearing element such that:

[0021] - the main wall at least partially conceals at least one piece of equipment technical aspects of the cabin in the dressing position; and

[0022] - the main wall is arranged away from the lateral portion of the fuselage in a a substantially vertical plan so as to provide access to at least one piece of technical equipment in the maintenance position;

[0023] - the lateral portion of the fuselage comprises a main wall and at least one shelf extending substantially in a horizontal plane from the main wall of the lateral portion of the fuselage, with at least one piece of technical equipment mounted on at least one shelf;

[0024] - the cladding panel is devoid of technical equipment;

[0025] - at least one technical equipment comprises at least one of the following: a lighting device, a sound device, an air conditioning device, a display device, a control device for other technical equipment, an oxygen therapy device;

[0026] - the aircraft portion further comprises a configurable locking system between a locked configuration in which the locking system is capable of holding at least one cladding panel in the cladding position and an unlocked configuration in which the locking system is capable of allowing the movement of at least one cladding panel from the cladding position to the maintenance position;

[0027] - the aircraft portion further comprises a control device comprising a control device capable of being operated by an operator to change the configuration of the locking system from the locked configuration to the unlocked configuration, the control device being arranged on at least one trim panel.

[0028] The invention further relates to a portion of an aircraft comprising:

[0029] - a fuselage comprising a roof and a lateral fuselage portion delimiting a cabin;

[0030] - at least one technical equipment mounted on the lateral portion of the fuselage;

[0031] - at least one trim panel intended to at least partially conceal the less a technical equipment vis-à-vis the cabin, comprising a main wall having an internal surface oriented towards the ceiling and / or the lateral portion of the fuselage, the main wall of at least one trim panel being separated from the ceiling and / or the lateral portion of the fuselage by at least one gap;

[0032] at least one cladding panel being mounted rotatably around a horizontal axis of rotation between:

[0033] - a cladding position in which the cladding panel hides at least at least partially one piece of technical equipment vis-à-vis the cabin;

[0034] - a maintenance position in which the trim panel is arranged so as to free up access to at least one piece of technical equipment;

[0035] the aircraft portion further comprising a locking system configurable between a locked configuration in which the locking system is capable of holding at least one trim panel in the trim position and an unlocked configuration in which the locking system is capable of allowing the movement of at least one trim panel from the trim position to the maintenance position,

[0036] the aircraft portion further includes a locking system control device, comprising a control member capable of being actuated by an operator to change the locking system configuration from the locked configuration to the unlocked configuration and arranged on the internal surface of the main wall of at least one dressing panel so as to be accessible by the operator via at least one gap when at least one dressing panel is in the dressing position;

[0037] - the locking system includes at least one locking mechanism comprising a locking element mounted on the body panel and a complementary locking element mounted on the lateral portion of the fuselage,

[0038] the locking element being movable between:

[0039] - a locking position in which the locking element is able to cooperate with the complementary locking element so that the locking element and the complementary locking element are fixed to each other; and

[0040] - an unlocked position in which the locking element is detached from the additional locking element;

[0041] the control device being configured to control at least one locking mechanism such that:

[0042] - in the locked configuration, the locking element is in the position of locking; and

[0043] - in the unlocked configuration, the locking element is in the position unlocking;

[0044] - at least one locking mechanism includes a configured return element to force the locking element towards the locking position;

[0045] - the locking system comprises a plurality of locking mechanisms and a centralized control device for the locking mechanisms configured so that the control device controls all the locking mechanisms such that:

[0046] - in the locked configuration, all the locking elements are in the locked position; and

[0047] - in the unlocked configuration, all the locking elements are in the unlocked position;

[0048] - the locking mechanisms are arranged so that the elements of The locking elements are aligned along a first line substantially parallel to the axis of rotation, and the complementary locking elements are aligned along a second line substantially parallel to the first line.

[0049] the locking elements comprising a proximal locking element arranged at a proximal end of the cladding panel, a distal locking element arranged at a distal end of the cladding panel opposite the proximal end of the cladding panel and at least one intermediate locking element located between the proximal and distal locking elements,

[0050] the centralized control device for the locking mechanisms comprising:

[0051] - a central rod extending substantially along the first line through the locking elements; and

[0052] - for each locking mechanism, a tube extending around the rod central;

[0053] each tube being integral with the locking element of the corresponding locking mechanism,

[0054] each tube being movable in translation along the first line in an unlocking direction to bring the locking element of the corresponding locking mechanism into the unlocking position and in a locking direction opposite to the locking direction to bring the locking element of the corresponding locking mechanism into the locking position;

[0055] - the return element of each locking mechanism secures the element of corresponding locking and the corresponding tube with the neighboring tube so that the movement of the corresponding tube causes the movement of the neighboring tube and the neighboring locking element;

[0056] - the control device includes a hook attached to a tube of the centralized control device for the locking mechanisms, the hook being movable in the locking and unlocking directions, the actuation of the control element causing the hook to move in the unlocking direction, the movement of the hook in the unlocking direction causing the tube to move in the unlocking direction;

[0057] - the control element is offset from the first line in a direction of control substantially perpendicular to the first line, the device of control also including a cable connecting the control unit and the locking system;

[0058] - the control member includes a lever that can be moved according to the direction of control, the control device further comprising a pulley cooperating with the cable so that the movement of the lever in the direction of control causes the movement of the hook in the direction of unlocking;

[0059] - the locking system includes a reset device configured for constrain the tubes according to the locking direction, the re-priming device comprising a stop element attached to the cladding panel and a return element attached on one side to the stop element and on the other side to at least one tube;

[0060] - the stop element is arranged between the distal locking element and the element of locking adjacent to the distal locking element,

[0061] the stop element comprising a body delimiting a cylindrical cavity through which the central rod of the locking mechanism extends, the return element of the resetting device being arranged around the central rod between the body of the stop element and the distal locking element,

[0062] the return element of the priming device constraining all the tubes in the locking direction.

[0063] - the locking element comprises a movable hook that rotates around a axis of rotation between an engagement position in which said hook is capable of engaging a pin of the corresponding complementary locking element and a release position in which said hook is capable of disengaging from said pin,

[0064] the hook being in the hooking position when the locking element is in the locking position and in the release position when the locking element is in the unlocking position,

[0065] the locking element further comprising a lever capable of being actuated by the control device to move the corresponding hook from the latching position to the release position or vice versa,

[0066] the locking element further comprising a cam integral with the lever of the locking element and a counter-cam integral with the hook of the locking element, the cam and the counter-cam being rotatable about an axis of rotation substantially parallel to the axis of rotation of the hook of the locking element,

[0067] the actuation of the locking element lever causing a rotation of the cam around its axis of rotation, the rotation of the cam around its axis of rotation causing the counter-cam to rotate around its axis of rotation, the rotation of the counter-cam around its axis of rotation causing the locking element hook to move towards its release position;

[0068] - at least one cladding panel is mounted to rotate around the axis of rotation horizontal on the ceiling, the main wall of at least one cladding panel extending between an upper edge facing the ceiling and a lower edge opposite the upper edge, the upper edge being separated from the ceiling by at least one gap;

[0069] - the gap has a width between 1 cm and 5 cm.

[0070] The invention will become clearer upon reading the following description, given solely by way of non-limiting example, and made with reference to the drawings in which:

[0071] [Fig-1] - [Fig.1] is a simplified schematic representation of an aircraft comprising a portion of an aircraft according to the invention;

[0072] [Fig.2] - [Fig.2] is a simplified schematic perspective representation of a portion of the aircraft of [Fig.1], according to the invention, in which the dressing panel is in the dressing position;

[0073] [Fig.3] - [Fig.3] is a simplified schematic perspective representation of the aircraft portion of [Fig.2], in which the trim panel is in the maintenance position;

[0074] [Fig.4] - [Fig.4] is a schematic perspective representation of the portion aircraft of [Fig.2], in which the ceiling, the lateral portion of the fuselage and the technical equipment have been omitted, the locking system being in the locked configuration;

[0075] [Fig.5] - [Fig.5] is a schematic perspective representation of the portion aircraft of [Fig.3], in which the ceiling, the lateral portion of the fuselage and the technical equipment have been omitted, the locking system being in the unlocked configuration;

[0076] [Fig.6] - [Fig.6] is a schematic top view representation of the portion aircraft of [Fig.2], in which the ceiling, the lateral portion of the fuselage and the technical equipment have been omitted, the locking system being in the locked configuration;

[0077] [Fig.7] - [Fig.7] is an enlarged schematic representation of portion VII of the [Fig. 6]; and

[0078] [Fig.8] - [Fig.8] is an enlarged schematic representation of a portion VIII of [Fig.6];

[0079] [Fig.9] - [Fig.9] is a schematic representation of an enlarged view in perspective of a locking mechanism of the aircraft portion locking system of [Fig.6] (in particular the right locking mechanism of [Fig.8]).

[0080] With reference to figures 1 to 9, a portion of aircraft 10 according to the invention is disclosed.

[0081] The aircraft portion 10 comprises a fuselage 12, at least one technical equipment 30 and at least one trim panel 40 intended to conceal at least partially the at least one technical equipment 30 from a cabin 14 of the aircraft.

[0082] In what follows, an aircraft portion 10 is described comprising a plurality of technical equipment 30 (in particular four technical equipment 30 as illustrated in the examples in Figures 2 and 3) and a single trim panel 40. Of course, those skilled in the art will understand that the invention also applies in cases where the aircraft portion 10 comprises a single technical equipment 30 and / or a plurality of trim panels 40.

[0083] The aircraft portion 10 further includes a floor (not illustrated), delimiting the cabin 14 with the fuselage 12.

[0084] Advantageously, the aircraft portion 10 further comprises a locking system 70 and a locking system control device 100 for the locking system 70.

[0085] With reference to [Fig.1], the fuselage 12 extends along a fuselage axis X-X' and has a median sagittal plane SM comprising the fuselage axis X-X'.

[0086] The fuselage 12 includes a ceiling 20 and a lateral fuselage portion 22 delimiting the cabin 14.

[0087] In the example of Figures 2 and 3, the ceiling 20 extends substantially parallel to the floor and substantially perpendicular to the median sagittal plane SM of the aircraft. However, the present invention is not limited to such a ceiling 20, and those skilled in the art will understand that the ceiling 20 may have a different shape, such as, for example, a vaulted shape.

[0088] For example, the ceiling 20 includes a rod 21 extending substantially parallel to an axis of rotation RI of the cladding panel 40.

[0089] In the example of Figures 2 and 3, the fuselage side portion 22 extends substantially perpendicularly to the floor and substantially parallel to the median sagittal plane SM of the aircraft. However, the present invention is not limited to such a fuselage side portion 22, and those skilled in the art will understand that the fuselage side portion 22 may have a different shape, such as, for example, a curved shape.

[0090] Advantageously, the lateral portion of the fuselage 22 comprises a main wall 24 and at least one shelf 26 extending substantially in a horizontal plane H from the main wall 24. By "horizontal" is meant a plane extending substantially parallel to the floor of the aircraft portion 10.

[0091] In particular, the main wall 24 of the lateral portion of the fuselage 22 delimits the cabin 14 with the floor and ceiling 20.

[0092] In particular, shelf 26 is intended to be arranged above a passenger living area of ​​the aircraft, for example, above aircraft seats, an aircraft bed, or the like.

[0093] The technical equipment 30 is mounted on the lateral portion of the fuselage 22.

[0094] In particular, as illustrated in the example of Figures 2 and 3, the equipment 30 techniques are mounted on shelf 26.

[0095] The technical equipment 30 includes at least one of the following: a lighting device, a sound device, an air conditioning device, a display device, a control device for other technical equipment, an oxygen therapy device.

[0096] For example:

[0097] - the lighting device includes a reading light, a night light or other;

[0098] - the air conditioning device includes a ventilation outlet, a blower with adjustable flow rate or other;

[0099] - the display device includes electronic signage, a screen or other;

[0100] - the control device includes a button or other; and / or

[0101] - The oxygen therapy device comprises an oxygen container, a mask oxygen, suitable piping, or something else.

[0102] In particular, the technical equipment 30 each includes a main part 32 intended not to be accessible from the cabin 14 under normal conditions of aircraft operation (excluding maintenance for example) in order, for example, to protect this main part 32 and / or improve the aesthetics of the cabin 14. In particular, the main parts 32 of the technical equipment 30 include electronic, hydraulic and / or mechanical components ensuring the operation of the lighting, sound, air conditioning, display, control and / or oxygen therapy devices but not requiring to be accessible by anyone under normal conditions of aircraft operation.

[0103] For example, the technical equipment 30 each includes an auxiliary part 34 intended to be permanently accessible from the cabin 34 under normal operating conditions of the aircraft, for example to allow the aircraft passengers to control the main part 32. In particular, the auxiliary parts 34 of the technical equipment 30 include buttons, screens, lights, ventilation openings, illuminated pictograms, etc.

[0104] The cladding panel 40 is mounted to rotate around the horizontal axis of rotation RI, in particular on the ceiling 20 between a cladding position (visible in figures 2, 4 and 6 to 9) and a maintenance position (visible in figures 3 and 5).

[0105] In the dressing position, the dressing panel 40 at least partially conceals the technical equipment 30 vis-à-vis the cabin 14, in particular the parts main 32 of the technical equipment 30, being retained on the lateral portion of fuselage 22.

[0106] In the maintenance position, the trim panel 40 is arranged away from the lateral portion of the fuselage 22 in a substantially vertical plane V (see [Fig.3]) so as to free access to the technical equipment 30, in particular to the main parts 32 of the technical equipment 30.

[0107] For example, the trim panel 40 is devoid of technical equipment 30. In other words, none of the technical equipment 30 of the aircraft portion 10 is included in and / or mounted on the trim panel 40.

[0108] For example, the axis of rotation RI is substantially parallel to the fuselage axis X-X' and is offset towards the median sagittal plane SM relative to the lateral portion of the fuselage 22.

[0109] Advantageously, the cladding panel 40 comprises a main wall 42, at least one hinge 56 and at least one load-bearing element 60.

[0110] In the example of Figures 4 to 9, the cladding panel 40 comprises a main wall 42, a plurality of hinges 56 and a plurality of load-bearing members 60. The example of Figures 4 to 9 is described in more detail below. Of course, the invention also applies in the case where the cladding panel 40 comprises a single hinge 56 and / or a single load-bearing member 60.

[0111] In the dressing position, the main wall 42 of the dressing panel 40 delimits with the ceiling 20 and the lateral portion of the fuselage 22, in particular the main wall 24 of the lateral portion of the fuselage 22 and the shelf 26, a space 44 for receiving the technical equipment 30.

[0112] In the dressing position, the main wall 42 of the dressing panel 40 at least partially conceals the technical equipment 30 opposite the cabin 14 by being retained on the lateral portion of the fuselage 22, in particular on the shelf 26. In particular, in the dressing position, the main wall 42 completely conceals the main parts 32 of the technical equipment 30 opposite the cabin 14.

[0113] In the maintenance position, the main wall 42 of the trim panel 40 is arranged away from the lateral portion of the fuselage 22 in the substantially vertical plane V so as to free access to the technical equipment 30.

[0114] Advantageously, the main wall 42 of the skin panel 40 is separated from the ceiling 20 and / or the lateral portion of the fuselage 22 by at least one gap 46.

[0115] According to the example illustrated in Figures 2 and 3, the main wall 42 of the cladding panel 40 is separated from the ceiling 20 by at least one gap 46, in particular a gap 46 extending substantially parallel to the axis of rotation RI.

[0116] In particular, the main wall 42 of the cladding panel 40 has an upper edge 48 intended to extend in relation to the ceiling 20 and a lower edge 50 opposite the upper edge 48 intended to extend in relation to the lateral portion of the fuselage 22.

[0117] According to the example illustrated in figures 2 and 3, the upper edge 48 of the main wall 42 of the cladding panel 40 is spaced from the ceiling 20 by the gap 46.

[0118] For example, the gap 46 has a width between 1 cm and 5 cm.

[0119] The main wall 42 of the cladding panel 40 has an internal surface 52 oriented towards the ceiling 20 and / or the lateral portion of the fuselage 22. In particular, the internal surface 52 is oriented towards the technical equipment 30 in the cladding position and in the maintenance position.

[0120] The hinges 56 are mounted to rotate around the axis of rotation RI on the ceiling 20, in particular by means of the force-recovery elements 60, between the dressing position and the maintenance position.

[0121] In particular, the hinges 56 allow the rotational movement of the main wall 42 of the cladding panel 40 between the cladding position and the maintenance position.

[0122] In particular, the hinges 56 articulate the main wall 42 of the cladding panel 40 with respect to the load-bearing members 60 so that the main wall 42 of the cladding panel 40 can be moved between the cladding and maintenance positions.

[0123] The force recovery members 60 each have a hook 62 cooperating with the rod 21 so that the force recovery member 60 is suspended from the rod 21.

[0124] The locking system 70 is configurable between a locked configuration in which the locking system 70 is able to hold the cladding panel 40 in the cladding position and an unlocked configuration in which the locking system 70 is able to allow the movement of the cladding panel 40 from the cladding position to the maintenance position.

[0125] Advantageously, the locking system 70 comprises at least one locking mechanism 72, in particular a plurality of locking mechanisms 72, as illustrated in the example of Figures 4 to 9. The example of Figures 4 to 9 is described in more detail below. Of course, the invention also applies in the case where the locking system 70 comprises a single locking mechanism 72.

[0126] Even more advantageously, the locking system 70 includes a device 120 for centralizing the control of the locking mechanisms 72.

[0127] Even more advantageously, the locking system 70 further includes a re-priming device 130.

[0128] The locking mechanisms 72 each comprise a locking element 74 and a complementary locking element 84.

[0129] Advantageously, the locking mechanisms 72 each include a return element 90 configured to constrain the locking element 74 towards a locking position described in more detail below.

[0130] The locking mechanisms 72 are arranged so that the locking elements 74 are aligned along a first line L1 substantially parallel to the axis of rotation RI and the complementary locking elements 84 are aligned along a second line L2 substantially parallel to the first line L1.

[0131] The locking elements 74 are mounted on the cladding panel 40, in particular on the internal surface 52 of the main wall 42 of the cladding panel 40.

[0132] With reference to Figures 4 to 9, the locking elements 74 comprise a proximal locking element 74A arranged at a proximal end 76A of the dressing panel 40, a distal locking element 74B arranged at a distal end 76B of the dressing panel 40 opposite the proximal end 76A of the dressing panel 40, and, for example, at least one intermediate locking element 74C located between the proximal locking elements 74A and distal locking elements 74B. Here, the proximal ends 76A and distal ends 76B are defined along the fuselage axis X-X'.

[0133] Each locking element 74 is movable between:

[0134] - a locking position in which said locking element 74 is suitable to cooperate with the corresponding complementary locking element 84, so that said locking element 74 and said complementary locking element 84 are joined together; and

[0135] - an unlocked position in which said locking element 74 is detached from said additional locking element 84.

[0136] For example, as seen in Figures 5 and 7 to 9, each locking element 74 includes a hook 78 that is movable and rotatable about an axis of rotation R2 between a hooking position (visible in Figures 7 to 9) in which said hook 78 is able to hook a pin 86 of the corresponding complementary locking element 84 and a release position (visible in [Fig.5]) in which said hook 78 is able to disengage from said pin 86.

[0137] For each locking element 74, in the locking position, the corresponding hook 78 is in the hooking position and in the unlocking position, the corresponding hook 78 is in the release position.

[0138] Advantageously, as can be seen in figures 7 to 9, each locking element 74 further includes a lever 80 suitable for being actuated by the control device 100 to move the corresponding hook 78 from the hooking position to the release position or vice versa.

[0139] With reference to [Fig.9], advantageously, each locking element 74 further comprises a cam 81 integral with the lever 80 of the corresponding locking element 74 and a counter-cam 92 integral with the hook 78 of the corresponding locking element 74.

[0140] The cam 81 and the counter cam 92 are in particular movable in rotation around an axis of rotation R3 substantially parallel to the axis of rotation R2 of the hook 78 of the corresponding locking element 74.

[0141] For each locking element 74, the actuation of the lever 80, in particular by the control device 100, causes a rotation of the cam 81 around its axis of rotation R3, in particular in a first direction, which causes the counter-cam 92 to rotate around its axis of rotation R3, in particular in said first direction, which causes the hook 78 of the corresponding locking element 74 to move towards its release position.

[0142] Advantageously, the locking element 74 further includes a return member (not visible in the figures) which, in the absence of actuation of the lever 80, is configured to constrain the counter cam 92 in rotation around its axis of rotation R3, in particular in a second direction opposite to the first direction, which constrains the movement of the hook 78 of the corresponding locking element 74 towards its hooking position.

[0143] The use of the cam 81, the counter-cam 92 and advantageously of the return member configured to constrain the counter-cam 92, makes it possible to compensate for play in the locking system 70, which otherwise could interfere with the simultaneous locking or unlocking of all the locking mechanisms 72.

[0144] The additional locking elements 84 are mounted on the lateral portion of the fuselage 22, in particular on the shelf 26.

[0145] For example, each additional locking element 84 includes a pawn 86.

[0146] In particular, the pins 86 are fixed on the lateral portion of the fuselage 22, in particular on the shelf 26. Advantageously, the pins 86 extend towards the trim panel 40.

[0147] Advantageously, the return element 90 of each locking mechanism 72 secures:

[0148] - the corresponding locking element 74 and a corresponding tube 124 (described (more details below); with

[0149] - a neighboring tube 124;

[0150] so that the displacement of the corresponding tube 124 causes the displacement of the neighboring tube 124 and of the neighboring locking element 74.

[0151] The control device 100 includes a control element 102 capable of being actuated by an operator to change the configuration of the locking system 70 from the locked configuration to the unlocked configuration.

[0152] Advantageously, the control device 100 further includes a hook 106.

[0153] Even more advantageously, the control device 100 further includes a cable 108 connecting the control element 102 and the locking system 70.

[0154] Even more advantageously, the control device 100 further includes a pulley 110 cooperating with the cable 108.

[0155] In particular, the control device 100 is configured to control the locking mechanisms 72 so that:

[0156] - in the locked configuration, the locking elements 74 are in the locking position; and

[0157] - in the unlocked configuration, the 74 locking elements are in the unlock position.

[0158] With reference to [Fig. 7], the control element 102 is arranged on the cladding panel 40, in particular on the inner surface 52 of the main wall 42 of the cladding panel 40, so as to be accessible by the operator via the gap 46 when the cladding panel 40 is in the cladding position. According to the example illustrated in Figures 2 to 8, the control element 102 is arranged near the upper edge 48 of the main wall 42 of the cladding panel 40.

[0159] Advantageously, the control element 102 is offset from the first line L1 along a DC control direction substantially perpendicular to the first line L1.

[0160] Even more advantageously, the control member 102 includes a lever 104 movable according to the DC control direction.

[0161] In particular, the actuation of the control member 102 causes the movement of the hook 106 in an unlocking direction Dl.

[0162] With reference to [Fig.7], the hook 106 is attached to a tube 124 of the device 120 for centralizing the control of the locking mechanisms 72. For example, as illustrated in Figures 6 and 7, the hook 106 is attached to the tube 124 extending between the proximal locking element 74A and the locking element 74 adjacent to the proximal locking element 74A.

[0163] The hook 106 is movable in a locking direction D2 and in the unlocking direction DL

[0164] The movement of the hook 106 in the unlocking direction Dl causes the tube 124 to which the hook 106 is attached to move in the unlocking direction DL. Advantageously, the movement of the tube 124 to which is secured the hook 106 in the unlocking direction DI causes the other tubes 124 to move in the unlocking direction Dl.

[0165] With reference to figures 4 to 7, for example, the cable 108 mechanically connects the lever 104 of the control member 102 and the locking system 70, in particular by mechanically connecting the lever 104 of the control member 102 and the hook 106 of the control device 100.

[0166] With reference to [Fig.7], the pulley 110 cooperates with the cable so that the movement of the lever 104 of the control member 102 in the DC control direction causes the movement of the hook 106 in the unlocking direction Dl.

[0167] With reference to Figures 4 to 8, the centralized control device 120 for the locking mechanisms 72 is configured so that the control device 100 controls all the locking mechanisms 72 such that:

[0168] - in the locked configuration, all 74 locking elements are in the locked position; and

[0169] - in the unlocked configuration, all 74 locking elements be in the unlocked position.

[0170] In particular, the device 120 for centralizing the control of the locking mechanisms 72 includes:

[0171] - a central rod 122 extending substantially along the first line L1 through the locking elements 74, in particular via the levers 80 of the locking elements 74; and

[0172] - for each locking mechanism 72, a tube 124 extending around the rod central 122.

[0173] With reference to [Fig.6], each tube 124 is integral with the locking element 74 of the corresponding locking mechanism 72, in particular with the corresponding lever 80.

[0174] Each tube 124 is movable in translation along the first line L1:

[0175] - in the unlocking direction Dl to drive the locking element 74 of the corresponding locking mechanism 72 in the unlocked position, in particular by actuation of the corresponding lever 80; and

[0176] - in the locking direction D2 opposite to the locking direction D1 to drive the locking element 74 of the corresponding locking mechanism 72 into the locked position, in particular by actuating the corresponding lever 80.

[0177] The re-priming device 130 is configured to constrain the tubes 124 according to the locking direction D2.

[0178] With reference to [Fig.8], the re-priming device 130 comprises a stop element 132 integral with the cladding panel 40, in particular mounted on the internal surface 52 of the main wall 42 of the cladding panel 40, and a return element 136 integral on one side with the stop element 132 and on the other side with at least one tube 124.

[0179] The stop element 132 is in particular arranged between the distal locking element 74B and the locking element 74 adjacent to the distal locking element 74B.

[0180] The stop element 132 includes a body 134 delimiting a cylindrical cavity through which the central rod 122 of the centralizing device 120 extends.

[0181] The return element 136 of the re-priming device 130 is arranged around the central rod 122 between the body 134 of the stop element 132 and the distal locking element 74B, in particular the lever 80 of the distal locking element 74B.

[0182] The return element 136 of the repriming device 130 forces all the tubes 124 in the locking direction D2, in particular by forcing the lever 80 of the distal locking element 74B so that it is actuated in order for the distal locking element 74B to be in the locked position. Consequently, by action of the return elements 90, each locking element 74 is drawn into the locked position.

[0183] The following describes the use of aircraft portion 10.

[0184] It is assumed that initially, the cladding panel 40 is in the cladding position.

[0185] When an operator wishes to have access to the technical equipment 30, in particular to the main parts 32 of the technical equipment 30, for example to carry out maintenance on the technical equipment 30, the operator moves the cover panel 40 from the cover position to the maintenance position.

[0186] To do this, for example, before moving the trim panel 40, the operator actuates the control device 102 to change the configuration of the locking system 70 from the locked configuration to the unlocked configuration.

[0187] In particular, the operator accesses the control unit 102 via the gap between on the one hand the main wall 42 of the body panel 40 and on the other hand the ceiling 20 and / or the lateral portion of the fuselage 22.

[0188] Once the locking system 70 is in the unlocked configuration, the trim panel 40 is moved by the operator and / or by the effect of gravity to the maintenance position.

[0189] Once the maintenance is completed, the operator moves the dressing panel 40 to the dressing position. Once in the dressing position, the dressing panel 40 is held in the dressing position because the locking system 70 has returned to the locked configuration.

[0190] Thanks to the invention, the space required by the technical equipment 30 is reduced since the equipment is no longer mounted on the panel 40. Furthermore, it eliminates the need for a specific device to prevent the panel from swinging, thus preventing it from being stabilized when maintenance is performed on equipment attached to the panel. In addition, it eliminates the need for significant lengths of electrical cables, conduits, and / or mechanical components, since it is no longer necessary to provide sufficient lengths to allow for the movement of the panel equipped with the equipment.

[0191] Furthermore, thanks to the invention, the maintenance operation is simplified since the operator only needs to move the rotating panel around the horizontal axis of rotation away from the lateral portion of the fuselage and leave the panel suspended from the ceiling. The equipment itself is fixed in position relative to the side wall, and the operator can directly perform maintenance operations on the equipment, which is stable in position.

[0192] Also, thanks to the invention, very simple locking and unlocking in position is provided. The locking system is compact and easily operated via the control element. The control element is hidden from the aircraft passengers, located in the cabin, but remains easily accessible to the operator when maintenance is required.

[0193] The centralized control device for the locking mechanisms allows all locking mechanisms to be easily controlled using a single control device, for example.

Claims

Demands

1. Portion of aircraft (10) comprising: - a fuselage (12) having a ceiling (20) and a lateral fuselage portion (22) delimiting a cabin (14); - at least one technical equipment (30) mounted on the lateral fuselage portion (22); - at least one covering panel (40) intended to at least partially conceal the at least one technical equipment (30) from the cabin (14); the at least one covering panel (40) being rotatably mounted about a horizontal axis of rotation (RI) on the ceiling (20) between: - a covering position in which the covering panel (40) at least partially conceals the at least one technical equipment (30) from the cabin (14) by being retained on the lateral fuselage portion (22);- a maintenance position in which the trim panel (40) is arranged away from the lateral portion of the fuselage (22) in a substantially vertical plane (V) so as to free access to at least one technical equipment (30).

2. Portion of aircraft (10) according to claim 1, wherein the fuselage (12) extends along a fuselage axis (X-X') and has a median sagittal plane (SM) comprising the fuselage axis (X-X'), the rotation axis (RI) being substantially parallel to the fuselage axis (X-X'), the rotation axis (RI) being offset towards the median sagittal plane (SM) relative to the lateral portion of fuselage (22).

3. Portion of aircraft (10) according to claim 1 or 2, wherein the dressing panel (40) includes at least one hinge (56) rotatably mounted about the axis of rotation (RI) on the ceiling (20) between the dressing position and the maintenance position.

4. Portion of aircraft (10) according to any one of the preceding claims, wherein the ceiling (20) comprises a rod (21) extending substantially parallel to the axis of rotation (RI), the trim panel (40) comprising at least one load-bearing member (60) having a hook (62), the hook (62) cooperating with the rod (21) so that the load-bearing member (60) is suspended from the rod (21).

5. Portion of aircraft (10) according to claims 3 and 4, wherein the trim panel (40) comprises a main wall (42), at least one hinge (56) articulating the main wall (42) with respect to at least one load-bearing member (60) such that: - the main wall (42) at least partially conceals at least one technical equipment (30) from the cabin (14) in the trim position; and - the main wall (42) is arranged away from the lateral portion of the fuselage (22) in a substantially vertical plane (V) so as to provide access to at least one technical equipment (30) in the maintenance position.

6. Portion of aircraft (10) according to any one of the preceding claims, wherein the lateral portion of the fuselage (22) comprises a main wall (24) and at least one shelf (26) extending substantially in a horizontal plane (H) from the main wall (24) of the lateral portion of the fuselage (22), at least one technical equipment (30) being mounted on the at least one shelf (26).

7. Portion of aircraft (10) according to any one of the preceding claims, wherein the trim panel (40) is devoid of technical equipment (30).

8. Portion of aircraft (10) according to any one of the preceding claims, wherein at least one technical equipment (30) comprises at least one of the following: a lighting device, a sound device, an air conditioning device, a display device, a control device for other technical equipment, an oxygen therapy device.

9. Aircraft portion (10) according to any one of the preceding claims, wherein the aircraft portion (10) further comprises a locking system (70) configurable between a locked configuration in which the locking system (70) is capable of holding at least one trim panel (40) in the trim position and an unlocked configuration in which the locking system (70) is capable of allowing the movement of at least one trim panel (40) from the trim position to the maintenance position.

10. Portion of aircraft (10) according to claim 9, further comprising a control device (100) including a component control (102) capable of being operated by an operator to change the configuration of the locking system (70) from the locked configuration to the unlocked configuration, the control element (102) being arranged on at least one trim panel (40).

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