Aircraft portion with modular fluid distribution and associated arrangement method

Abstract

Aircraft portion with modular fluid distribution and associated arrangement method The aircraft portion (10) comprises: - a wall (20A), mounted at a first (P1) or second (P2) coordinate, intended to separate the first (16A) and second (16B) cabin portions; - a circuit (30) fluidically connecting a source (28) and the second cabin portion, comprising: - a pipe (32) comprising: - a first section (34A) delivering a fluid between the first and second coordinates; - a second section (34B) delivering the fluid behind the second coordinate; - a control device (44A) intended to be in the configuration: - open, in which the first and second sections are in fluid communication, when the wall is mounted at the first coordinate; - closed, in which the fluid communication is interrupted, when the wall is mounted at the second coordinate. Figure for abstract: Figure 1

Description

Title of the invention: Aircraft portion with modular fluid distribution and associated arrangement method

[0001] The present invention relates to a portion of an aircraft comprising:

[0002] - a fuselage delimiting a cabin extending along a longitudinal axis, the cabin comprising a first cabin portion and a second cabin portion;

[0003] - a first dividing wall extending substantially perpendicular to the longitudinal axis and being intended to separate the first cabin portion and the second cabin portion, the first partition wall being capable of being mounted on the fuselage at a first longitudinal coordinate or at a second longitudinal coordinate along the longitudinal axis, the second longitudinal coordinate being located behind the first longitudinal coordinate with respect to an orientation direction substantially parallel to the longitudinal axis; and

[0004] - at least one first fluidic circuit intended to fluidly connect at least a first source of a first fluid and the second cabin portion.

[0005] In particular, the fluid supplied by the first fluid source is air (having for example specific characteristics such as a defined temperature, and / or a defined pressure, etc.), the air being intended to be blown into the second cabin portion.

[0006] In such an aircraft portion, independence in the air supply between each cabin portion separated by a dividing wall is often desired. In particular, it may be desired to blow air having certain characteristics into a first cabin portion and to blow air having different characteristics into a second cabin portion. It is therefore necessary to adapt the fluid circuit according to the position in which the first dividing wall is mounted, in order to obtain this independence.

[0007] However, in some aircraft, the cabin configuration is modular. The partition walls can be placed at different locations within the cabin depending on the customer's wishes and therefore the lengths of the cabin portions vary depending on these wishes.

[0008] Furthermore, during the life of the aircraft, the partition walls can be dismantled and reassembled elsewhere in the cabin in order to adapt the size of the cabin portions to the wishes of the passengers, particularly in the event of a change of ownership.

[0009] Following such a change in configuration, it is required to adapt the fluid circuit according to the new position in which the partition wall is mounted. This adaptation work is tedious and may require the replacement of the circuits fluidics.

[0010] An aim of the invention is then to propose a portion of aircraft in which each fluid circuit is easily adaptable depending on the position in which each separation wall is installed.

[0011] To this end, the invention relates to a portion of aircraft comprising:

[0012] - a fuselage delimiting a cabin extending along a longitudinal axis, the cabin comprising a first cabin portion and a second cabin portion;

[0013] - a first separating wall intended to extend substantially perpendicularly directly to the longitudinal axis and intended to separate the first cabin portion and the second cabin portion, the first partition wall being adapted to be mounted on the fuselage at a first longitudinal coordinate or at a second longitudinal coordinate along the longitudinal axis, the second longitudinal coordinate being located behind the first longitudinal coordinate with respect to an orientation direction substantially parallel to the longitudinal axis;

[0014] - at least one first fluidic circuit intended to fluidly connect at least a first source of a first fluid and the second cabin portion, the at least one first fluid circuit comprising:

[0015] - at least one first pipe comprising:

[0016] - a first section comprising at least one first output capable of delivering the first fluid in the cabin between the first longitudinal coordinate and the second longitudinal coordinate;

[0017] - a second section comprising at least one second output capable of delivering the first fluid in the cabin behind the second longitudinal coordinate relative to the orientation direction, the first section of the at least one first pipe being intended to be fluidically connected to the at least one first source by the second section of the at least one first pipe;

[0018] - at least one first control device configurable between a configuration open, wherein the first section of the at least one first conduit is in fluid communication with the second section of the at least one first conduit, and a closed configuration, wherein the fluid communication between the first section of the at least one first conduit and the second section of the at least one first conduit is interrupted;

[0019] in which:

[0020] - the at least one first control device of the at least one first circuit fluidic is intended to be in open configuration when the first partition wall is mounted at the first longitudinal coordinate;

[0021] - the at least one first control device of the at least one first circuit fluidic is intended to be in closed configuration when the first se- preparation is mounted at the second longitudinal coordinate.

[0022] Thanks to the invention, the first fluid circuit is easily adaptable depending on the position in which the first partition wall is installed, by configuring the first fluid circulation control device in the open configuration or in the closed configuration. There is then no need to provide separate fluid circuits for each configuration of the cabin.

[0023] According to other advantageous aspects of the invention, the aircraft portion comprises one or more of the following characteristics, taken in isolation or in all technically possible combinations:

[0024] - the aircraft portion is such that:

[0025] - the first partition wall is capable of being mounted on the fuselage in addition to a third longitudinal coordinate, the third longitudinal coordinate being located behind the second longitudinal coordinate relative to the direction of orientation;

[0026] - the at least one second outlet is capable of delivering the first fluid into the cabin between the second longitudinal coordinate and the third longitudinal coordinate;

[0027] - the at least one first pipe comprises a third section comprising at least at least one third outlet capable of delivering the first fluid into the cabin behind the third longitudinal coordinate relative to the orientation direction, the second section of the at least one first pipe being intended to be fluidically connected to the at least one first source by the third section of the at least one first pipe;

[0028] - the at least one first fluidic circuit further comprises at least one second control device configurable between an open configuration, in which the second section of the at least one first conduit is in fluid communication with the third section of the at least one first conduit, and a closed configuration, in which the fluid communication between the second section of the at least one first conduit and the third section of the at least one first conduit is interrupted;

[0029] in which:

[0030] - when the at least one first partition wall is mounted at the second co longitudinal ordinate or at the first longitudinal coordinate, the at least one second control device of the at least one first fluid circuit is intended to be in open configuration;

[0031] - when the first partition wall is mounted at the third longitudinal coordinate tudinal, the at least one second control device of the at least one first fluid circuit is intended to be in closed configuration;

[0032] - the aircraft portion is such that:

[0033] - the cabin comprises a third cabin portion, the aircraft portion further comprising:

[0034] - a second dividing wall intended to extend substantially perpendicularly freely to the longitudinal axis and intended to separate the third cabin portion and the second cabin portion, the second partition wall being capable of being mounted on the fuselage at a fourth longitudinal coordinate or at a fifth longitudinal coordinate, the fourth longitudinal coordinate being located behind the third longitudinal coordinate relative to the direction of orientation, the fifth longitudinal coordinate being located behind the fourth longitudinal coordinate relative to the direction of orientation;

[0035] - at least one second fluidic circuit intended to fluidly connect at least a second source of a second fluid and the third cabin portion, the at least one second fluid circuit comprising:

[0036] - at least one second pipe comprising:

[0037] - a first section comprising at least one first output capable of delivering the second fluid in the cabin between the fourth longitudinal coordinate and the fifth longitudinal coordinate;

[0038] - a second section comprising at least one second output capable of delivering the second fluid in the cabin behind the fifth longitudinal coordinate relative to the orientation direction, the first section of the at least one second pipe being intended to be fluidically connected to the at least one second source by the second section of the at least one second pipe;

[0039] - at least one control device configurable between an open configuration, wherein the first section of the at least one second conduit is in fluid communication with the second section of the at least one second conduit, and a closed configuration, wherein the fluid communication between the first section of the at least one second conduit and the second section of the at least one second conduit is interrupted;

[0040] in which:

[0041] - the at least one control device of the at least one second fluid circuit is intended to be in an open configuration when the second partition wall is mounted at the fourth longitudinal coordinate;

[0042] - the at least one control device of the at least one second fluid circuit is intended to be in the closed configuration when the second partition wall is mounted at the fifth longitudinal coordinate;

[0043] - the aircraft portion is such that:

[0044] - the third section of the at least one first pipe is intended to be fluidly connected to at least one first source,

[0045] the first section of the at least one second pipe being intended to be fluidically connected to the third section of the at least one first pipe,

[0046] the at least one second fluid circuit comprising at least one intermediate control device configurable between an open configuration, in which the first section of the at least one second pipe is in fluid communication with the third section of the at least one first pipe, and a closed configuration, in which the fluid communication between the first section of the at least one second pipe and the third section of the at least one first pipe is interrupted,

[0047] in which:

[0048] - when the second partition wall is mounted at the fourth coordinate lon horizontally, the at least one intermediate control device of the at least one second fluid circuit is intended to be in a closed configuration;

[0049] - when the second partition wall is mounted at the fifth coordinate lon horizontally, the at least one intermediate control device of the at least one second fluid circuit is intended to be in open configuration;

[0050] - the aircraft portion further comprises:

[0051] - at least one auxiliary fluid circuit intended to fluidly connect at least a third source of a third fluid and the first cabin portion, the at least one auxiliary fluid circuit comprising at least one auxiliary pipe comprising a section comprising at least one outlet capable of delivering the third fluid into the cabin in front of the first longitudinal coordinate relative to the orientation direction, the section of the at least one auxiliary pipe being intended to be fluidically connected to the at least one third source;

[0052] the first section of the at least one first pipe being intended to be fluidically connected to the section of the at least one auxiliary pipe,

[0053] the at least one first fluid circuit comprising at least one intermediate control device configurable between an open configuration, in which the first section of the at least one first pipe is in fluid communication with the section of the at least one auxiliary pipe, and a closed configuration, in which the fluid communication between the first section of the at least one first pipe and the section of the at least one auxiliary pipe is interrupted,

[0054] in which:

[0055] - when the first partition wall is mounted at the first longitudinal coordinate tudinal, the at least one intermediate control device of the at least one first fluid circuit is intended to be in closed configuration;

[0056] - when the first partition wall is mounted at the second longitudinal coordinate tudinal, the at least one intermediate control device of the at least one first fluid circuit is intended to be in open configuration;

[0057] - when the first partition wall is mounted at the third longitudinal coordinate tudinal, the at least one intermediate control device of the at least one first fluid circuit is intended to be in open configuration;

[0058] - the aircraft portion is such that each control device comprises:

[0059] - a support permanently mounted on the corresponding sections of the corresponding pipe(s) so as to fluidly connect the corresponding sections of the corresponding pipe(s); and

[0060] - a control assembly comprising:

[0061] - a shutter element capable of being removably mounted on said support of so as to interrupt the fluid communication between the corresponding sections of the corresponding pipe(s); and

[0062] - a covering element capable of being removably mounted on said support replacing the shutter element so as to allow fluid communication between the corresponding sections of the corresponding pipe(s); and

[0063] in which each control device is:

[0064] - in closed configuration when the shutter element is mounted on said support;

[0065] - in open configuration when the covering element is mounted on said support;

[0066] - the aircraft portion is such that the support of each control device comprises a tubular wall delimiting a fluid circulation passage between the corresponding sections of the corresponding pipe(s),

[0067] the tubular wall of the support of each control device comprising an insertion slot,

[0068] the shutter element of each control device comprising an interruption plate intended to be inserted into said fluid circulation passage through said insertion slot so as to interrupt the fluid communication between the corresponding sections of the corresponding conduit(s) when the shutter element is mounted on said support;

[0069] - the aircraft portion is such that the covering element of each device of control comprises a cover intended to close the insertion slot when the covering element is mounted on said support;

[0070] - the aircraft portion is such that each control device comprises a seal sealing element arranged around the corresponding insertion slot, the shutter element, respectively the covering element, cooperating with the corresponding seal when the shutter element, respectively the covering element, is mounted on the support, so as to prevent the passage of fluid through the slot of insertion;

[0071] - the aircraft portion is such that the shutter element and the covering element of each control device are each capable of being mounted on said support by screwing;

[0072] - the aircraft portion is such that the shutter element, respectively the element of covering, of each control device comprises an internal surface oriented towards the support when said shutter element, respectively said covering element, is mounted on said support, and an external surface opposite the internal surface,

[0073] the outer surface of said shutter element comprising a closed configuration indicator and the outer surface of said covering element comprising an open configuration indicator different from the closed configuration indicator;

[0074] The invention further relates to a method for fitting out at least one portion of an aircraft as described above, comprising the following steps:

[0075] a) mounting the first partition wall at the first longitudinal coordinate and configuring the at least one first control device of the at least one first fluid circuit in the open configuration; or

[0076] b) mounting the first partition wall at the second longitudinal coordinate and configuring the at least one first control device of the at least one first fluid circuit in the closed configuration.

[0077] According to other advantageous aspects of the invention, the method comprises one or more of the following characteristics, taken in isolation or in all technically possible combinations:

[0078] - during step b), at least one second device for controlling the at least one first fluid circuit is configured in an open configuration so that the second section of the at least one first pipe is in fluid communication with a third section of the at least one first pipe, the third section comprising at least one third outlet capable of delivering the first fluid into the cabin behind a third longitudinal coordinate relative to the orientation direction, the second section of the at least one first pipe being intended to be fluidically connected to the at least one first source by the third section of the at least one first pipe, the third longitudinal coordinate being behind the second longitudinal coordinate relative to the orientation direction,

[0079] the method further comprising as an alternative to steps a) and b), the following step:

[0080] c) mounting the first partition wall at the third longitudinal coordinate tudinal and configuration of the at least one second device for controlling the at least one first fluidic circuit in a closed configuration in which the com fluid communication between the second section of the at least one first pipe and the third section of the at least one first pipe is interrupted;

[0081] - the method further comprises the following step:

[0082] d) mounting a second partition wall at a fourth longitudinal coordinate such that the second partition wall extends substantially perpendicular to the longitudinal axis and separates a third cabin portion and the second cabin portion, the fourth longitudinal coordinate being located behind the third longitudinal coordinate relative to the orientation direction, and

[0083] configuration of at least one device for controlling at least one second fluid circuit in an open configuration in which a first section of at least one second pipe of the at least one second fluid circuit is in fluid communication with a second section of the at least one second pipe, the first section of the at least one second pipe comprising at least one first outlet capable of delivering a second fluid into the cabin between the fourth longitudinal coordinate and a fifth longitudinal coordinate located behind the fourth longitudinal coordinate relative to the orientation direction, the second section of the at least one second pipe comprising at least one second outlet capable of delivering the second fluid into the cabin behind the fifth longitudinal coordinate relative to the orientation direction,the first section of the at least one second pipe being intended to be fluidically connected to at least one second source of the second fluid by the second section of the at least one second pipe;

[0084] - the method further comprises, as an alternative to step d), the following step:

[0085] e) mounting the second partition wall at the fifth longitudinal coordinate such that the second partition wall extends substantially perpendicular to the longitudinal axis and separates the third cabin portion and the second cabin portion, and

[0086] configuration of the at least one control device of the at least one second fluid circuit in a closed configuration in which the fluid communication between the first section of the at least one second pipe and the second section of the at least one second pipe is interrupted;

[0087] - during step d), at least one intermediate control device of the at least one second fluid circuit is configured in a closed configuration such that the fluid communication between the first section of the at least one second pipe and the third section of the at least one first pipe is interrupted, the third section of the at least one first pipe being intended to be fluidically connected to the at least one first source; and

[0088] - during step e), the at least one intermediate control device of the at least a second fluid circuit is configured in an open configuration such that the first section of the at least one second conduit is in fluid communication with the third section of the at least one first conduit;

[0089] - after step a), at least one intermediate control device of the at least one first fluid circuit is configured in a closed configuration so that the fluid communication between the first section of the at least one first pipe and a section of at least one auxiliary pipe of at least one auxiliary fluid circuit is interrupted, the at least one auxiliary fluid circuit being intended to fluidically connect at least one third source of a third fluid and the first cabin portion, the at least one auxiliary fluid circuit comprising at least one auxiliary pipe comprising a section comprising at least one outlet capable of delivering the third fluid into the cabin in front of the first longitudinal coordinate relative to the orientation direction, the section of the at least one auxiliary pipe being intended to be fluidically connected to the at least one third source,the first section of the at least one first pipe being intended to be fluidically connected to the section of the at least one auxiliary pipe;

[0090] - after step b), the at least one intermediate control device of the at least one first fluid circuit is configured in an open configuration such that the first section of the at least one first conduit is in fluid communication with the section of the at least one auxiliary conduit;

[0091] - after step c), the at least one intermediate control device of the at least one first fluid circuit is configured in an open configuration such that the first section of the at least one first conduit is in fluid communication with the section of the at least one auxiliary conduit;

[0092] - the method comprises:

[0093] - for a first aircraft portion of a first aircraft, the assembly of the first partition wall at the first longitudinal coordinate and the configuration of the at least one first control device of the at least one first fluid circuit in the open configuration; and

[0094] - for a second aircraft portion of a second aircraft, the assembly of the first partition wall at the second longitudinal coordinate and the configuration of the at least one first control device of the at least one first fluid circuit in the closed configuration;

[0095] the at least one first pipe of the first fluid circuit of the first aircraft portion being identical to the at least one first pipe of the first fluid circuit of the second aircraft portion.

[0096] The invention will appear more clearly on reading the description which follows, given solely by way of non-limiting example, and made with reference to the drawings in which:

[0097] [Fig.l] [Fig.l] is a simplified schematic representation of the lower part of an aircraft portion according to the invention, in which a first separating wall is mounted on the fuselage at a first longitudinal coordinate, a second separating wall is mounted on the fuselage at a fourth longitudinal coordinate, a first device for controlling two first fluid circuits being in the open configuration, a second device for controlling the two first fluid circuits being in the open configuration, an intermediate device for controlling the two first fluid circuits being in the closed configuration, a first device for controlling two second fluid circuits being in the open configuration, an intermediate device for controlling the two second fluid circuits being in the closed configuration;

[0098] [Fig.2] [Fig.2] is a simplified schematic representation of the portion aircraft of [Fig.l], wherein the first partition wall is mounted on the fuselage at a second longitudinal coordinate, the second partition wall is mounted on the fuselage at the fourth longitudinal coordinate, the first control device of the first two fluid circuits being in the closed configuration, the second control device of the first two fluid circuits being in the open configuration, the intermediate control device of the first two fluid circuits being in the open configuration, the first control device of the second two fluid circuits being in the open configuration, the intermediate control device of the second two fluid circuits being in the closed configuration;

[0099] [Fig.3] [Fig.3] is a simplified schematic representation of the portion aircraft of [Fig.l], wherein the first partition wall is mounted on the fuselage at a third longitudinal coordinate, the second partition wall is mounted on the fuselage at a fifth longitudinal coordinate, the first control device of the first two fluid circuits being in the open configuration, the second control device of the first two fluid circuits being in the closed configuration, the intermediate control device of the first two fluid circuits being in the open configuration, the first control device of the second two fluid circuits being in the closed configuration, the intermediate control device of the second two fluid circuits being in the open configuration;

[0100] [Fig.4] [Fig.4] is a schematic representation of a perspective view of two sections of fluid circuit conduit and a device for controlling the aircraft portion of [Fig.l], in particular a support and a shutter element of the control device, the shutter element being illustrated at a distance from the support, the corresponding conduit(s) extending along the same conduit axis;

[0101] [Fig.5] [Fig.5] is a schematic representation of a sectional view of the two fluid circuit pipe sections and the control device of [Fig.4] along a sectional plane parallel to the corresponding pipe axis, the shutter element being shown mounted on the support so as to interrupt the fluid communication between the corresponding pipe sections;

[0102] [Fig.6] [Fig.6] is a schematic representation of a perspective view of two sections of fluid circuit pipe and a control device of the aircraft portion of [Fig.l], in particular of a support and a covering element of the control device, the covering element being illustrated at a distance from the support, the corresponding pipe(s) extending along the same pipe axis;

[0103] [Fig.7] [Fig.7] is a schematic representation of a sectional view of the two fluid circuit pipe sections and the control device of [Fig.6] along a sectional plane parallel to the corresponding pipe axis, the covering element being shown mounted on the support so as to allow fluid communication between the corresponding pipe sections;

[0104] [Fig.8] [Fig.8] is a schematic representation of a method of fitting out a portion of an aircraft, according to the invention.

[0105] With reference to Figures 1 to 7, a portion of aircraft 10 according to the invention is described.

[0106] The aircraft portion 10 comprises a fuselage 14, a first separation wall 20A and at least one first fluid circuit 30.

[0107] Advantageously, the aircraft portion 10 further comprises at least one first source 28 of a first fluid.

[0108] Still advantageously, the aircraft portion 10 further comprises a second separation wall 20B and at least one second fluid circuit 60.

[0109] Still advantageously, the aircraft portion 10 further comprises at least one second source 58 of a second fluid.

[0110] As illustrated in the examples of Figures 1 to 3, the aircraft portion 10 further comprises at least one third source 118 of a third fluid and at least one auxiliary fluid circuit 120.

[0111] In the following, except when explicitly mentioned otherwise, a single first fluid circuit 30 and where appropriate a single first fluid source 28, a single second fluid circuit 60, a single second fluid source 58, a single third fluid source 118 and a single auxiliary fluid circuit 120 are described. Of course, the invention also relates to an aircraft portion 10 comprising a plurality of first fluid circuits 30, where appropriate a plurality of first fluid sources fluid 28, a plurality of second fluid circuits 60, a plurality of second fluid sources 58, a plurality of third fluid sources 118 and / or a plurality of auxiliary fluid circuits 120 (as illustrated in the examples of Figures 1 to 3).

[0112] With reference to Figures 1 to 3, the fuselage 14 delimits a cabin 16 extending along a longitudinal axis X.

[0113] A direction D of orientation from front to rear is defined substantially parallel to the longitudinal axis X. The terms “front” and “rear” are defined relative to the direction of orientation D (the direction of orientation D points “rear”). The direction of orientation D is directed from a first longitudinal end of the fuselage 14 to a second opposite longitudinal end of the fuselage 14.

[0114] In the example of Figures 1 to 3, the orientation direction D is directed from one end of the aircraft portion 10 oriented towards the nose of the aircraft to one end of the aircraft portion 10 oriented towards the tail of the aircraft. Of course, the invention also applies in the case where the orientation direction D is directed from one end of the aircraft portion 10 oriented towards the tail of the aircraft to one end of the aircraft portion 10 oriented towards the nose of the aircraft.

[0115] With reference to Figures 1 to 3, the fuselage 14 has a median longitudinal plane M extending along the longitudinal axis X and a vertical axis Z oriented from bottom to top, said median longitudinal plane M forming in particular a plane of symmetry of the fuselage 14. The median longitudinal plane M also forms a median longitudinal plane of the aircraft portion 10, which is advantageously substantially symmetrical with respect to this plane M. The fuselage 14 separates a left part and a right part of the aircraft portion 10.

[0116] The fuselage 14 further has a transverse plane T extending along the longitudinal axis X and a transverse axis Y oriented from left to right of the aircraft portion 10. The transverse plane T separates a lower part and an upper part of the aircraft portion 10.

[0117] For example, the aircraft portion 10 comprises a first assembly 26A comprising a first fluid circuit 30 and where appropriate a first fluid source 28, a second fluid circuit 60, a second fluid source 58, a third fluid source 118, an auxiliary fluid circuit 120, in the lower right part of the aircraft portion 10.

[0118] Advantageously, the aircraft portion 10 further comprises a second assembly 26B comprising a first fluid circuit 30 and where appropriate a first fluid source 28, a second fluid circuit 60, a second fluid source 58, a third fluid source 118, an auxiliary fluid circuit 120, in the part in lower left of the aircraft portion 10, for example arranged substantially symmetrically to the first assembly 26A relative to the median longitudinal plane M.

[0119] Still advantageously, the aircraft portion 10 further comprises a third assembly (not illustrated) comprising a first fluid circuit and where appropriate a first fluid source, a second fluid circuit, a second fluid source, a third fluid source, an auxiliary fluid circuit, in the upper right part of the aircraft portion 10, for example arranged in a substantially symmetrical manner to the first assembly 26A relative to the transverse plane T.

[0120] Still advantageously, the aircraft portion 10 further comprises a fourth assembly (not illustrated) comprising a first fluid circuit and where appropriate a first fluid source, a second fluid circuit, a second fluid source, a third fluid source, an auxiliary fluid circuit, in the upper left part of the aircraft portion 10, for example arranged in a substantially symmetrical manner to the second assembly 26B relative to the transverse plane T.

[0121] According to a particular example, the first assembly 26A and the second assembly 26B comprise a second fluid circuit 60 and a second fluid source 58 and the third assembly and the fourth assembly are devoid of a second fluid circuit 60 and a second fluid source 58.

[0122] The cabin 16 comprises a first cabin portion 16A and a second cabin portion 16B.

[0123] Advantageously, the cabin 16 further comprises a third cabin portion 16C.

[0124] Advantageously, as illustrated in Figures 1 to 3, the third cabin portion 16C is at the rear of the second cabin portion 16B which itself is at the rear of the first cabin portion 16A, relative to the orientation direction D.

[0125] The first separation wall 20A is capable of being mounted on the fuselage 14 at a first longitudinal coordinate PI or at a second longitudinal coordinate P2, along the longitudinal axis X.

[0126] Advantageously, the first separation wall 20A is further capable of being mounted on the fuselage 14 at a third longitudinal coordinate P3, along the longitudinal axis X.

[0127] As illustrated in Figures 1 to 3, the second longitudinal coordinate P2 is behind the first longitudinal coordinate PI, relative to the orientation direction D, and the third longitudinal coordinate P3 is behind the second longitudinal coordinate P2, relative to the orientation direction D.

[0128] The first separation wall 20A is intended to extend substantially perpendicular to the longitudinal axis X and to separate the first cabin portion 16A and the second cabin portion 16B, in particular when the first partition wall 20A is mounted on the fuselage 14.

[0129] The second partition wall 20B is capable of being mounted on the fuselage 14 at a fourth longitudinal coordinate P4 or at a fifth longitudinal coordinate P5, along the longitudinal axis X.

[0130] As illustrated in Figures 1 to 3, the fourth longitudinal coordinate P4 is behind the third longitudinal coordinate P3, relative to the orientation direction D, and the fifth longitudinal coordinate P5 is behind the fourth longitudinal coordinate P4, relative to the orientation direction D.

[0131] The second separation wall 20B is intended to extend substantially perpendicular to the longitudinal axis X and to separate the third cabin portion 16C and the second cabin portion 16B, in particular when the second separation wall 20B is mounted on the fuselage 14.

[0132] Advantageously, the first fluid source 28 is configured to supply the first fluid, in particular air, to the first fluid circuit 30. In particular, the first fluid supplied by the first fluid source 28 has a first set of characteristics. The first set of characteristics includes in particular a first temperature, a first pressure, etc.

[0133] As illustrated in the example of FIGS. 1 to 3, the first source of fluid 28 is arranged behind the second cabin portion 16B, in particular behind the third cabin portion 16C, relative to the orientation direction D.

[0134] The first fluid circuit 30 is intended to fluidically connect the first fluid source 28 and the second cabin portion 16B.

[0135] The first fluid circuit 30 comprises at least one first pipe 32 and at least one first control device 44A.

[0136] Advantageously, the first fluid circuit 30 further comprises at least one second control device 44B.

[0137] Still advantageously, the first fluid circuit 30 further comprises at least one intermediate control device 44C.

[0138] In the following, an aircraft portion 10 is described in which the first fluid circuit 30 comprises a single pipe 32, a single first control device 44A, where appropriate a single second control device 44B and a single intermediate control device 44C. Of course, the invention also relates to an aircraft portion 10 in which the first fluid circuit 30 comprises a plurality of pipes 32, a plurality of first control devices 44A, where appropriate a plurality of second control devices 44B and / or a plurality of intermediate control devices 44C.

[0139] The first conduit 32 comprises a first section 34A and a second section 34B.

[0140] Advantageously, the first pipe 32 further comprises a third section 34C.

[0141] As illustrated in the example of Figures 1 to 3, the first pipe 32 extends at least in part along a first pipe axis A-A', substantially parallel to the longitudinal axis X. In particular, the first section 34A, the second section 34B and / or where appropriate the third section 34C each extend at least in part along the first pipe axis A-A'.

[0142] The first section 34A is fluidically connected to the first fluid source 28 by the second section 34B, in particular by the second section 34B and the third section 34C.

[0143] Advantageously, as illustrated in FIGS. 1 to 3, the first section 34A is further fluidically connected to the third fluid source 118 by a section 124 of at least one auxiliary pipe 122 of the auxiliary fluid circuit 120.

[0144] The first section 34A comprises at least one first outlet 36A, in particular a plurality of first outlets 36A, capable of delivering the fluid, in particular the first fluid supplied by the first fluid source 28, into the cabin 16 between the first longitudinal coordinate PI and the second longitudinal coordinate P2.

[0145] Advantageously, the at least one first outlet 36A is further capable of delivering the fluid, in particular the third fluid supplied by the third fluid source 118, into the cabin 16 between the first longitudinal coordinate PI and the second longitudinal coordinate P2.

[0146] For example, the second section 34B is fluidically connected to the first fluid source 28 by the third section 34C.

[0147] Still advantageously, the second section 34B is fluidically connected to the third fluid source 118 by the first section 34A, in particular by the first section 34A and by the section 124 of the auxiliary fluid circuit 120.

[0148] The second section 34B comprises at least one second outlet 36B, in particular a plurality of second outlets 36B, capable of delivering the fluid, in particular the first fluid supplied by the first fluid source 28, into the cabin 16 behind the second longitudinal coordinate P2, advantageously between the second longitudinal coordinate P2 and the third longitudinal coordinate P3.

[0149] Advantageously, the at least one second outlet 36B is capable of delivering the fluid, in particular the third fluid supplied by the third fluid source 118, into the cabin 16 behind the second longitudinal coordinate P2 relative to the orientation direction D, advantageously between the second longitudinal coordinate P2 and the third longitudinal coordinate P3.

[0150] The third section 34C is fluidically connected to the first source of fluid 28.

[0151] The third section 34C comprises at least one third outlet 36C, in particular a plurality of third outlets 36C, capable of delivering the fluid, in particular the fluid supplied by the first fluid source 28, into the cabin 16 behind the third longitudinal coordinate P3, advantageously between the third longitudinal coordinate P3 and the fourth longitudinal coordinate P4.

[0152] Advantageously, the first control device 44A fluidly connects the first section 34A and the second section 34B.

[0153] The first control device 44A is configurable between an open configuration, in which the first section 34A is in fluid communication with the second section 34B, and a closed configuration in which the fluid communication between the first section 34A and the second section 34B is interrupted.

[0154] The first control device 44A is intended to be in the open configuration when the first partition wall 20A is mounted at the first longitudinal coordinate PI ([Fig.l]) or at the third longitudinal coordinate P3 ([Fig.3]).

[0155] The first control device 44A is intended to be in the closed configuration when the first partition wall 20A is mounted at the second longitudinal coordinate P2 ([Fig.2]).

[0156] Advantageously, the second control device 44B fluidly connects the second section 34B and the third section 34C.

[0157] In particular, the second control device 44B is configurable between an open configuration, in which the second section 34B is in fluid communication with the third section 34C, and a closed configuration, in which the fluid communication between the second section 34B and the third section 34C is interrupted.

[0158] Advantageously, the second control device 44B is intended to be in the open configuration when the first separation wall 20A is mounted at the first longitudinal coordinate ([Fig.l]) or at the second longitudinal coordinate P2 ([Fig.2]).

[0159] Still advantageously, the second control device 44B is intended to be in the closed configuration when the first separation wall 20A is mounted at the third longitudinal coordinate P3 ([Fig.3]).

[0160] Advantageously, the intermediate control device 44C of the first fluid circuit 30 fluidically connects the first section 34A of the first pipe 32 and the section 124 of the auxiliary fluid circuit 120.

[0161] In particular, the intermediate control device 44C is configurable between an open configuration, in which the first section 34A of the first conduit 32 is in fluid communication with the section 124 of the auxiliary fluid circuit 120, and a closed configuration, in which the fluid communication between the first section 34A of the first conduit 32 and the section 124 of the auxiliary fluid circuit 120 is interrupted.

[0162] Advantageously, the intermediate control device 44C is intended to be in the open configuration when the first separation wall 20A is mounted at the second longitudinal coordinate ([Fig.2]) or at the third longitudinal coordinate P3 ([Fig.3]).

[0163] Still advantageously, the intermediate control device 44C is intended to be in the closed configuration when the first separation wall 20A is mounted at the first longitudinal coordinate PI ([Fig.l]).

[0164] When the first control device 44A and the second control device 44B are in the open configuration and the intermediate control device 44C is in the closed configuration ([Fig.l]), the first fluid source 28 supplies the first, second and third outlets 36A, 36B, 36C.

[0165] When the first control device 44A is in the closed configuration, the second control device 44B is in the open configuration and the intermediate control device 44C is in the open configuration ([Fig.2]), the first fluid source 28 supplies the second and third outlets 36B, 36C and the third fluid source 118 supplies the first outlet 36A (the first outlet 36A is then not supplied with fluid by the first fluid source 28).

[0166] When the first control device 44A is in the open configuration, the second control device 44B is in the closed configuration and the intermediate control device is in the open configuration ([Fig.3]), the first fluid source 28 supplies the third outlet 36C and the third fluid source 118 supplies the first and second outlets 36A, 36B (the first and second outlets 36A, 36B are then not supplied with fluid by the first fluid source 28).

[0167] Advantageously, the second fluid source 58 is configured to supply the second fluid, in particular air, to the second fluid circuit 60. In particular, the second fluid supplied by the second fluid source 58 has a second set of characteristics. The second set of characteristics includes in particular a second temperature, a second pressure, etc. For example, at least one characteristic of the second set of characteristics is different from the corresponding characteristic of the first set of characteristics of the first fluid.

[0168] As illustrated in the example of Figures 1 to 3, the second fluid source 58 is arranged behind the second cabin portion 16B, in particular behind the third cabin portion 16C.

[0169] The second fluid circuit 60 is intended to fluidly connect the second fluid source 58 and the third cabin portion 16C.

[0170] The second fluid circuit 60 comprises at least one second pipe 62 and at least one control device 74A.

[0171] Advantageously, the second fluid circuit 60 further comprises at least one intermediate control device 74B.

[0172] In the following, an aircraft portion 10 is described in which the second fluid circuit 60 comprises a single second pipe 62, a single control device 74A and, where appropriate, a single intermediate control device 74B. Of course, the invention also relates to an aircraft portion 10 in which the second fluid circuit 60 comprises a plurality of second pipes 62, a plurality of control devices 74A and / or, where appropriate, a plurality of intermediate control devices 74B.

[0173] Advantageously, the second pipe 62 comprises a first section 64A and a second section 64B.

[0174] As illustrated in the example of Figures 1 to 3, the second pipe 62 extends at least in part along a second pipe axis B-B', substantially parallel to the longitudinal axis X. In particular, the first section 64A and / or the second section 64B extend at least in part along the second pipe axis B-B'.

[0175] The first section 64A of the second conduit 62 is fluidically connected to the second fluid source 58 by the second section 64B.

[0176] Advantageously, the first section 64A of the second pipe 62 is fluidically connected to the first pipe 32 of the first fluid circuit 30, in particular to the third section 34C of the first pipe 32 of the first fluid circuit 30.

[0177] Still advantageously, the first section 64A is fluidically connected to the first fluid source 28, in particular by the first pipe 32 of the first fluid circuit 30, in particular by the third section 34C of the first pipe 32 of the first fluid circuit 30.

[0178] The first section 64A comprises at least one first outlet 66A, in particular a plurality of first outlets 66A, capable of delivering the fluid, in particular the second fluid supplied by the second fluid source 58, into the cabin 16 between the fourth longitudinal coordinate P4 and the fifth longitudinal coordinate P5.

[0179] Advantageously, the at least one first outlet 66A is further capable of delivering the first fluid supplied by the first fluid source 28, into the cabin 16 between the fourth longitudinal coordinate P4 and the fifth longitudinal coordinate P5.

[0180] Advantageously, the second section 64B is fluidically connected to the second fluid source 58. In particular, the second section 64B is in fluid communication with the second fluid source 58.

[0181] The second section 64B comprises at least one second outlet 66B, in particular a plurality of second outlets 66B, capable of delivering the fluid, in particular the second fluid supplied by the second fluid source 58, into the cabin 16 behind the fifth longitudinal coordinate P5.

[0182] Advantageously, the control device 74A of the second fluid circuit 60 fluidly connects the first section 64A and the second section 64B.

[0183] The control device 74A of the second fluid circuit 60 is configurable between an open configuration, in which the first section 64A is in fluid communication with the second section 64B, and a closed configuration in which the fluid communication between the first section 64A and the second section 64B is interrupted.

[0184] The control device 74A of the second fluid circuit 60 is intended to be in the open configuration when the second separation wall 20B is mounted at the fourth longitudinal coordinate P4 (figures 1 and 2).

[0185] The control device 74B of the second fluid circuit 60 is intended to be in the closed configuration when the second separation wall 20B is mounted at the fifth longitudinal coordinate P5 ([Fig.3]).

[0186] Advantageously, the intermediate control device 74B of the second fluid circuit 60 fluidly connects the first pipe 32 and the second pipe 62, in particular the third section 34C of the first pipe 32 and the first section 64A of the second pipe 62.

[0187] In particular, the intermediate control device 74B of the second fluid circuit 60 is configurable between an open configuration, in which the first conduit 32, in particular the third section 34C of the first conduit 32, is in fluid communication with the second conduit 62, in particular the first section 64A of the second conduit 62, and a closed configuration, in which the fluid communication between the first conduit 32, in particular the third section 34C of the first conduit 32, and the second conduit 62, in particular the first section 64A of the second conduit 62, is interrupted.

[0188] Advantageously, the intermediate control device 74B is intended to be in the closed configuration when the second separation wall 20B is mounted at the fourth longitudinal coordinate P4 (figures 1 and 2).

[0189] Still advantageously, the intermediate control device 74B is intended to be in the open configuration when the second separation wall 20B is mounted at the fifth longitudinal coordinate P5 ([Fig.3]).

[0190] When the control device 74A of the second fluid circuit 60 is in the open configuration and the intermediate control device 74B of the second fluid circuit 60 is in the closed configuration (figures 1 and 2), the second source of fluid 58 feeds the first and second outputs 66A, 66B.

[0191] When the control device 74A of the second fluid circuit 60 is in the closed configuration and the intermediate control device 74B of the second fluid circuit 60 is in the open configuration ([Fig.3]), the first fluid source 28 supplies the first outlet 66A and the second fluid source 58 supplies the second outlet 66B.

[0192] According to the example illustrated in Figures 1 to 3, the third fluid source 118 is configured to supply the third fluid, in particular air, to the auxiliary fluid circuit 120. In particular, the fluid supplied by the third fluid source 118 has a third set of characteristics. The third set of characteristics includes in particular a third temperature, a third pressure, etc. For example, at least one characteristic of the third set of characteristics is different from the corresponding characteristic of the first set of characteristics of the first fluid or the corresponding characteristic of the second set of characteristics of the second fluid.

[0193] As illustrated in the example of Figures 1 to 3, the third fluid source 118 is arranged in front of the first cabin portion 16A.

[0194] The auxiliary fluid circuit 120 is intended to fluidically connect the third fluid source 118 and the first cabin portion 16A.

[0195] The auxiliary fluid circuit 120 comprises at least one auxiliary pipe 122. In the following, an aircraft portion 10 is described in which the auxiliary fluid circuit 120 comprises a single auxiliary pipe 122. Of course, the invention also relates to an aircraft portion 10 in which the auxiliary fluid circuit 120 comprises a plurality of auxiliary pipes 122.

[0196] The auxiliary conduit 122 comprises a conduit section 124.

[0197] As illustrated in the example of Figures 1 to 3, the auxiliary pipe 122 extends at least in part along a third pipe axis C-C', substantially parallel to the longitudinal axis X. In particular, the section 124 extends at least in part along the third pipe axis C-C'.

[0198] Section 124 is fluidically connected to third fluid source 118.

[0199] The section 124 comprises for example at least one outlet 126, in particular a plurality of outlets 126, capable of delivering the fluid, in particular the third fluid supplied by the third fluid source 118, into the cabin 16 in front of the first longitudinal coordinate PI relative to the orientation direction D.

[0200] In the following, with reference to FIGS. 4 to 7, each control device 44 (44A, 44B, 44C), 74 (74A, 74B) is described in more detail.

[0201] In particular, a single control device 44, 74 is described. The description of course applies to each control device 44, 74, except when it is otherwise specified.

[0202] The control device 44, 74 comprises a support 80 and a control assembly 90.

[0203] Advantageously, the control device 44, 74 further comprises a seal 110.

[0204] As will be detailed below, the control device 44, 74 is:

[0205] - in closed configuration when a shutter element 92 of the assembly of control 90 is mounted on the support 80; and

[0206] - in open configuration when a covering element 102 of the assembly of control 90 is mounted on support 80.

[0207] With reference to Figures 4 to 7, the support 80 is permanently mounted on the corresponding sections 34A, 34B, 34C, 64A, 64B, 124 of the corresponding pipe(s) 32, 62, 122 so as to fluidically connect the corresponding sections 34A, 34B, 34C, 64A, 64B, 124 of the corresponding pipe(s) 32, 62.

[0208] By way of example, the support 80 of the first control device 44A is permanently mounted on the sections 34A and 34B of the first pipe 32 so as to fluidly connect the sections 34A and 34B of the first pipe 32.

[0209] Advantageously, the support 80 of the intermediate control device 74B is permanently mounted on the third section 34C of the first pipe 32 and on the first section 64A of the second pipe 62 so as to fluidly connect the third section 34C of the first pipe 32 and the first section 64A of the second pipe 62.

[0210] With reference to figures 4 to 7, the support 80 comprises a tubular wall 82 delimiting a passage 84 for circulation of the fluid between the corresponding sections 34A, 34B, 34C, 64A, 64B, 124 of the corresponding pipe(s) 32, 62, 122.

[0211] The tubular wall 82 comprises an insertion slot 86. The insertion slot 86 advantageously communicates with the fluid circulation passage 84.

[0212] The control assembly 90 comprises the shutter element 92 and the covering element 102.

[0213] With reference to figures 4 and 5, the shutter element 92 is capable of being removably mounted on the support 80, in particular by screwing, so as to interrupt the fluid communication between the corresponding sections 34A, 34B, 34C, 64A, 64B, 124 of the corresponding pipe(s) 32, 62, 122.

[0214] In particular, the shutter element 92 comprises an interruption plate 94 intended to be inserted into the corresponding fluid circulation passage 84 through the corresponding insertion slot 86, in particular when the shutter element is mounted on the support 80, so as to interrupt the fluid communication between the corresponding sections 34A, 34B, 34C, 64A, 64B, 124 of the pipe 32, 62, 122 corresponding.

[0215] Furthermore, advantageously, the shutter element 92 comprises a base 93 on which the interruption plate 94 is mounted. As illustrated in the example of FIGS. 4 and 5, when the shutter element 92 is mounted on the support 80, the interruption plate 94 extends into the fluid circulation passage 84 and the base 93 is screwed to the support 80 so as to hold the interruption plate 94 in the passage 84.

[0216] Advantageously, the base 93 and the interruption plate 94 are made in one piece.

[0217] Advantageously, the shutter element 92 comprises an internal surface 95 oriented towards the support 80 when the shutter element 92 is mounted on the support 80, and an external surface 96 opposite the internal surface 95. In particular, the internal surface 95 of the shutter element 92 is formed by an internal surface of the base 93, oriented towards the support 80 when the shutter element is mounted on the support 80, and by a surface of the interruption plate 94. The external surface 96 of the shutter element 92 is formed by an external surface of the base 93 opposite the internal surface of the base 93.

[0218] Advantageously, as illustrated in [Fig. 4], the external surface 96 of the shutter element 92 comprises a closed configuration indicator 98. For example, the closed configuration indicator 98 is a ballot cross. The closed configuration indicator 98 allows an operator to easily recognize that a control device 44, 74 is in the closed configuration, when he sees the closed configuration indicator 98 on the external surface 96 of the shutter element 92 mounted on said control device 44, 74.

[0219] With reference to figures 6 and 7, the covering element 102 is capable of being removably mounted on the support 80, in particular by screwing, replacing the shutter element 92, so as to allow fluid communication between the corresponding sections 34A, 34B, 34C, 64A, 64B, 124 of the corresponding pipe(s) 32, 62, 122.

[0220] In particular, the covering element 102 comprises a cover 104 intended to close the insertion slot 86, in particular when the covering element 102 is mounted on the support 80.

[0221] Furthermore, for example, the covering element 102 comprises a base 103 on which the cover 104 is mounted. As illustrated in the example of FIGS. 6 and 7, when the shutter element 102 is mounted on the support 80, the cover 104 covers, and in particular closes, the insertion slot 86 and the base 103 is screwed to the support 80 so as to hold the cover 104 on the insertion slot 86.

[0222] Advantageously, the base 103 and the cover 104 are made in one piece.

[0223] Still advantageously, as illustrated in the example of [Fig.7], the base 103 and the cover 104 form a single piece.

[0224] Still advantageously, the covering element 102 comprises an internal surface 105 oriented towards the support 80 when the covering element 102 is mounted on the support 80, and an external surface 106 opposite the internal surface 105. In particular, the internal surface 105 of the covering element 102 is formed by an internal surface of the base 103 and / or of the cover 104, oriented towards the support 80 when the covering element 102 is mounted on the support 80, and by a surface of the interruption plate 94. The external surface 106 of the covering element 102 is formed by an external surface of the base 93 opposite the internal surface of the base 93.

[0225] Advantageously, as illustrated in [Fig. 6], the external surface 106 of the covering element 102 comprises an open configuration indicator 108. For example, the open configuration indicator 108 is a check mark. The open configuration indicator 108 allows an operator to easily recognize that a control device 44, 74 is in the open configuration, when he sees the open configuration indicator 108 on the external surface 106 of the covering element 102 mounted on said control device 44, 74.

[0226] With reference to Figures 4 to 7, the seal 110 is arranged on the support 80, around the corresponding insertion slot 86, so that the shutter element 92, respectively the covering element 102, cooperates with the corresponding seal 110 when the shutter element 92, respectively the covering element 102, is mounted on the support 80, so as to prevent the passage of fluid through the insertion slot 86.

[0227] With reference to [Fig.8], a method 200 is described for fitting out at least one portion of an aircraft 10 as described above.

[0228] The method 200 advantageously comprises the provision 210 of the aircraft portion 10.

[0229] The method 200 further comprises, for example, a step 220A of mounting the first separation wall 20A at the first longitudinal coordinate PL.

[0230] During step 220A, the first control device 44A of the first fluid circuit 30 is configured in the open configuration.

[0231] Advantageously, during step 220A, the second control device 44B of the first fluid circuit 30 is also configured in the open configuration.

[0232] Also advantageously, during step 220A, the intermediate control device 44C of the first fluid circuit 30 is configured in the closed configuration.

[0233] As an alternative to step 220A, the method 100 comprises a step 220B of mounting the first partition wall 20A at the second longitudinal coordinate P2.

[0234] During step 220B, the first control device 44A of the first circuit fluidic 30 is configured in the closed configuration.

[0235] Advantageously, during step 220B, the second control device 44B of the first fluid circuit 30 is configured in the open configuration.

[0236] Still advantageously, during step 220B, the intermediate control device 44C of the first fluid circuit 30 is configured in the open configuration.

[0237] For example, as an alternative to step 220A and step 220B, the method 200 comprises a step 220C of mounting the first partition wall 20A at the third longitudinal coordinate P3.

[0238] During step 220C, the second control device 44B of the first fluid circuit 30 is configured in the closed configuration.

[0239] For example, during step 220C, the first control device 44A of the first fluid circuit 30 is configured in the open configuration.

[0240] In particular, during step 220C, the intermediate control device 44C of the first fluid circuit 30 is configured in the open configuration.

[0241] For example, and in particular after step 220A, 220B or where appropriate 220C, the method 200 further comprises a step 230A of mounting the second separation wall 20B at the fourth longitudinal coordinate P4.

[0242] During step 230A, the control device 74A of the second fluid circuit 60 is configured in the open configuration.

[0243] Advantageously, during step 230A, the intermediate control device 74B of the second fluid circuit 60 is configured in the closed configuration.

[0244] As an alternative to step 230A, the method 200 comprises a step 230B of mounting the second partition wall 20B at the fifth longitudinal coordinate P5.

[0245] During step 230B, the control device 74A of the second fluid circuit 60 is configured in the closed configuration.

[0246] Advantageously, during step 230B, the intermediate control device 74B of the second fluid circuit 60 is configured in the open configuration.

[0247] According to a particular example, the method 200 comprises:

[0248] - for a first aircraft portion 10 of a first aircraft, as described above- above, the performance of step 220A; and

[0249] - for a second aircraft portion 10 of a second aircraft, as described above, the completion of step 220B.

[0250] Advantageously, the first pipe 32 of the first fluid circuit 30 of the first aircraft portion 10 is identical to the first pipe 32 of the first fluid circuit 30 of the second aircraft portion 10.

[0251] Still advantageously, the first aircraft portion 10 and the second aircraft portion 10 comprise substantially identical first PI and second P2 longitudinal coordinates.

[0252] In particular, for each of the first and second aircraft portions 10, one of the steps 220A, 220B, 220C is carried out and, where appropriate, one of the steps 230A, 230B is carried out, without it being necessary to carry out the same combinations of steps in the first and second aircraft portions 10.

[0253] Advantageously, the first aircraft portion 10 and the second aircraft portion 10 comprise third P3, fourth P4 and fifth P5 longitudinal coordinates and second ducts 62 which are substantially identical.

[0254] The method 200 thus makes it possible to provide different arrangements for several distinct aircraft during the assembly of said aircraft, depending in particular on the wishes of the users of the aircraft, in particular relating to the positioning of the first separation wall 20A and / or the second separation wall 20B along the longitudinal axis X at the different longitudinal positions P1, P2 and / or P3, and where appropriate P4 and / or P5.

Claims

1. Claims Aircraft portion (10) comprising: - a fuselage (14) delimiting a cabin (16) extending along a longitudinal axis (X), the cabin (16) comprising a first cabin portion (16A) and a second cabin portion (16B); - a first separating wall (20A) intended to extend substantially perpendicular to the longitudinal axis (X) and intended to separate the first cabin portion (16A) and the second cabin portion (16B), the first separating wall (20A) being capable of being mounted on the fuselage (14) at a first longitudinal coordinate (PI) or at a second longitudinal coordinate (P2) along the longitudinal axis (X), the second longitudinal coordinate (P2) being located behind the first longitudinal coordinate (PI) relative to an orientation direction (D) substantially parallel to the longitudinal axis (X); - at least one first fluid circuit (30) intended to fluidically connect at least one first source (28) of a first fluid and the second cabin portion (16B), the at least one first fluid circuit (30) comprising: - at least one first pipe (32) comprising: - a first section (34A) comprising at least one first outlet (36A) capable of delivering the first fluid into the cabin (16) between the first longitudinal coordinate (PI) and the second longitudinal coordinate (P2); - a second section (34B) comprising at least one second outlet (36B) capable of delivering the first fluid into the cabin (16) behind the second longitudinal coordinate (P2) relative to the orientation direction (D), the first section (34A) of the at least one first pipe (32) being intended to be fluidically connected to the at least one first source (28) by the second section (34B) of the at least one first pipe (32); - at least one first control device (44A) configurable between an open configuration, in which the first section (34A) of the at least one first pipe (32) is in fluid communication with the second section (34B) of the at least one first pipe (32), and a closed configuration, in which the fluid communication between the first section (34A) of the at least one first

2. conduit (32) and the second section (34B) of the at least one first conduit (32) is interrupted; in which: - the at least one first control device (44A) of the at least one first fluid circuit (30) is intended to be in the open configuration when the first separation wall (20A) is mounted at the first longitudinal coordinate (PI); - the at least one first control device (44A) of the at least one first fluid circuit (30) is intended to be in closed configuration when the first separation wall (20A) is mounted at the second longitudinal coordinate (P2). Aircraft portion (10) according to claim 1, wherein: - the first separating wall (20A) is capable of being mounted on the fuselage (14) furthermore at a third longitudinal coordinate (P3), the third longitudinal coordinate (P3) being located behind the second longitudinal coordinate (P2) relative to the orientation direction (D); - the at least one second outlet (36B) is capable of delivering the first fluid into the cabin (16) between the second longitudinal coordinate (P2) and the third longitudinal coordinate (P3); - the at least one first pipe (32) comprises a third section (34C) comprising at least one third outlet (36C) capable of delivering the first fluid into the cabin (16) behind the third longitudinal coordinate (P3) relative to the orientation direction (D), the second section (34B) of the at least one first pipe (32) being intended to be fluidically connected to the at least one first source (28) by the third section (34C) of the at least one first pipe (32); - the at least one first fluid circuit (30) further comprises at least one second control device (44B) configurable between an open configuration, in which the second section (34B) of the at least one first pipe (32) is in fluid communication with the third section (34C) of the at least one first pipe (32), and a closed configuration, in which the fluid communication between the second section (34B) of the at least one first pipe (32) and the third section (34C) of the at least one first pipe (32) is interrupted; in which:

3. - when the at least one first separating wall (20A) is mounted at the second longitudinal coordinate (P2) or at the first longitudinal coordinate (PI), the at least one second control device (44B) of the at least one first fluid circuit (30) is intended to be in open configuration; - when the first separating wall (20A) is mounted at the third longitudinal coordinate (P3), the at least one second control device (44B) of the at least one first fluid circuit (30) is intended to be in the closed configuration. The aircraft portion (10) of claim 2, wherein the cabin (16) comprises a third cabin portion (16C), the aircraft portion (10) further comprising: - a second separating wall (20B) intended to extend substantially perpendicular to the longitudinal axis (X) and intended to separate the third cabin portion (16C) and the second cabin portion (16B), the second separating wall (20B) being capable of being mounted on the fuselage (14) at a fourth longitudinal coordinate (P4) or at a fifth longitudinal coordinate (P5), the fourth longitudinal coordinate (P4) being located behind the third longitudinal coordinate (P3) relative to the orientation direction (D), the fifth longitudinal coordinate (P5) being located behind the fourth longitudinal coordinate (P4) relative to the orientation direction (D); - at least one second fluid circuit (60) intended to fluidically connect at least one second source (58) of a second fluid and the third cabin portion (16C), the at least one second fluid circuit (60) comprising: - at least one second pipe (62) comprising: - a first section (64A) comprising at least one first outlet (66A) capable of delivering the second fluid into the cabin (16) between the fourth longitudinal coordinate (P4) and the fifth longitudinal coordinate (P5); - a second section (64B) comprising at least one second outlet (66B) capable of delivering the second fluid into the cabin (16) behind the fifth longitudinal coordinate (P5) relative to the orientation direction (D), the first section (64A) of the at least one second pipe (62) being intended to be fluidically connected to the at least one second source (58) by the second section (64B) of the at least a second pipe (62); - at least one control device (74A) configurable between an open configuration, in which the first section (64A) of the at least one second pipe (62) is in fluid communication with the second section (64B) of the at least one second pipe (62), and a closed configuration, in which the fluid communication between the first section (64A) of the at least one second pipe (62) and the second section (64B) of the at least one second pipe (62) is interrupted; in which: - the at least one control device (74A) of the at least one second fluid circuit (60) is intended to be in the open configuration when the second separation wall (20B) is mounted at the fourth longitudinal coordinate (P4); - the at least one control device (74A) of the at least one second fluid circuit (60) is intended to be in closed configuration when the second separation wall (20B) is mounted at the fifth longitudinal coordinate (P5).

4. Aircraft portion (10) according to claim 3, wherein the third section (34C) of the at least one first pipe (32) is intended to be fluidically connected to the at least one first source (28), the first section (64A) of the at least one second pipe (62) being intended to be fluidically connected to the third section (34C) of the at least one first pipe (32), the at least one second fluid circuit (60) comprising at least one intermediate control device (74B) configurable between an open configuration, in which the first section (64A) of the at least one second pipe (62) is in fluid communication with the third section (34C) of the at least one first pipe (32), and a closed configuration, in which the fluid communication between the first section (64A) of the at least one second pipe (62) and the third section (34C) of the at least one first line (32) is interrupted,in which:, - when the second partition wall (20B) is mounted at the fourth longitudinal coordinate (P4), the at least one intermediate control device (74B) of the at least one second circuit fluidic (60) is intended to be in a closed configuration; - when the second separating wall (20B) is mounted at the fifth longitudinal coordinate (P5), the at least one intermediate control device (74B) of the at least one second fluid circuit (60) is intended to be in the open configuration.

5. Aircraft portion (10) according to any one of the preceding claims, wherein each control device (44A, 44B, 44C, 74A, 74B) comprises: - a support (80) permanently mounted on the corresponding sections (34A, 34B, 34C, 64A, 64B, 124) of the corresponding pipe(s) (32, 62, 122) so as to fluidically connect the corresponding sections (34A, 34B, 34C, 64A, 64B, 124) of the corresponding pipe(s) (32, 62, 122); and - a control assembly (90) comprising: - a shutter element (92) capable of being removably mounted on said support (80) so as to interrupt the fluid communication between the corresponding sections (34A, 34B, 34C, 64A, 64B, 124) of the corresponding pipe(s) (32, 62, 122);and - a covering element (102) capable of being removably mounted on said support (80) in replacement of the shutter element (92) so as to allow fluid communication between the corresponding sections (34A, 34B, 34C, 64A, 64B, 124) of the corresponding pipe(s) (32, 62, 122); and in which each control device (44A, 44B, 44C, 74A, 74B) is: - in the closed configuration when the shutter element (92) is mounted on said support (80); - in open configuration when the covering element (102) is mounted on said support (80).

6. Aircraft portion (10) according to claim 5, wherein the support (80) of each control device (44A, 44B, 44C, 74A, 74B) comprises a tubular wall (82) delimiting a fluid circulation passage (84) between the corresponding sections (34A, 34B, 34C, 64A, 64B, 124) of the corresponding conduit(s) (32, 62, 122), the tubular wall (82) of the support (80) of each control device (44A, 44B, 44C, 74A, 74B) comprising an insertion slot (86), the shutter element (92) of each control device (44A, 44B, 44C, 74A, 74B) comprising an interruption plate (94) for insertion into said fluid flow passage (84) through said insertion slot (86) so as to interrupt the fluid communication between the corresponding sections (34A, 34B, 34C, 64A, 64B, 124) of the corresponding conduit(s) (32, 62, 122) when the closure member (92) is mounted on said support (80).

7. Aircraft portion (10) according to claim 6, wherein the covering element (102) of each control device (44A, 44B, 44C, 74A, 74B) comprises a cover (104) intended to close the insertion slot (86) when the covering element (102) is mounted on said support (80).

8. Aircraft portion (10) according to claim 6 or 7, wherein each control device (44A, 44B, 44C, 74A, 74B) comprises a seal (110) arranged around the corresponding insertion slot (86), the shutter element (92), respectively the covering element (102), cooperating with the corresponding seal (110) when the shutter element (92), respectively the covering element (102), is mounted on the support (80), so as to prevent the passage of fluid through the insertion slot (86).

9. Aircraft portion (10) according to any one of claims 5 to 8, wherein the shutter element (92) and the covering element (102) of each control device (44A, 44B, 44C, 74A, 74B) are each capable of being mounted on said support (80) by screwing.

10. Aircraft portion (10) according to any one of claims 5 to 9, wherein the shutter element (92), respectively the covering element (102), of each control device (44A, 44B, 44C, 74A, 74B) comprises an inner surface (105) oriented towards the support (80) when said shutter element (92), respectively said covering element (102), is mounted on said support (80), and an outer surface (106) opposite the inner surface (105), the outer surface (106) of said shutter element (92) comprising a closed configuration indicator (98) and the outer surface (106) of said covering element (102) comprising an open configuration indicator (108) different from the closed configuration indicator (98).

11. Method (200) for fitting out at least one portion of an aircraft (10) according to any one of the preceding claims, comprising the following steps:

12.

13. a) mounting (220A) of the first partition wall (20A) at the first longitudinal coordinate (PI) and configuring the at least one first control device (44A) of the at least one first fluid circuit (30) in the open configuration; or b) mounting (220B) of the first partition wall (20A) at the second longitudinal coordinate (P2) and configuring the at least one first control device (44A) of the at least one first fluid circuit (30) in the closed configuration. Arrangement method (200) according to claim 11, wherein during step b) (220B), at least one second control device (44B) of the at least one first fluid circuit (30) is configured in an open configuration so that the second section (34B) of the at least one first pipe (32) is in fluid communication with a third section (34C) of the at least one first pipe (32), the third section (34C) comprising at least one third outlet (36C) capable of delivering the first fluid into the cabin (16) behind a third longitudinal coordinate (P3) relative to the orientation direction (D), the second section (34B) of the at least one first pipe (32) being intended to be fluidically connected to the at least one first source (28) by the third section (34C) of the at least one first pipe (32),the third longitudinal coordinate (P3) being behind the second longitudinal coordinate (P2) relative to the orientation direction (D), the method (200) further comprising as an alternative to steps a) (220A) and b) (220B), the following step:, c) mounting (220C) the first partition wall (20A) at the third longitudinal coordinate (P3) and configuring the at least one second control device (44B) of the at least one first fluid circuit (30) in a closed configuration in which the fluid communication between the second section (34B) of the at least one first pipe (32) and the third section (34C) of the at least one first pipe (32) is interrupted. The arrangement method (200) of claim 12, further comprising the following step: d) mounting (230A) a second partition wall (20B) at a fourth longitudinal coordinate (P4) such that the second partition wall (20B) extends substantially perpendicular to the longitudinal axis (X) and separates a third cabin portion (16C) and the

14.

15. second cabin portion (16B), the fourth longitudinal coordinate (P4) being located behind the third longitudinal coordinate (P3) relative to the orientation direction (D), and configuration of at least one control device (74A) of at least one second fluid circuit (60) in an open configuration in which a first section (64A) of at least one second pipe (62) of the at least one second fluid circuit (60) is in fluid communication with a second section (64B) of the at least one second pipe (62), the first section (64A) of the at least one second pipe (62) comprising at least one first outlet (66A) capable of delivering a second fluid into the cabin (16) between the fourth longitudinal coordinate (P4) and a fifth longitudinal coordinate (P5) located behind the fourth longitudinal coordinate (P4) relative to the orientation direction (D),the second section (64B) of the at least one second pipe (62) comprising at least one second outlet (66B) capable of delivering the second fluid into the cabin (16) behind the fifth longitudinal coordinate (P5) relative to the orientation direction (D), the first section (64A) of the at least one second pipe (62) being intended to be fluidically connected to at least one second source (58) of the second fluid by the second section (64B) of the at least one second pipe (62)., The arrangement method (200) of claim 13, further comprising as an alternative to step d) (230A), the following step: e) mounting (230B) the second partition wall (20B) at the fifth longitudinal coordinate (P5) such that the second partition wall (20B) extends substantially perpendicular to the longitudinal axis (X) and separates the third cabin portion (16C) and the second cabin portion (16B), and configuring the at least one control device (74A) of the at least one second fluid circuit (60) in a closed configuration in which the fluid communication between the first section (64A) of the at least one second pipe (62) and the second section (64B) of the at least one second pipe (62) is interrupted. Arrangement method (200) according to claim 14, wherein: - during step d) (230A), at least one intermediate control device (74B) of the at least one second fluid circuit (60) is configured in a closed configuration such that the communication fluidic between the first section (64A) of the at least one second pipe (62) and the third section (34C) of the at least one first pipe (32) is interrupted, the third section (34C) of the at least one first pipe (32) being intended to be fluidically connected to the at least one first source (28); and - during step e) (230B), the at least one intermediate control device (74B) of the at least one second fluid circuit (60) is configured in an open configuration so that the first section (64A) of the at least one second pipe (62) is in fluid communication with the third section (34C) of the at least one first pipe (32).

16. A method of arranging (200) according to any one of claims 11 to 15, comprising: - for a first aircraft portion (10) of a first aircraft, the mounting (220A) of the first separation wall (20A) at the first longitudinal coordinate (PI) and the configuration of the at least one first control device (44A) of the at least one first fluid circuit (30) in the open configuration; and - for a second aircraft portion (10) of a second aircraft, the mounting (220B) of the first separation wall (20A) at the second longitudinal coordinate (P2) and the configuration of the at least one first control device (44A) of the at least one first fluid circuit (30) in the closed configuration; the at least one first pipe (32) of the first fluid circuit (30) of the first aircraft portion (10) being identical to the at least one first pipe (32) of the first fluid circuit (30) of the second aircraft portion (10).

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