Airplane comprising a transverse frame for an avionics bay

Abstract

The subject of the invention is an aircraft comprising a transverse frame for the avionics bay (58) of the aircraft delimited by a main structure (52) and a floor, said transverse frame having a network structure with square and / or rectangular mesh cells. According to an arrangement according to the invention, the avionics bay (58) of the aircraft comprises: two longitudinal rows of avionics racks (68, 68') parallel to the longitudinal direction and arranged on each side of a free area (70); a transverse avionics rack (102) supported by the transverse frame (80) at the rear of the two longitudinal rows of avionics racks (68, 68') located at the rear boundary of the avionics bay (58). Such a transverse frame can optimize the space occupied by the avionics bay.

Description

Technical Field

[0001] This application relates to a transverse frame intended for use in an avionics bay of an aircraft, a component module, and an aircraft including said transverse frame. Background Technology

[0002] Figure 1 An aircraft 10 is depicted, including a fuselage 12 composed of several end-to-end positioned sections, extending between a nose cone 14 corresponding to the foremost section and a tail cone 16 corresponding to the rearmost section.

[0003] For the remainder of this specification, the longitudinal axis 18 of the aircraft 10 corresponds to the horizontal axis extending from the nose cone 14 to the tail cone 16 of the aircraft 10 when the aircraft 10 is on the ground. The longitudinal direction is the direction parallel to the longitudinal axis 18. The longitudinal plane is the plane parallel to the longitudinal axis 18. The lateral plane is the plane perpendicular to the longitudinal axis 18.

[0004] Like all sections, nose cone 14 includes a main structure comprising lateral stiffeners called bulkheads, longitudinal stiffeners called stringers, and skin forming the outer cladding of the aircraft. Nose cone 14 includes a floor connected to the main structure that divides the nose cone into two regions: an upper region corresponding to the cockpit and a lower region corresponding to the avionics bay. Nose cone 14 also includes a secondary structure comprising panels that separate and cover the interior of the main structure and the various equipment, accessories, and racks connected to it.

[0005] According to an assembly technique described in document FR 3051176, the floor and secondary components located above the floor of the nose cone are assembled to form a self-supporting component module, which is introduced and secured into the main structure. Simultaneously with the assembly of the main structure, the self-supporting component module is assembled and equipped with various components of the secondary structure. Therefore, the installation of the secondary structure components is performed as a parallel process, thereby contributing to an increased aircraft assembly rate. Once the self-supporting component module has been assembled, the avionics bay located below the floor is then installed.

[0006] According to the description in document FR 3000030 and in Figure 3 The configuration schematically shown in the diagram includes two rows of avionics racks 22, 22', and 26 arranged parallel to the longitudinal axis 18, on either side of a single aisle 24, and symmetrically arranged with respect to the vertical longitudinal midplane PMV. Therefore, each row includes: at least one front avionics rack containing battery cells and complementary components; and at least one rear avionics rack 26. Figure 2 As can be seen in the text.

[0007] Each rear avionics rack 26, positioned on either side of a single aisle 24, includes a support structure 28 that connects to the floor 32 at several connection points 30.1 in its upper portion and to the main structure 34 of the nose cone 14 at several connection points 30.2 in its lower portion. Each rear avionics rack 26 includes, at its rear, a pressure bulkhead 36 defining the avionics bay 20 and baggage compartment 38; and includes a retaining area 40 in front of the pressure bulkhead 36 for absorbing loads in the event of container detachment from the baggage compartment 38. Each rear avionics rack 26 performs a support function and includes compartments for housing equipment 42 (such as batteries or inertial units). The rear avionics racks 26 positioned on either side of the aisle serve as supports for lateral electrical pathways 44 and lateral fluid conduits 46.

[0008] The arrangement of this avionics bay is not entirely satisfactory because it is not optimal in terms of compactness.

[0009] This invention aims to overcome all or some of the shortcomings of the prior art. Summary of the Invention

[0010] Therefore, one aspect of the present invention is a transverse frame for an avionics bay of an aircraft defined by the main structure and the floor, characterized in that the transverse frame comprises:

[0011] - Vertical connecting rods, each positioned in a first transverse plane, including a first connecting portion at its upper end configured to connect to an anchor point provided in the floor, and a second connecting portion at its lower end configured to connect to an anchor point provided in the main structure.

[0012] - A first horizontal transverse member, which connects the connecting rods in pairs and is positioned in the first transverse plane.

[0013] - A vertical column, wherein the vertical column is positioned in a second transverse plane spaced apart from the first transverse plane.

[0014] - A second horizontal transverse member, which connects the columns in pairs and is positioned in the second transverse plane.

[0015] - A horizontal longitudinal member, which is oriented perpendicularly to the first transverse plane and connects in pairs to the connecting rod and the column.

[0016] The connecting rods, the columns, the first transverse member, the second transverse member, and the longitudinal member are arranged such that the transverse frame forms a grid structure with square and / or rectangular grid cells.

[0017] This transverse frame allows for optimization of the space occupied by the avionics bay, as a portion of the passageway between existing longitudinal avionics racks is occupied by the transverse frame. With this configuration, all avionics bay equipment is accessible from the open area or from the baggage compartment. Optimizing the space occupied by the avionics bay allows for an increase in baggage compartment volume.

[0018] According to another feature, at least some of the grid cells of the transverse frame include inclined stiffeners to obtain a lattice-like structure.

[0019] According to one configuration, at least some of the inclined reinforcing members are positioned in a longitudinal vertical grid cell and are inclined downward and toward the first transverse plane.

[0020] According to another feature, the transverse frame includes inclined hangers, each of which connects the upper end of a connecting rod to a column.

[0021] According to one configuration, the longitudinal member and the first transverse member and the second transverse member are arranged in the same uppermost horizontal plane to form a top horizontal support, and some of the inclined hangers are connected to the column in such a way that a portion of the top horizontal support facing the second transverse plane is left unsupported.

[0022] According to another feature, the transverse frame includes at least one shelf positioned on at least one horizontal grid cell in the horizontal grid cells and forming a shelf.

[0023] According to one configuration, the transverse frame includes at least one sliding connector that connects the device to the transverse frame and is configured to allow the device to translate relative to the transverse frame in a direction perpendicular to the first transverse plane.

[0024] According to one embodiment, a first and a second transverse member positioned between two consecutive vertical longitudinal planes can be removed to divide the transverse frame into two sub-components.

[0025] Another subject of the invention is a component module designed to be inserted into the main structure of the nose cone of an aircraft, the component module comprising a floor, an upper secondary structure, and a transverse frame according to one of the foregoing features.

[0026] Another subject of the invention is an aircraft comprising an avionics bay separated from a second bay by a rear boundary, and comprising a transverse frame according to the invention, wherein a first transverse plane of the transverse frame is positioned perpendicular to the longitudinal direction of the aircraft at the rear boundary.

[0027] According to another feature, the transverse frame includes a pressure baffle that supports against the link and provides a seal between the avionics bay and the second bay. The pressure baffle includes at least one opening, and for each opening, an ejector panel is configured to occupy a stationary state and a post-ejection separated state. In the stationary state, the ejector panel covers the opening. In the post-ejection separated state, the ejector panel exposes the opening at least partially.

[0028] According to one embodiment, the pressure diaphragm includes an opening for each transverse vertical grid cell located in the first transverse plane and for each region between the links located above the uppermost first transverse member.

[0029] According to one arrangement, the avionics bay includes: two longitudinal rows of avionics equipment racks, the two longitudinal rows of avionics equipment racks being parallel to the longitudinal direction and arranged on both sides of an open area; and a transverse avionics equipment rack, the transverse avionics equipment rack being supported by the transverse frame located at the rear of the two longitudinal rows of avionics equipment racks. Attached Figure Description

[0030] Further features and advantages will become apparent from the following description of the invention, which is given by way of example only with reference to the accompanying drawings, in which:

[0031] Figure 1 This is a side view of the aircraft;

[0032] Figure 2 This is a plan view of the rear avionics equipment rack, illustrating one embodiment of an arrangement of the prior art;

[0033] Figure 3 It is a schematic perspective view of an avionics equipment rack positioned in an avionics avionics bay, arranged to showcase existing technologies;

[0034] Figure 4 This is a schematic cross-sectional view through a transverse frame illustrating an embodiment of the invention;

[0035] Figure 5 It is a schematic perspective view of the avionics equipment rack and transverse frame positioned in the avionics bay of an aircraft illustrating one arrangement of the present invention;

[0036] Figure 6 is a perspective view of a transverse frame illustrating an embodiment of the present invention;

[0037] Figure 7 is a side view of the transverse frame visible in Figure 6;

[0038] Figure 8 is a front view of the horizontal frame visible in Figure 6;

[0039] Figure 9 is a perspective view of the transverse frame located below the floor of the aircraft's nose cone, as seen in Figure 6.

[0040] Figure 10 is a perspective view of the transverse frame supporting some of the equipment in Figure 6, as seen from the rear.

[0041] Figure 11 is a perspective view of the transverse frame supporting some of the equipment in Figure 6, as seen from the front.

[0042] Figure 12 is a perspective view of the transverse frame supporting all the equipment in Figure 6, as seen from the front.

[0043] Figure 13 is a perspective view of the transverse frame of Figure 6, located in the avionics bay, as seen from the rear, which is equipped with at least one pressure baffle and illustrates an embodiment of the invention.

[0044] Figure 14A is a schematic side view of a pressure diaphragm in a static state;

[0045] Figure 14B is a schematic side view of the pressure diaphragm in the post-ejection separation state, as seen in Figure 14A.

[0046] Figure 14C is a schematic side view of the pressure diaphragm in the disassembled state, as seen in Figure 14B.

[0047] Figure 15 It is a perspective view including the component modules of a horizontal frame that illustrates an embodiment of the present invention;

[0048] Figure 16 It is in the future Figure 15 The visible component modules are assembled into the nose cone, and the side view of the aircraft's nose cone and the component modules are shown before the step.

[0049] Figure 17 Is Figure 16 A side view of the nasal cone and component modules, visible in the image, after the step of assembling the component modules into the nasal cone. Detailed Implementation

[0050] according to Figure 16 and Figure 17In one embodiment shown, the nose cone 50 of the aircraft includes a main structure 52, which includes a lateral stiffener 52.1 called a bulkhead, a longitudinal stiffener 52.2 called a stringer, and a skin 52.3 forming the outer cladding of the aircraft. The nose cone 50 includes a floor 54 connected to the main structure 52, which divides the nose cone into two regions: an upper region corresponding to the cockpit 56 and a lower region corresponding to the avionics bay 58. The nose cone 50 also includes... Figure 16 The visible upper secondary structure 60 includes panels that separate and cover the interior of the main structure 52, as well as various equipment, accessories, and racks that are positioned on top of the floor 54 once assembled.

[0051] according to Figure 4 , Figure 5 ,as well as Figure 17 The avionics bay 58, as visible in the diagram, is defined by the following: a floor 54 at the top; a main structure 52 at the bottom and sides; a front landing gear compartment 62 at the bottom; and a rear boundary 64. Figure 4 (As can be seen in the image), the rear boundary separates the avionics compartment 58 from the second compartment, and in particular from the baggage compartment 66.

[0052] According to one configuration, the avionics bay 58 includes:

[0053] - Two longitudinal rows of avionics racks 68 and 68' are located above the nose landing gear compartment 62, parallel to the longitudinal axis 18, arranged on both sides of the open area 70, and symmetrically arranged with respect to the vertical midplane PMV passing through the longitudinal axis A18.

[0054] - An air conditioning unit, which has: a horizontal duct 72 (in...) Figure 4 As seen in Figure 12), the lateral duct is positioned in the lateral plane, behind the front landing gear compartment 62; the air handling system 74 (as seen in Figures 9, 10, 11, 13, and...) Figure 15 As can be seen in the image, the air handling system is located at the rear of the front landing gear compartment 62.

[0055] -Electrical pathway 75 ( Figure 4 (As can be seen in Figure 11)

[0056] - Other devices, such as battery 76 ( Figure 4 Figures 9, 10, 11, and... Figure 15 (See in Figures 10, 11, and 13) and inertial unit 78 (see in Figures 10, 11, and 13).

[0057] None of these components are described further because they are known to those skilled in the art.

[0058] According to one feature of the invention, the avionics bay 58 includes a transverse frame 80 located at the rear of the nose landing gear compartment 62.

[0059] According to one embodiment shown in Figures 6 to 8 and Figure 11, the transverse frame 80 includes:

[0060] - Vertical links 82.1 to 82.6, positioned in the first transverse plane P1, each vertical link including a first connection 84.1 at its upper end and a second connection 84.2 at its lower end, the first connection being configured to connect to an anchor point provided in the floor 54, and the second connection being configured to connect to an anchor point provided in the main structure 52.

[0061] - First horizontal transverse members 86.1 to 86.3, which are paired to connect to links 82.1 to 82.6 and are positioned in the first transverse plane P1.

[0062] - Vertical columns 88.1 to 88.6, these vertical columns are positioned in a second transverse plane P2 that is parallel to and spaced apart from plane P1.

[0063] - Second horizontal transverse members 90.1 to 90.3, which connect in pairs to columns 88.1 to 88.6 and are positioned in the second transverse plane P2.

[0064] - Horizontal longitudinal members 92, which are oriented perpendicularly to the first transverse plane P1 and connect in pairs to the connecting rods 82.1 to 82.6 and the columns 88.1 to 88.6.

[0065] Links 82.1 to 82.6 are arranged symmetrically with respect to the vertical midplane PMV. According to one configuration, the transverse frame 80 includes six links 82.1 to 82.6, which traverse the entire width of the avionics bay 58, corresponding to the dimensions of the avionics bay in the first transverse plane P1. When viewed from the rear of the aircraft forward, these links are numbered 82.1 to 82.6 from left to right.

[0066] Links 82.1 to 82.6 are connected by the following: a top first transverse member 86.1 of a first series located in the same first horizontal longitudinal plane PH1; a middle first transverse member 86.2 of a second series located in the same second horizontal longitudinal plane PH2; and a bottom first transverse member 86.3 of a third series located in the same third horizontal longitudinal plane PH3.

[0067] According to one configuration, the first link 82.1 and the second link 82.2 are connected by a top first transverse member 86.1 and a middle first transverse member 86.2; the second link 82.2 and the third link 82.3 are connected by a top first transverse member 86.1, a middle first transverse member 86.2, and a bottom first transverse member 86.3; the third link 82.3 and the fourth link 82.4 are connected by a top first transverse member 86.1 and a middle first transverse member 86.2; the fourth link 82.4 and the fifth link 82.5 are connected by a top first transverse member 86.1, a middle first transverse member 86.2, and a bottom first transverse member 86.3; and the fifth link 82.5 and the sixth link 82.6 are connected by a top first transverse member 86.1 and a middle first transverse member 86.2.

[0068] The transverse frame 80 includes as many columns 88.1 to 88.6 as links 82.1 to 82.6. Therefore, the transverse frame 80 includes six columns 88.1 to 88.6 distributed across the entire width of the avionics bay 58, with columns 88.1 to 88.6 respectively arranged in the same vertical longitudinal planes PV1 to PV6 as links 82.1 to 82.6.

[0069] The columns 88.1 to 88.2 are connected by the following: a first series of top second transverse members 90.1 positioned in the same first horizontal longitudinal plane PH1 as the top first transverse member 86.1; a second series of intermediate second transverse members 90.2 positioned in the same second horizontal longitudinal plane PH2 as the intermediate first transverse member 86.2; and a third series of bottom second transverse members 90.3 positioned in the same third horizontal longitudinal plane PH3 as the bottom first transverse member 86.3.

[0070] According to one configuration, the first column 88.1 and the second column 88.2 are connected by a top second transverse member 90.1 and a middle second transverse member 90.2; the second column 88.2 and the third column 88.3 are connected by a top second transverse member 90.1 and a middle second transverse member 90.2; the third column 88.3 and the fourth column 88.4 are connected by a top second transverse member 90.1, a middle second transverse member 90.2, and a bottom second transverse member 90.3; the fourth column 88.4 and the fifth column 88.5 are connected by a top second transverse member 90.1, a middle second transverse member 90.2, and a bottom second transverse member 90.3; and the fifth column 88.5 and the sixth column 88.6 are connected by a top second transverse member 90.1 and a middle second transverse member 90.2.

[0071] According to one embodiment shown in Figure 11, the first post 88.1 and the sixth post 88.6 connect the top second transverse member 90.1 and the middle second transverse member 90.2, and do not extend beyond these transverse members. Other posts 88.2 to 88.5 connect the top second transverse member 90.1 and the bottom second transverse member 90.3, and do not extend beyond these transverse members.

[0072] According to one configuration, each joint where the connecting rods 82.1 to 82.6 intersect with the first transverse members 86.1 to 86.3 is connected via longitudinal members 92 to the corresponding joint where the columns 88.1 to 88.6 intersect with the second transverse members 90.1 to 90.3 (the same vertical longitudinal planes PV1 to PV6 and the same horizontal longitudinal planes PH1 to PH3).

[0073] Of course, the present invention is not limited to this number of links and columns, or to this configuration of the first transverse member and the second transverse member.

[0074] Regardless of the embodiment, the links 82.1 to 82.6, the columns 88.1 to 88.6, the first transverse members 86.1 to 86.3 and the second transverse members 90.1 to 90.3, and the longitudinal members 92 are arranged such that the transverse frame 80 forms a grid structure with square and / or rectangular grid cells; the two longitudinal members 92, the first transverse members 86.1 to 86.3, and the second transverse members 90.1 to 90.3 form horizontal grid cells; the two longitudinal members, the links 82.1 to 82.6, and the columns 88.1 and 88.6 form vertical grid cells; the two first transverse members 86.1 to 86.3 and the two links 82.1 to 82.6 form transverse and vertical grid cells, or the two second transverse members 90.1 to 90.3 and the two columns 88.1 to 88.6 form transverse and vertical grid cells.

[0075] According to one embodiment, the transverse frame 80 is made of metal and is a fully welded structure. Of course, the invention is not limited to this material or manufacturing method.

[0076] According to a configuration shown in Figures 6 and 11, the first and second transverse members, which connect the third link 82.3 and the fourth link 82.4, and the third column 88.3 and the fourth column 88.4, can be removed between two consecutive vertical longitudinal planes PV3 and PV4. Therefore, the transverse frame 80 includes two fully welded sub-assemblies 80.1 and 80.2, which are manufactured independently of each other and can be independently connected to the floor 54.

[0077] According to one configuration, the first lateral plane P1 on which the connecting rods 82.1 to 82.6 are located is offset rearward relative to the second lateral plane P2 on which the columns 88.1 to 88.6 are located. The first lateral plane P1 forms the front surface F1 of the lateral frame 80 accessible from the luggage compartment 66.

[0078] The first transverse members 86.1 to 86.3 and the second transverse members 90.1 to 90.3, along with the longitudinal member 92, arranged in the same horizontal longitudinal plane PH1 or PH3, form continuous or discontinuous horizontal supports. Therefore, the transverse frame 80 includes a top horizontal support S1 arranged in the horizontal longitudinal plane PH1, an intermediate horizontal support S2 arranged in the horizontal longitudinal plane PH2, and a bottom horizontal support S3 arranged in the horizontal longitudinal plane PH3.

[0079] According to one embodiment, the transverse frame 80 includes at least one shelf 94 positioned in at least one horizontal grid cell and supported by two longitudinal members 92, first transverse members 86.1 to 86.3, and second transverse members 90.1 to 90.3. Each shelf 94 has substantially the same profile as the horizontal grid cell housing it. This shelf 94 forms a shelf unit.

[0080] These shelves 94 are positioned according to the equipment installed in the transverse frame 80. For example, they are used to support the battery 76.

[0081] According to one embodiment, the transverse frame 80 includes at least one sliding connector 95 (visible in FIG11), which is, for example, two rails connecting the device and the transverse frame 80, and is configured to allow the device to translate relative to the transverse frame in a direction perpendicular to the first transverse plane P1, so as to allow the device to be withdrawn.

[0082] The transverse frame 80 includes at least one inclined stiffener 96. At least some grid cells of the transverse frame 80 include the inclined stiffener 96 to achieve a lattice-like structure. The inclined stiffener 96 is positioned such that it enhances load absorption in the longitudinal direction from front to back. Therefore, the inclined stiffener 96 is provided in at least some longitudinal vertical grid cells and / or horizontal grid cells. Thus, as shown in FIG7, if the container 98 detaches, the transverse frame 80 provides effective load absorption.

[0083] The arrangement of at least some of these inclined stiffeners 96' at the longitudinal vertical grid cells, inclined downward and toward the first transverse plane, will transfer the load applied on the second transverse plane P2 toward the anchoring point provided on the main structure 52.

[0084] The transverse frame 80 includes inclined hangers 100.1 to 100.6, each of which connects the upper end of links 82.1 to 82.6 and columns 88.1 to 88.6. These inclined hangers 100.1 to 100.6 transfer the load applied on the second transverse plane P2 toward the anchor points provided on the floor 54.

[0085] According to one configuration, the transverse frame 80 includes: end tilting hangers 100.1, 100.6, which connect the upper ends of the first link 82.1 and the last link 82.6, and the upper ends of the first column 88.1 and the last column 88.6; and intermediate tilting hangers 100.2 to 100.5, which connect the upper ends of the links 82.2 to 82.5 and the columns 88.2 to 88.5 at the level of the intermediate second transverse member 90.2. Therefore, a portion of the orientation of the top horizontal support S1 toward the second transverse plane P2 is left unobstructed and not hindered by the intermediate tilting hangers 100.2 to 100.5, meaning that this space can accommodate the transverse avionics rack 102 located behind the two longitudinal rows of avionics racks 68, 68', such as... Figure 5 Figure 9, and Figure 15 What is shown.

[0086] The inclined hangers 100.1 to 100.6 and the inclined stiffeners 96, 96' allow the load to be transferred from the second transverse plane P2 to the first transverse plane P1, meaning that it is not necessary to connect the columns 88.1 to 88.6 to the floor 54 or to the main structure 52. This design allows for a reduction in the number of fixing points between the transverse frame 80 and the main structure 52 / floor 54.

[0087] According to another feature, the transverse frame 80 includes tie rods 104 for connecting it to the main structure 52 or the floor 54. In one configuration, two tie rods 104 connect the upper ends of the first upright 88.1 and the last upright 88.6 to the floor 54. Tie rods 104' connect longitudinal members 92 located at each end of the horizontal supports S1 to S3, and are positioned in a transverse plane (parallel to both the first and second transverse planes P1 and P2) between the first transverse plane P1 and the second transverse plane P2, absorbing loads in the horizontal transverse direction.

[0088] According to one embodiment shown in Figure 13, the front face F1 of the transverse frame 80 includes a pressure baffle 106 that seals and supports abutment links 82.1 to 82.6 between the avionics bay 58 and the baggage compartment 66. To provide access to the transverse frame 80, the pressure baffle 106 includes at least one opening 108. According to one configuration, the pressure baffle 106 includes an opening 108 for each transverse vertical grid cell located in the first transverse plane P1, and for each region located between links 82.1 to 82.6 above the top first transverse member 86.1.

[0089] For each opening 108, the pressure baffle 106 includes an ejection panel 110. Each ejection panel 110 is configured to occupy: a stationary state, as seen in FIG. 14A, in which the pressure relief panel closes the opening 108; a post-ejection separation state, as seen in FIG. 14B, in which the pressure relief panel exposes the opening 108 at least partially; and a dismounted state, as seen in FIG. 14C, in which the pressure relief panel exposes the opening 108 fully to allow access to the transverse frame 80 from the luggage compartment 66.

[0090] Therefore, for each pressure relief panel 110, the pressure baffle 106 includes a connector that connects the pressure relief panel 110 to the remainder of the pressure baffle 106. This connector is configured to provide a seal between the pressure relief panel 110 and the remainder of the pressure baffle 106 in a static state, and to eject when the pressure difference on the pressure baffle 106 exceeds a given threshold to transition from a static state to a disengaged state, so as to allow the pressure relief panel 110 to be disassembled and reassembled.

[0091] According to one embodiment, at least one connector (preferably four connectors at each corner of the ejector panel 110) is provided to fasten the ejector panel 110 to the remainder of the pressure baffle 106, thereby restricting the movement of the ejector panel 110 when transitioning from a stationary state to a separated state under overpressure conditions.

[0092] according to Figure 4 Figure 12 and Figure 15In one arrangement, the electrical path 75 is positioned on the rear portion of the top horizontal support S1. The transverse avionics frame 102 is at least partially positioned on the front portion of the top horizontal support S1. Transverse conduits 72 are fixed below the transverse avionics frame 102 to columns 88.1 to 88.2 and / or to second transverse members 90.1 to 90.3. An air handling system 74 is positioned between a third link 82.3 and a fourth link 82.4. Finally, a battery 76 and an inertial unit 78 are positioned on intermediate horizontal supports S2 and bottom horizontal supports S3 on either side of the third link 82.3 and the fourth link 82.4. Of course, the invention is not limited to this arrangement. Other arrangements are conceivable.

[0093] According to the assembly method, the component module 112, including the floor 54, the upper secondary structure 60, the transverse frame 80, and its equipment, is assembled, and the transverse frame 80 is fixed to the floor 54 using the first connecting part 84.1 and the tie rod 104. This operation can be performed simultaneously with the main structure 52 of the nose cone.

[0094] Next, component module 112 is inserted into and connected to the main structure 52. The transverse frame 80 is secured to the main structure 52 using the second connecting part 84.2 and the tie rod 104'.

[0095] The pressure baffle 106 is assembled with the ejection panel 110 before or after the insertion component module 112.

[0096] like Figure 4 and Figure 5 As shown, the transverse frame 80 optimizes the use of space in the avionics bay 58, while a portion of the passageway provided between the existing longitudinal avionics racks 68, 68' is occupied by the transverse frame 80. With this configuration, all equipment in the avionics bay 58 is accessible from the open area 70 or from the baggage compartment 66. Optimizing the space occupied by the avionics bay 58 allows for an increase in the volume of the baggage compartment 66.

[0097] The pressure baffle 106 has a removable ejector panel 110 that makes the equipment mounted on the transverse frame 80 more accessible.

[0098] The mesh structure (possibly reinforced) of the transverse frame allows for a reduction in the holding area used to absorb loads in the event of container detachment in the baggage compartment 66, thereby ultimately allowing for an increase in the volume of the baggage compartment 66.

[0099] According to another aspect, the transverse frame 80 includes a reduced number of connectors to the floor 54 and the main structure 52, thereby reducing assembly time. Furthermore, because these connectors are positioned in the first transverse plane P1, they are easily accessible from the luggage compartment 66.

[0100] Finally, the transverse frame 80 means that equipment located in the avionics bay 58 can be secured to the component module and introduced into the main structure 52 of the aircraft in a single step.

Claims

1. An aircraft comprising an avionics bay (58) separated from a second bay (66) by a rear boundary (64) and a transverse frame (80) for the avionics bay (58), the avionics bay being defined by a main structure (52) and a floor (54), wherein, The transverse frame includes: Vertical connecting rods (82.1 to 82.6) are positioned in a first transverse plane (P1), each of the vertical connecting rods including a first connecting portion (84.1) at the upper end connected to an anchor point provided in the floor (54), and a second connecting portion (84.2) at the lower end connected to an anchor point provided in the main structure (52). A first horizontal transverse member (86.1 to 86.3), which connects in pairs to the vertical connecting rods (82.1 to 82.6) and is positioned in the first transverse plane (P1). Vertical columns (88.1 to 88.6) are positioned in a second transverse plane (P2) spaced apart from the first transverse plane (P1). The second horizontal transverse member (90.1 to 90.3), which connects in pairs to the vertical columns (88.1 to 88.6) and is positioned in the second transverse plane (P2), and A horizontal longitudinal member (92) is oriented perpendicularly to the first transverse plane (P1) and connects in pairs the vertical connecting rods (82.1 to 82.6) and the vertical columns (88.1 to 88.6). The vertical connecting rods (82.1 to 82.6), the vertical columns (88.1 to 88.6), the first horizontal transverse member (86.1 to 86.3), the second horizontal transverse member (90.1 to 90.3), and the horizontal longitudinal member (92) are arranged such that the transverse frame (80) forms a grid structure with square and / or rectangular grid cells. The transverse frame (80) includes inclined hangers (100.1 to 100.6), each of which connects the vertical connecting rod (82.1 to 82.6) to the vertical column (88.1 to 88.6). The horizontal longitudinal member (92), the first horizontal transverse member (86.1), and the second horizontal transverse member (90.1) are arranged in the same uppermost horizontal plane to form a top horizontal support member (S1). Some of the inclined hangers (100.2 to 100.5) are connected to the vertical column (88.1 to 88.6) in such a way that a portion of the top horizontal support (S1) facing the second transverse plane (P2) is left unsupported.

2. The aircraft according to claim 1, characterized in that, At least some of the grid cells of the transverse frame (80) include inclined stiffeners (96, 96') to obtain a lattice-like structure.

3. The aircraft according to claim 2, characterized in that, At least some of the inclined reinforcing members (96') are positioned in a longitudinally vertical grid cell and are inclined downward and toward the first transverse plane (P1).

4. The aircraft according to any one of claims 1 to 3, characterized in that, The transverse frame includes at least one shelf (94) positioned on at least one grid cell in a horizontal grid cell and forming a shelf.

5. The aircraft according to any one of claims 1 to 3, characterized in that, The transverse frame (80) includes at least one sliding connector (95) that connects the device to the transverse frame (80) and is configured to allow the device to translate relative to the transverse frame (80) in a direction perpendicular to the first transverse plane (P1).

6. The aircraft according to any one of claims 1 to 3, characterized in that, The first and second horizontal transverse members, positioned between two consecutive vertical longitudinal planes (PV3, PV4), can be removed to divide the transverse frame into two sub-assemblies (80.1, 80.2).

7. The aircraft according to any one of claims 1 to 3, characterized in that, The first transverse plane (P1) of the transverse frame (80) is positioned perpendicular to the longitudinal direction of the aircraft at the rear boundary (64).

8. The aircraft according to claim 7, characterized in that, The transverse frame (80) includes a pressure baffle (106) that supports against the vertical connecting rods (82.1 to 82.6) and provides a seal between the avionics bay (58) and the second bay (66). The pressure baffle (106) includes at least one opening (108), and for each opening (108), an ejection panel (110) is configured to occupy a stationary state and a post-ejection separation state, in which the ejection panel (110) covers the opening (108), and in the post-ejection separation state, the ejection panel (110) exposes the opening (108) at least partially.

9. The aircraft according to claim 8, characterized in that, For each transverse vertical grid cell located in the first transverse plane (P1), and for each region between the vertical links (82.1 to 82.6) located above the uppermost first horizontal transverse member (86.1), the pressure diaphragm (106) includes an opening (108).

10. The aircraft according to any one of claims 1 to 3, characterized in that, The avionics bay (58) includes: two longitudinal rows of avionics racks (68, 68'), which are parallel to the longitudinal direction and arranged on both sides of the open area (70); and a transverse avionics rack (102), which is supported by the transverse frame (80) located at the rear of the two longitudinal rows of avionics racks (68, 68').

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