• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Aircraft comprising a fuselage (1) divided by a floor (2) into an upper volume (3) and a lower volume (4) in which floor-supporting beams (5) extend and delimit with the fuselage and floor two lateral housings (6) which have a substantially triangular cross-section and extend parallel to a longitudinal direction of the fuselage. Calculation units (100) are arranged in the side housings and each comprises a housing (101) defining a main compartment containing calculation modules (122) insertable into the main compartment in an insertion direction through an opening thereof. ci and connectable to connectors (115) carried by a bottom wall (116) of the compartment to open into the main compartment opposite the opening, the insertion direction being substantially parallel to the longitudinal direction of the fuselage.
    公开号:FR3056964A1
    申请号:FR1659469
    申请日:2016-09-30
    公开日:2018-04-06
    发明作者:Francois Guillot；Jean-Marc BLINEAU；Philippe Avignon；Serge Roques；Franck Albero
    申请人:Safran Electronics and Defense SAS；Safran Electrical and Power SAS；
    IPC主号:
    专利说明:

    Holder (s): SAFRAN ELECTRONICS & DEFENSE Simplified joint-stock company, SAFRAN ELECTRICAL & POWER Simplified joint-stock company.
    Extension request (s)
    Agent (s): CABINET BOETTCHER.
    P4j AIRCRAFT HAVING DISTRIBUTED CALCULATORS IN THE FUSELAGE.
    FR 3 056 964 - A1 (57) Aircraft comprising a fuselage (1) divided by a floor (2) into an upper volume (3) and a lower volume (4) in which extend beams (5) supporting the floor and delimiting with the fuselage and the floor two lateral housings (6) which have a substantially triangular cross section and which extend parallel to a longitudinal direction of the fuselage. Calculation units (100) are arranged in the lateral housings and each comprise a housing (101) defining a main compartment containing calculation modules (122) insertable in the main compartment according to an insertion direction through an opening thereof. ci and connectable to connectors (115) carried by a bottom wall (116) of the compartment to open into the main compartment opposite the opening, the direction of insertion being substantially parallel to the longitudinal direction of the fuselage.
    The present invention relates to the field of aeronautics.
    STATE OF THE ART
    A passenger transport aircraft generally comprises a fuselage divided by a floor into a higher volume, the cabin, comprising seats receiving travelers, and a lower volume, the hold, accommodating the luggage of travelers. 'In the lower volume extend beams supporting the floor and separating with the fuselage and the floor two lateral housings (commonly called "cargo triangle zones") which have a substantially triangular cross section and which extend: parallel to : a longitudinal direction of the fuselage on either side of a median zone (commonly called “useful cargo zone”). Because of their shape, the side housings are considered to be a dead volume used only to run the various cables and fluid lines therein used for the operation of the aircraft and its equipment.
    It is known to install in the middle area of the lower volume, generally in the vicinity of the cockpit of the aircraft, calculation units or bays each comprising: a box defining a Gdmpartiinent containing: insertable calculation modules: in the corrt25 part in a direction of insertion by an opening thereof and connectable to connectors carried: by a bottom wall of the compartment to open into the compartment opposite the opening. By “calculation module” is meant any snseep30 electronic circuit capable of processing signals and / or data:, and in particular of making: calculations on these signals or these data. The electronic circuit can constitute a computer and include a set of processors of ASIA type or other, A programmable network of: FBGA type. . . The calculation modules are mainly connected to the control instruments on which the pilot of the aircraft acts, to indicators for the pilot's information, to sensors distributed in the aircraft and to equipment of 1 ' aircraft.
    The search for the optimization of the occupancy of space in the aircraft makes problematic the installation of the computing units on board the aircraft.
    OBJECT OF THE INVENTION
    The object of the invention is to provide a solution to this problem.
    BRIEF STATEMENT OF THE INVENTION
    To this end, provision is made, according to the invention, for an aircraft 'comprising a fuselage and calculation units distributed in the fuselage. The fuselage is divided by a floor into an upper volume and a lower volume in which extend beams supporting the floor and delimiting with the fuselage and the floor two lateral housings which have a triangular cross section which extend parallel to a longitudinal direction of the fuselage. The calculation units are arranged in the lower volume and each comprise a housing defining a main compartment containing calculation modules insertable into the main compartment in an insertion direction through an opening thereof and connectable to worn connectors by a bottom wall of the main compartment to open into the compartment: main opposite the opening. The computing units are arranged in at least one of the lateral housings in such a way that the direction of insertion is substantially parallel to the longitudinal direction of the fuselage.
    Thus, the invention allows the use of lateral housings of the lower volume by accommodating there · Calculation Units without excessively affecting the accessibility of the calculation modules and connectors allowing the connection of the calculation modules to the electrical harness of 1 ' aircraft.
    According to a first particular characteristic, the housing delimits an auxiliary compartment for a common cooling module connected to a cooling air duct.
    The common module then preferably comprises a non-return valve arranged to allow a passage of cooling air from the duct to the common module and to oppose an air flow in the opposite direction, and the common module comprises a socket. of outdoor air associated with a fan for introducing air into the common module and to a non-return valve arranged to allow air to pass from the fan to the common module and to oppose air circulation in the opposite direction.
    Advantageously, the common module comprises an outside air intake and a fan which is mounted opposite this air intake and which is associated with an air filtering device by centrifugation,
    According to a second particular characteristic, one of the electronic modules is arranged in two directions opposite to each other in a direction of introduction into the compartment, the compartment comprising means for supplying electrical power to the electronic module and means for connecting the electronic unit to the electronic module, these means leading to a connection face belonging to the receiving compartment extending parallel to the direction of introduction.
    According to a third particular characteristic, at least, one of the calculation modules comprises · pins intended to be engaged in metallized holes of a printed circuit board, the printed circuit board: being covered with a layer: of electrically insulating flexible material which is pierced by the pins when
    these are engaged in the metallized holes and are clamped between a pin holder and the printed circuit board.
    Other characteristics and advantages of the invention will become apparent on reading the. description which follows of particular nonlimiting embodiments: die 1 / invention.
    BRIEF DESCRIPTION OF THE FIGURES Reference will be made to the attached drawings, among which:
    - Figure 1 is a schematic view of an aircraft according to the invention;
    - Figure 2 is. one: schematic view: in section of this aircraft along line II of FIG. 1;
    - Figure 3 is a schematic side view of a computing unit according to the invention;
    - Figure 4 is a: schêmatiqüé enlarged and sectional view along plane II of Figure 1 of the common cooling and supply module 7 ;
    - figured 5: est. a schematic front view of a fan of this common cooling and supply module;
    - Figure 6 is a view: in cross section showing: the connection of one of: · calculation modules to a printed circuit board;
    - Figure 7 is a partial perspective view of a compartment of a computing unit and: d: 'a first type of module: electronic: intended to be e m n ed;
    - Figure 8 is a view: schematic of an electronic circuit of a first type of electronic module according to the invention;
    FIG. 9 is a schematic perspective view of a second: typed die: module: electronics:
    according to the invention;
    - Figure 10 is a view identical to Figure 1 on which the electronic modules are represented before their installation in the computing units;
    - Figure 11 is a detailed sectional view along a plane XI-XI of Figure 7, to show a step of mounting an electronic module in a unit- calculation according to 1'invent ion;
    - Figure 12 is a detailed sectional view along the plane XI-XI of an electronic module mounted in a computing unit according to the invention;
    - Figure 13 is a schematic view of a connection face of a particular embodiment of a computing unit according to the invention;
    - Figure 14 is a view, in longitudinal section along a plane XIV-XIV in Figure 13, of debt unit de- calculation;
    - Figure 15 is a schematic view of a connection face of a common module according to a particular embodiment of one invention;
    FIG. 16 is a view, in section on the plane XIV-XIV, showing the assembly of the calculation unit of FIG. 14 and the common module of FIG. 15,
    - the figure 17 is a view similar to. that of the figure 16 showing a first step of of- installation of the common module F the, figure 18 is a view- similar to that of the- figure 16 showing a second stage of of- installation of the common module r " the.· figure- 19 is a view similar to that of the·. figure 16 - showing a third step of,
    removal of the common module,
    DETAILED DESCRIPTION OF THE INVENTION
    Referring to the figures, the aircraft generally comprises a fuselage 1 divided by a floor 2 into an upper volume 3 and a lower volume 4. The upper volume 3 is intended to receive seats for picking up passengers and constitutes the cabin of the aircraft; the lower volume 4 is intended for a. receive travelers' or cargo baggage - and constitutes · the hold of the aircraft.
    In the lower volume 4 extend pou10 trelies 5 supporting the floor 2 and delimiting with the fuselage 1 and the floor 2 two lateral housings 6 which have a substantially triangular cross section and which extend parallel to a longitudinal direction L -fuselage 1 on either side of a zone mè15; diané or centrale 7. In the lateral housings - 6 run under the floor 2 of the cables 8 of the electric harness 9 of the aircraft and one of D-S; main lines or tubing; 10 air conditioning carrying air blown in; the upper volume 3 to cool it. 'The wiring harness 9 - includes cables - used for power transmission and: cables - for signal transmission; control and data.
    The aircraft comprises calculation units 100 each comprising a housing 101 defining a main compartment 102, a first auxiliary compartment 103 extending under the main compartment 102 'and a second auxiliary compartment 104 extending behind an upper part of the first auxiliary compartment 102 and behind a lower part of the main compartment 102. The housing 101 comprises a front opening 105 for access to the main compartment 102; ; two lateral openings 106 for access to the main compartment 102 f the two lateral openings; 07:, opposite the one another, access to the first auxiliary compartment
    103; and two lateral openings 108; ·, opposite one another, for access to the second auxiliary compartment 104. The front opening 105 is left open; the side openings · 106 are closed by a removable panel 10 9; · the side openings 107, 108 oriented towards the middle zone 7 are left open; the lateral openings 107, 108 oriented opposite the middle zone 7 are closed by a removable panel 1.10,
    111. The removable panels are held in the closed position by a quick locking mechanism or by screws. panels 110, 111 can be mounted on one
    OR the other of the side openings 107, 108 according to the direction of mounting of the computing unit 100 in the lateral housing 6 as will be seen below.
    The main compartment 102 contains models of calculation, generally designated at 122; the first auxiliary compartment 103 contains a common module, generally designated at 125, for cooling and supplying the calculation modules 122; and the second auxiliary compartment 104 contains a common module, generally designated at 124, for interconnecting the calculation modules 122. The common modules: 123, 124 provide a transverse function for 'them; calculation modules 122.
    The calculation modules 122 can be inserted into the main compartment 102 in an insertion direction I through the front opening 105 of the housing 101 and are connectable to connectors 115- carried by a bottom wall 116 of the housing 101 so as to open into the main compartment 102 opposite the front opening 105. The calculation modules 122 have
    An overhanging front face which is fixed on the housing 101 and which partially closes the opening 105 (this opening being completely closed when all the calculation modules 122 are in place), the connectors 115 are connected to cables of the electrical harness 9 mainly dedicated to the transmission of control and data signals so as to connect the calculation modules 122 mainly to the control instruments on which the pilot of the aircraft acts, to indicators for the information of - pilot, to sensors distributed in
    The aircraft and aircraft equipment. the calculation modules 122 include a printed circuit board carrying electronic control- and / or power components c they · are known- in themselves and will not be more: detailed here. The calculation modules 122 also carry on their edge opposite the opening 105 a connector allowing their connection to a connector carried by a face of a printed circuit board 118 ′ which separates the lower part from the bottom of the main compartment 102 and the second auxiliary compartment 104 and 'së extends into the first auxiliary compartment 103. The calculation modules 122 are mounted in the main compartment -102 by means of slides 117 which are fixed in the housing 1 for s extend per— p end icu la ir entent to the opening '105' and therefore parallel to the direction of insertion I. The slides 117 are made of thermally conductive material to drain by conduction part of the heat produced by the electronic components of the calculation modules 122- to the housing 101. The housing 101 is for this purpose produced at
    25- less partially of thermally conductive material so as to allow- evacuation, to the outside of the heat produced · by the operation of the calculation modules 122. In addition, the housing is provided with openings on its upper wall for allow the escape of a convective flow.
    The: connector of the calculation modules 122 allowing their connection to the printed circuit board 118 comprises an ISO support 'projecting' from which extend, parallel to the direction of insertion I, pins' 151 elastically deformable in a transverse plane at their longitudinal axis between a relaxed state and a deformed state, the pins 151 having a larger cross section in the relaxed state than in the deformed state. The corresponding connector of the printed circuit board 118 includes metallized holes 152 each intended to receive one of the pins 151 which is forcibly engaged in the metallized hole and is clamped there in its deformed state. The printed circuit board 118 is not placed in a dust-tight enclosure. In a carbon fuselage aircraft, there is a risk that carbon dust · will settle on the printed circuit board and create short circuits. To avoid this)., The printed circuit board 118 is covered with a layer of tri-insulating electrical material 153 which is pierced by the pins 151 when these are engaged in the metallized holes 152. When the calculation modules 122 are connected to the printed circuit board 118, the layer of electrically insulating material 1.53 is clamped between the supports
    150 'and the printed circuit board 118, which tends to close the tears caused by the pins 151 and prevents dust · from getting between the calculation modules 122 and the printed circuit board 113. The electrically insulating material is here a silicone and more particularly one if the icon · vulcanizable at ambient temperature (or RTV for “Roôm Vulcanization Temperature”). Of course, any material having an elasiomeric behavior can be used, and in particular other types of silicone,
    The common module 123 is inserted into the first auxiliary compartment 103 through the lateral opening 107 oriented towards the middle zone · 7 in an insertion direction P perpendicular to the insertion direction
    I. The common module 123 has an overhanging front face 112 which is fixed to the housing 101 and which closes ίο
    Opening 107.
    As visible in FIGS. 7 and 10, the common module 124 is inserted into the second auxiliary compartment 104 by the lateral opening 108 oriented towards the middle zone 7 in an insertion direction P 'perpendicular to the insertion direction I. The common module 124 has an overhanging front face which is fixed to the casing 101 and which closes the opening 108 ·.
    The common modules · 123 and 124 both carry flexible contacts allowing them to be connected to conductive pads of the printed circuit board 118 · which is itself connected, on the one hand, to the 'calculation modules 122 as mentioned above and, on the other hand, to a connector 119 carried by the bottom wall 116 and connected to power cables and for wiring harness control 9.
    'The flexible contacts are arranged on either side of a center line parallel to the direction of insertion in such a way that the contacts intended to receive the supply comprise a pole: positive and a negative pole extending along a line perpendicular to the center line with one of the poles above the center line and the other of the poles below the center line.
    The second auxiliary compartment 104 comprises a connection face 160 extending parallel to the direction of insertion P ', facing the printed circuit' 118 '. One first conductive pad 161 and a second conductive pad 162 disposed on either side of a center line 163 of the connection face 160 open onto the connection face 160. A central conductive pad 164 located · on the center line 163 opens · also on the connection face 160. · the conductive areas 161, 162 and 16 · 4 are oblbngues and extend in a direction parallel to the center line 163. The first conductive area 161 is connected to a first track of the printed circuit 118 and constitutes a positive pole of an electrical supply 165, the second conductive pad 162 is in turn connected to a second track of printed circuit 118 and constitutes a negative pole of an electrical supply 165. The conductive track centf ale 164 constitutes a mass of the electrical supply 165. 'Magnetic couplers 166.1 to 166.12 also lead to the connection face 160. One p The first series of magnetically coupled couplers comprises magnetic couplers 166.1 to 166.6 which extend symmetrically on either side of the center line · 163 · in the vicinity of a first opening 108 in compartment 104. A second series of magnetic couplers comprises magnetic couplers 166.7 to 166112 which extend symmetrically on either side of the center line 163 near a second opening 108 of the compartment 104 opposite the first: opening 108. Optical couplers 167.1 to 167.4 also open out on the connection face 160. A first series of optical couplers comprises the optical couplers 167.1 and 167.2 which extend symmetrically on either side of the center line 163 near a first opening 108 of the compartment 104. A second series of optical couplers Includes optical couplers 167.3 and 167.4 which extend symmetrically on either side of the median line 163 near a second opening 108 of the compartment 104 opposite the first opening 10 8. The first series: of optical couplers 163 '. 1 and 167.2 and the first series of magnetic couplers 166.1 to 166.6 are respectively symmetrical to the second series of optical couplers 167.3 and 167.4 and the: second: series of magnetic couplers 166.7 to 16: 6: .12 by r appor t to a median plane of the face 160 orthogonal to the direction mé35 diane 163.
    The magnetic couplers 166.1 to 166.12 and the optical couplers 167.1 to 167.4 are connected to the printed circuit 118. The connection face 160 is covered with a thin layer 168 of PTFË · and the face 169 opposite) to l; a; branch face 160 includes; three longitudinal springs 170.1 to 170.3 extending parallel to the center line 163 ;. The printed circuit 118 is connected, on the one hand, to the calculation modules 122 like this; the · was mentioned above and, on the other hand, to a connector 119 carried by the bottom wall 116 and connected to cables power and harness control 9.
    The module 124 is here substantially rectangular in shape and includes two ends of; introduction respectively 125 and 126 of the module 124 into the compartment 104 in two opposite directions of the direction of introduction P '. The module 124 also includes a; connection face 127 to the housing 10 0 onto which open a first and a second flexible contact respectively, 171 and 172, disposed on either side of a center line 173 of the connection face 127. A third central flexible contact 174 located on the median line 173 also leads to the face; of connection; 127. As can be seen in FIG. 7, the flexible contacts 171, 172 and 174 extend in a direction parallel to the center line 173 and the branch face 123 extends parallel to the direction d) of introduction P '. Magnetic couplers; 17 5.1 to 175.12 also lead to the connection face 127. A first series of magnetic couplers comprises magnetic couplers 135.) 1 to 175.6 which extend symmetrically on either side of the line -medium 173 in the vicinity · of The insertion end 125. A second series of couplers; magnetic includes magnetic couplers; 17) 5.7 to 17 5.12) which extend symmetrically on either side of the center line 173 near the insertion end 126. Optical splitters 176.1 to 176.4 also open out on the connection face 127 and extend symmetrically on either side of the center line 173. One · first series of optical couplers comprises optical couplers 17 6.1 and 176.2 which extend symmetrically on either side of the center line ' 173 near the insertion end 12'5. A second series of optical couplers comprises optical couplers 176.3 and 17 6.4 which extend symmetrically on either side of the center line · 173 near the insertion end 126. The first series of optical couplers 176.1 and 176.2 and the first series of magnetic couplers 175.1 to 175.6 are respectively symmetrical to the second series of optical couplers 176.3 and 176.4 and the second series of magnetic couplers 175.7 to 175.12 with respect to a median plane of the face 127 orthogonal to the middle direction 173. The branching face 127 is covered with a thin layer 177 of PTFE.
    The flexible contacts 171 and 172, the magnetic couplers 175.1 to 175.12 and the optical couplers 176.1 to 176.4 are connected · to an electronic circuit 180 · which comprises a first circuit 181 and a second circuit 182 ', For • reasons of clarity ··, only two magnetic couplers 175.1 and 175.4 on all of the magnetic couplers 175.1 to 175.6 and optical couplers 176.1 and 176.2 will be represented in the diagram in FIG. 8. The flexible contacts 171 and 172 are connected to the input terminals of a first circuit 181 which includes a diode bridge 183. This first circuit 181 makes it possible to restore a constant supply polarity between its output terminals : 184 and 185 whatever the polarity of the voltage applied between the flexible · knives ·: 171 and 172. The second · circuit 183 is connected to the magnetic couplers 175:, - 1 and 17 5.4 which are here transmitters / 'rece ers whose par t ie transmission is set to low impedance according to the polarity of the voltage applied between the flexible contacts 171 and 172. This setting at low impedance is carried out by a MOS transistor 186 - the gate of which is subjected to the voltage applied between the flexible contacts 171 and 172. A Zener diode 187 protects the input of MOS transistor 186 overvoltages. Thus, the second circuit 183 makes it possible to modify the direction of communication of the couplers 175.1 and 175.4 as a function of the polarity of the voltage applied between the · flexible contacts 171 and 172. The second circuit 183 · being connected in the same way to the other couplers magnetic and optical, it therefore allows, in the same way, to modify the communication direction of magnetic couplers 175.1 to 175.12 and optical
    17 6.1 to 176.4 depending on the polarity of the voltage applied between the flexible contacts 171 and 172 ·.
    The module 123 also has a connection face 527 to the housing 100 onto which open a first flexible contact 571 and a second flexible contact 572, disposed on either side of a center line 573 of the connection face 527. A third central flexible contact 574 located on the center line 573 also opens on the connection face 527. Rubber visible in FIG. 9, the flexible contacts
    571, 572 and 574 extend in a direction parallel to the center line · 57 3 and the branching face 527 extends parallel to the insertion direction P. The branching face 527 may include air connectors (not shown ) connected to fan 140
    30 · module 123 and electrical connectors for monitoring operation.
    Referring to Figure 10, the establishment of four common modules 124, 224, 324, 424 identical · respectively in four computing units 100, 200, 300 and
    4 00 of a fuselage 1 of an aircraft will be described. Elements identical · or analogous to those of the common module 124 will include a numerical reference · increased respectively by a hundred, two hundred and three hundred to respectively designate the · elements of the common modules 224, 324 and 424. the identical elements or analogous to those of the computing unit 100 will include a numerical reference increased respectively by one hundred, two hundred and three hundred to respectively designate the elements of the computing units
    200, 300 and 400.
    · The calculation units 100 and 200 are respectively located to the right and to the left of a longitudinal direction · L of the fuselage; 1 and have their respective openings · frontal 105 and 205 opening towards the front of the fuselage 1. The calculation units 300 and 400 are, for their part, respectively located on the right and on the left · of a longitudinal direction · L of the fuselage 1 and have their respective front openings · 305 and 405 opening · towards the rear of the fuselage 1,
    The assembly of the common module 124 in the compartment 104 of the unit 100 is done by introducing the insertion end 126 of the common module 124 into the lateral opening 108 oriented towards the central zone 7 of the compartment 104 according to a direction of · introduction P 'perpendicular to the longitudinal direction L, the connection face 127 being oriented towards the front of the fuselage 1. During the translation of the common module 123 · in the: compartment 104 :, the layers of PTEE 168 and 177 respectively of the connection faces 160 and 127 are brought into contact under the effect of the longitudinal springs 170.1 to 170.3 and slide one against the other. As: visible screw: in FIG. 11, the flexible contacts 171, 172 and 174 are pushed back by the connection face 160 when they enter the second auxiliary compartment 104 and slide against the PTEE layer 168 on the face of bran3056964 chement 160 until they are respectively facing conductive pads 161, 162 and 164. In this position, the optical couplers 176.1 to 17 6.4 as well as the magnetic couplers 175.1 to 175.12 of the 5 connection face 127 of the module common 124 face respectively the optical couplers 167.1 to 167.4 and the magnetic couplers 166.1 to 166.12 of the connection face 16 Q of the second auxiliary compartment 104. the layers 168 and 177 also guarantee a controlled distance 10 between the connection faces 160 and 127 The positive pole constituted by the first conductive pad 161 of the electrical supply 165 of the second auxiliary compartment 104 is in electrical contact with the e flexible contact 171 of the common module 124. The pole: héga15 tif constituted: 'by the second conductive pad 162 of the electrical supply 165 of the second auxiliary compartment 104 is, in turn, in electrical contact with the flexible contact / 172 of the common module 124. Thus, the first circuit 181 receives a voltage üni-nn 'measured 20 between the first and second flexible contacts: 171 and 172, positive. The second circuit 182 then passes the magnetic couplers 175.1 to 175.3 and 175.3 to 175.9 as well as the optical couplers: 176.1 and 17 6.3 in “emission” mode and the magnetic couplers / 175.4 to 175.6, 25 175.9 to 17 5.12 and the optical couplers 176.2 and 176.4 in "reception" mode. The removal of the module / common 124 / out of the second auxiliary compartment 104: is done by grasping the end 125 of the common module 12/4 in order to make it translate in the direction RL. During debt 30 translation, the: flexible contacts 131, 172 and 174 are repelled by the connection face 160 and / slide against the PTEE layer 168 · of the connection face
    160 until the complete extraction of the common module 124 ′ out of the second auxiliary compartment 104.
    The assembly of the common module 224 in the compartment 204 of the unit 200 is done by introducing the insertion end 225) of the common module 224 into the lateral opening 208 oriented towards the middle zone 7 of the second · auxiliary compartment 204 in an insertion direction P 'perpendicular to the longitudinal direction L, the connection face 227 being oriented towards the front of the fuselage 1,' In this position, the optical couplers 276.1 to 276-.4 as well as the magnetic couplers 276.1 to 27 6.12 of the connection face 227 of the common module 224 respectively make the optical couplers 267.1 to 267.4 and the magnetic couplers 266.1 to 266.12) of the connection face 260 of the second) auxiliary compartment 20) 4. The positive pole constituted by the first conductive pad 261 of the electrical supply 265 of the second auxiliary compartment 20) 4 is in electrical contact with the flexible contact 271 of the common module 224. The pole; negative formed by the second conductive pad 262 of the electrical supply 265 of the second auxiliary compartment 2) 04 · is, in turn, in electrical contact with the flexible contact 272 of the common module 224. Thus, the first circuit 281 receives a voltage U271-272 / measured between the first and second flexible contacts 271 and 272, positive. The second circuit 282 then switches the magnetic couplers 27.5, .1 to 27 5.3 and 275.7 to 2) 75.9 as well as the optical couplers 276.1 and 276.3 in "emission" mode and the magnetic couplers 275.4 to ; 275.6, 275.10 to 275).) 12 and the optical couplers 27 6.2 and 276.4 in "reception" mode.
    The assembly of the common module 3) 24 in the compartment 304) of the unit 30)) 0 is done by inserting the insertion end 32 6 of the common module 32 4- in the opening- lateral, 368- facing the central region 7 of the second auxiliary compartiinent 304 according to a) direction of introduction 7 P · perpendicular to the longitudinal direction L, the side branch 327 is oriented toward the rear of fuselage 1. in this position, the optical couplers 37 6.1, 376.2, 3-76,3, 37 6.4 as well as the magnetic couplers 37 5.1 to 335.6 and 37 5.7 to 37 5.12 of the connection face 327 of the common module 324 respectively face the optical couplers 367.4, 367.3 , 367.2 and 367.1 and the magnetic couplers 366.12 to 366.7 and 366.6 to 366.1 of the connection face 360 of the second auxiliary compartment 304. The positive blade formed by the first conductive pad 361 of the electrical supply 365 of the second auxiliary compartment 304 is in electrical contact with the flexible contact 372 of the common module 324. The negative pole constituted by the second beach
    65 of. to him, with the flexible contact 372 of the common module 324. Thus, the first circuit 381 receives a voltage 0371-372: / measured between the first and second flexible contacts 371 and 372, negative. The second circuit 382 then passes the magnetic couplers 375.1 to 375.3, 375.7 to 375.9 and the optical couplers · 376.1 and 376.3 · in “reception” mode and the magnetic couplers · 375.4 to 375.6, 375.10 to 37 5.12 and the optical couplers 376.2 and 376.4 in “emission” mode, conductive 362 two! compartment in electrical contact
    The auxiliary power supply 304 is, as for
    The mounting of the common module 424 in the compartment 404 of the unit 406 is done: by introducing the insertion end 42 5 'of the common module 42 4 into the lateral opening 408 oriented towards the zone: median · 7 of the second auxiliary compartment: 404 according to a direction of insertion P 'perpendicular to the longitudinal direction L, the connection face 427 being oriented towards at the rear: of the fuselage 1. in this position, the optical couplers 476.1, 476.2 , 476.3, 476.4 as well as the magnetic couplers 475.1 to 475.6 and 475.7 to
    475.12 of the connection face 427 of the common module 424 respectively face the optical couplers 467.4, 4 67.3, 467.2, 467.1 and the magnetic couplers) 4 66.12 to 4 66 ;. 7 and 466.6 to 466.1 of the connection side 460 of the second auxiliary compartment 404. The positive pole constituted by the first conductive pad 461 of the power supply 465 of the second auxiliary compartment 404 is in electrical contact with the flexible contact 472 of the common module 424. The negative pole constituted by the second conductive pad 462 of the electrical supply 465 of the second auxiliary compartment 404 is, in turn, in electrical contact with the flexible contact 472 of the common module 424. Thus, the first circuit 481 receives a voltage U471-472, measured between · the first and second flexible contacts · 471 and 4 72, negative. The second circuit 482 then passes · the magnetic couplers 475.1, 475.2, 47 5.3 and the optical coupler 476.1 in “reception” mode and the magnetic couplers; 475.4, 475.5, 475.6 and 476.2 in "broadcast 20" mode.
    It will be understood that the arrangement described above of the flexible contacts makes it possible to use common modules 124, 224, 32 4 ·, 424 identical in · the calculation units.
    100, 200, 300 and 400 · since it suffices to reverse the common mo25 düle around its longitudinal axis for the electrical contacts; is either on the left; either right.
    One then obtains a single model of computation unit cooperating with a single type of module and being able to be assembled in four different configurations without modifications. The costs of certification, production, maintenance and installation are thus greatly reduced.
    Elements identical or analogous to those of the calculation unit 100 will include a reference humé3056964 rique increased by four hundred respectively in the following description of a particular embodiment of a calculation unit according to the invention.
    With reference to FIG. 13, the branching face 560 of the second auxiliary housing 504 comprises five conductive tracks 561, 562, 564, 590 and 591. The first conductive pad 561 is connected to a first track of the printed circuit 518 and constitutes a positive pole of an electric power supply 565, the second track con10 duc t rie e 562 is in turn feïié-a second track;
    of the printed circuit 518 and constitutes a negative pole of an electrical supply 565. The central conductive track 564 constitutes a mass of the electrical supply 565. The additional tracks; 590 and 591 which extend symmetrically with respect to the center line 563 are respectively · entry and exit ports · of communication. Magnetic couplers 592.1 to 592.5 also open on the connection face 560. These magnetic couplers extend symmetrically on either side of the center line 563 near a first opening 508 of the compartment 504.
    As visible) in FIG. 14, the printed circuit 518; comprises a metal plate 583 extending over the entire connection surface 560 and on which are fixed the conductive pads 561, 562, 564, 590, 591 as well as the windings of the couplers; magnetic
    592.1 to 592.5. The PTFE 568 layer; covers the plate 593 and includes a reservation directly above the conductive pads; 561, 562, 564, 590 ;, 591. The printed circuit
    518; also comprises cylinders 584.1 to 5 94.5 for shielding the magnetic couplers 592.1 to 592.5 extending close to the face of the; opposite plate 593; at; layer 368 ;.
    As shown in Figures 15 and 16, the connection face 327 of the module; common 524 also includes a metal plate 594 extending over the entire surface 560 and on which flexible contacts 511, 572, 574, 595, 596 are fixed as well as windings of the magnetic couplers /597.1 to 5 / 97.5 . The flexible contacts' · 571, 572, 574, 595, 596 respectively comprise three elastic bridges 571.1 to 571.3,
    572.1 to 572.3, 574.1 to 574.3, 5 35.1 to 595.3, 596.1 to 596.3. The PTFE-577 layer covers the. plate 594 and 'includes a reservation directly above the conductive areas 571, 572, 574, 595, 596. The connection face
    560 also includes cylinders 5 / 98.1 to 5 / 94.5 for shielding the magnetic couplers 5 / 92. / 1 -â 592.5 extending: near: the face of the plate 593 opposite the layer 568.
    When the common module 524 is in place in the second · housing / auxiliary 504 (/ figured 16), the magnetic couplers 597.1 to 597.:5 of the common module 5-24 face the magnetic couplers 5 / 92.1 to 592.5 of the calculation unit 300 /, - thus ensuring magnetic coupling of the unit 500 and the module: 524. The elastic bridges of the contacts: flexible 571, 572, 574, 595 and 5/96 come respectively into contact with the conductive pads 561, / 562 /, / 564, 5/90 and 5/91, ensuring the supply of the Module · common 52/4 by the power supply 565 and the communication of the module: common 524 with the computing unit 500. The metal plates 59/3 and / 594 facing each other / provide efficient / coupling / capacitive ent / ie: the module, common 524 and the calculation unit 500.
    The removal of the / common module 524 out of the second auxiliary compartment / 504 s / é is done by grasping / emitting the end 523 of the common module 5/24 in order to make it translate in the direction P '. During this translation, the bridges of the flexible contacts 371, 372 and
    574 are repelled by the face of / connection 5/60 / and
    35: slide against the PTEE 568 layer of the bran3056964 chemenf 560 face until the common module 524 is completely extracted from the second auxiliary compartment 104 (ligures: 17 to 19.
    The: calculation units 100 are arranged in at least one of the lateral housings 6 in such a way that the direction of insertion I is substantially parallel to the longitudinal direction L of the fuselage 1. It will be noted that the withdrawal of the panel 109 provides direct access to the calculation module 122 closest to the middle zone 7. 10 More precisely, the calculation units 100 are mounted in pairs in adjacent positions in the lateral housings 6 so that the walls of bottom 116 of the boxes 101 extend opposite one another. Cables: 8 of the harness 9 are ame1: 5 born between the two computing units 100: to be connected to these via connectors 115 and 119 ·, which facilitates the connection of the computing units 100 to the 'harness and risk 9,
    It is understood that the arrangement described: above flexible contacts makes it possible to use common modules 123 and 124 identical in the two calculation units 100 since it suffices to refer the common module around its longitudinal axis and the insertion direction so that the electrical contacts are either on the left or on the right.
    The common module 123 will now be detailed. A conduit 11, extending between the fuselage 1 and the computing unit 100,. connects the main pipe 10: closest: to an air intake mounted on the panel 110 to open opposite an opening of the common module 113 opposite which is mounted a first non-return valve 130: .1 arranged for authorize a passage of the air for cooling the duct 11 as far as: the common module 123: and oppose a ci roll of air in s ens op35 posed :. The common module 123 includes an outside air intake 3056964 laughing 120 which opens into the central zone 7 and which is associated with a fan 140 for introducing air into the common module 12-3 and a second non-return valve.
    130.2 designed to allow air to pass from the fan '140 · into the common module 123 and to prevent air circulation in the opposite direction. The common module 123 has an upper wall provided with air exhaust openings towards the pri ne i pa 1 102 compartment.
    The valves 130.1 and 130.2 are similar to each other and here comprise a hollow body · 131, fixed to one of the side walls of the common module 123- and tightly connected to the conduit 11 for the valve 130.1 and to the fan outlet 140 'for valve 130.2. The body 13-1 is provided with a plurality of openings opposite each of which is mounted a flap 132 having a free edge and opposite an edge hinged to the body 131 so that the flap 132 pivots between a closed position and an open position. The shutters 132 are
    -so positioned so that the flaps 132 can be lifted by an air flow going towards the interior of the common module 12 3 so as to let this air flow pass but are pressed -in the closed position by any air flow having an opposite direction. The return means is, for example, a calibrated spring to allow the flaps 132 to be lifted by the air flow entering the common module 123 without causing a pressure drop in · 1-e air flow preventing it ci to browse the common module '123; and the main compartment 102. As a variant, the return means can be gravity. We understand that:
    when the air blowing system of l-'aérôn-ef is in operation, the non-return valve
    130.1 allows air to pass through while the fan 140 is stopped and the non-return valve 130.2 prevents · the passage of air from the non-return valve 130.1;
    when the blowing system; air from the aircraft has failed, the fan 140 is turned on to blow air only; non-return valve 1) 30.2 lets through; that the non-return valve 130.1 prevents the passage of air from the non-return valve 130.2. The activation of the fan 140 e; st controlled via the electrical harness 9 after; failure detection; the blowing system; of air from the aircraft.
    The fan 140 here comprises an impeller; 141 driven, by an electric motor not shown, in rotation in a casing 142 ;. The housing 142 comprises two walls 143; perpendicular to the axis of rotation of the impeller 141 joined by a circular peripheral wall 144 entôürattt the impeller 141 which extends between the walls 143. One of the walls 143; is fixed to the wall of the common module 123 and the other of the walls 143 is provided with orifices 145) d ') air exhaust in the vicinity of the circular peripheral wall 144 while being spaced from the circular peripheral wall 144. The circular peripheral wall 14 4; extends around the impeller 141 and having an extended lower part tangent so much by a vertical tangential corridor 146 au25; what is fixed; a receptacle 14 7. The impeller 141 comprises a hollow hub forming a conduit in communication with; the air intake) 120; in such a way that the rotation of; the impeller 141 tends to entrain the air coming from the air intake 120 towards the orifices 145 of the casing
    142. The dust which may be found in; the air flow are driven by a centrifugal effect against; the circular peripheral wall 144 as far as the vertical tangential corridor 146 and the receptacle 147 where the dust will be trapped ;. Cleaning the réeep35 tackle 147 allows; remove dust.
    Of course, the invention is not limited to the embodiments described but · includes any variant coming within the scope of the invention as defined by the claims.
    In particular, the housing of the computing unit
    100 may have another shape and include a different number of auxiliary compartments or no auxiliary compartment at all.
    Although here the module described is a com10 module provided with calculation modules, the invention also applies to other types of electronic module such as, for example, ventilation modules or dedicated modules, part of the calculation modules or just one of them.
    Although here the supply of the electronic module 15 is done using oblong conductive pads, the intention also applies to other means of electrical supply of the electronic module such as for example circular conductive pads or inductive contactless connectors.
    Although here: the connection faces of the electronic module and of the second auxiliary compartment include a PTFE coating, the invention also applies to other types of reducing coating: friction such as for example PGTFE, FE, HFA or other polymers. The invention also applies to a single connection face - of the electronic module or of the computing unit - which comes out provided / with a coating reducing friction. The coating may extend over the entire connection face or only over a part thereof.
    Although here the second auxiliary compartment has three longitudinal springs /, the invention also applies to other types / of elastic elements / arranged to exert a contacting force against the connection face such as for example / a single longitudinal spring, rubber blades or coil springs.
    Although here the common module is of substantially parallelepiped shape, the invention also applies to modules of different shape such as for example triangular or straight cylindrical modules.
    Although here the electronic module; includes flexible contacts, the invention also applies to other means of connection to an electrical supply such as for example fixed electrical pads, non-contact inductive connectors or conductive brushes.
    Although here the electronic module, like the calculation unit, includes optical couplers and magnetic couplers, the invention also applies to other connection means such as for example conductive pads or radio transceivers or microwave. Magnetic and / or optical connectors are preferred because they allow electrical decoupling of the electronic module and the computing unit.
    Although gu'ici the connection means are distributed; symmetrically with respect to a median axis and a plane orthogonal to this axis, the invention also applies to connection means · distributed differently, it is then required to also invert the common module around an axis perpendicular to its direction of; introduction. In this particular case, the insertion of the common module in; the compartment is always made by the same insertion end. Although here the unit
    3; Q is a calculation unit, the invention also applies to other types of electronic unit such as for example a unit; communication, air conditioning or other.
    As a variant, the common module is designed to as35 provide a single transverse function; and for example a power supply of the calculation modules, a cooling of the calculation modules or an interconnection of the calculation modules.
    As a variant, it is possible to use common modules 5 intended to be used only in one position, either having flexible contacts on the right, or with flexible contacts on the left. In another variant, the common modules have a bottom equipped with a connector and the housing of the computing unit can be equipped with a homologous connector movable to be mounted on the bottom panel of the auxiliary compartments), whatever the direction of mounting of the computing unit in the lateral housing.
    As a variant, other means of ventilation may be used, for example a fan placed behind a filter responsible for preventing the introduction of dust into the common cooling module.
    权利要求:
    Claims (22)
    [1" id="c-fr-0001]
    1. Aircraft comprising a fuselage (1) and calculation units (100) distributed in the fuselage, the fuselage being divided by a floor (2) into an upper volume (3) and a lower volume (4) in which s extend beams (5) supporting the floor and delimiting with the fuselage and the floor two lateral housings (6) which have a substantially triangular cross section and which extend parallel to a longitudinal direction of the fuselage, the calculation units being arranged in the lower volume and each comprising a housing (101) defining a main compartment (102) containing calculation modules (122) insertable into the main compartment in an insertion direction (I) by a first opening (105) thereof ci and connectable to connectors (115) carried by a bottom wall (116) of the main compartment to open into the main compartment opposite the first opening, characterized e n the computing units are arranged in at least one of the lateral housings in such a way that the direction of insertion is substantially parallel to the longitudinal direction of the fuselage.
    [2" id="c-fr-0002]
    2. Aircraft according to claim 1, comprising an air conditioning circuit for the upper volume (3), the air conditioning circuit comprising a pipe (10) for blowing air which extends under the floor (2) in the lateral housings ( 6) of the lower volume (4) and which is connected to a common module (123) for cooling the calculation modules of each calculation unit, the common cooling module being arranged under the calculation modules (122) and in communication with the main compartment (102) and the box (1) comprising an air exhaust vent opening into the main compartment above the calculation modules.
    [3" id="c-fr-0003]
    3. Aircraft according to claim 2, in which the common cooling module (123) is connected to the pipe (10) by a conduit (11) extending between the fuselage (1) and the calculation unit (100) .
    [4" id="c-fr-0004]
    4. Aircraft according to claim 2 or claim 3, wherein the common module (123) comprises a non-return valve (130.1) arranged to allow a passage of cooling air from the duct (11) to the common module and s '' opposing an air flow in the opposite direction, and the common module comprises an outside air intake associated with a fan (140) for introducing air into the common module and with a non-return valve (130, 2) arranged to allow air to pass from the fan to the common module and to oppose air circulation in the opposite direction.
    [5" id="c-fr-0005]
    5. Aircraft according to any one of claims 2 to 4, in which the common module (123) comprises an outside air intake and a fan (140) which is mounted opposite this air intake and which is associated with centrifugal air filtering device.
    [6" id="c-fr-0006]
    6. Aircraft according to claim 5, in which the fan (140) comprises an impeller (141) driven by an electric motor rotating in a casing (142) a circular peripheral wall (144) extended tangentially by a vertical tangential corridor (146) having a lower end to which is fixed a receptacle (147) for collecting dust, the casing comprising an air inlet orifice in the vicinity of the axis of rotation of the wheel and at least one orifice for air outlet in the vicinity of the circular peripheral wall.
    [7" id="c-fr-0007]
    7. Aircraft according to any one of the preceding claims, in which the housing (101) of the computing units (100) delimits an auxiliary compartment (104) receiving a common module (124) which provides a transverse function for the computing modules. (122) and which is inserted into the auxiliary compartment by an opening in an insertion direction perpendicular to the longitudinal direction of the fuselage so that the opening of the auxiliary compartment is oriented towards a middle region of the lower volume (4).
    [8" id="c-fr-0008]
    8. The aircraft as claimed in claim 7, in which the common module (123) is arranged to supply power to the calculation modules (122).
    [9" id="c-fr-0009]
    9. Aircraft according to claim 7, in which the common module (124) is arranged to ensure data transmission with the calculation modules (122).
    [10" id="c-fr-0010]
    10. Aircraft according to claim 7, in which the common module (123) is arranged to provide cooling of the calculation modules (122).
    [11" id="c-fr-0011]
    11. Aircraft according to at least one of claims 7 to 10, in which at least one connector opens on one side of the auxiliary compartment adjacent to the opening of the auxiliary compartment (104) to cooperate with a lateral connector of the common module (124 ) and allow an electrical connection when: inserting the common module into the auxiliary compartment.
    [12" id="c-fr-0012]
    12. Aircraft according to any one of the preceding claims, comprising two calculation units (100) mounted in adjacent positions in the same lateral housing (6), the bottom walls (116) of the housings (101) extending in look at each other.
    [13" id="c-fr-0013]
    13. Aircraft according to any one of the preceding claims, in which the housing (101) has a second access opening to the main compartment (102), the second opening being produced on one side of the housing perpendicular to the first opening.
    [14" id="c-fr-0014]
    14. Aircraft according to any one of the preceding claims, in which one of the electro3056964 modules (124, 224, 324, 424) is arranged in two directions opposite to each other in an insertion direction. (P ') in the compartment, the compartment comprising power supply means (125, 225, 325, 425) of the electronic module (124, 224, 324, 424) and connection means (166.1-166.12, 167.1- 167.4) from the electronic unit (100, 200, 300, 400) to the electronic module (124, 224, 324, 424), these means opening onto a connection face (160) belonging to the reception compartment (104, 204, 304, 404) extending parallel to the direction of introduction (P ').
    [15" id="c-fr-0015]
    15. The aircraft as claimed in claim 14, in which the supply means (125, 225, 325, 425) comprise a first conductive pad (161, 261, 361,
    461) and a second conductive pad (162, 262, 362,
    462) arranged on either side of a center line (163) of the branch face (160, 260, 360, 460), one of the first and second conductive pads (161, 261, 361, 461) being the positive pole of the electrical supply of the electronic module, the other of the first and second conductive pads (162, 262, 362, 462) being the negative pole of the electrical supply of the electronic module.
    [16" id="c-fr-0016]
    16. Aircraft according to claim 15, in which the conductive pads (161, 261, 361, 461, 162, 262, 362, 462) extend in a direction parallel to the center line (163).
    [17" id="c-fr-0017]
    17. Aircraft according to any one of claims 14 to 16, in which the branching face (160, 260, 360, 460) at least partially comprises a coating reducing friction (168).
    [18" id="c-fr-0018]
    18. Aircraft according to any one of claims 14 to 17, in which the connection means (166.1-166.12, 167.1-167.4) of the electronic module to the electronic unit comprise at least one ma3056964 gnetic coupler (166.1-166.12).
    [19" id="c-fr-0019]
    19. Aircraft according to any one of claims 14 to 18, in which the connection means 166.1166.12, 167.1-167.4) of the electronic module to the electronic unit comprise at least one optical coupler (167.1-167.4).
    [20" id="c-fr-0020]
    20. Aircraft according to any one of claims 14 to 19, in which one face of the compartment opposite to the branching face comprises at least one elastic element (170.1-170.3) arranged to exert a contacting force against the face of connection (160, 260, 360, 460).
    [21" id="c-fr-0021]
    21. Aircraft according to any one of the preceding claims, in which at least one of the calculation modules comprises pins (151) intended to be engaged in metallized holes (152) of a printed circuit board (118), the printed circuit board (118) being covered with a layer of electrically insulating flexible material (153) which is pierced by the pins (151) when these are engaged in the metallized holes (152) and is clamped between a support ( 150) of the pins and the printed circuit board (118).
    [22" id="c-fr-0022]
    22. Aircraft according to the preceding claim, in which the electrically insulating material is a silicone and more particularly a silicone which can be vulcanized at room temperature.
    1/9
    130.1 130.2 140
    2/9
    107 103
    131 132 131
    3/9
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    同族专利:
    公开号 | 公开日
    EP3520586A1|2019-08-07|
    FR3056964B1|2021-10-08|
    CN109792851B|2021-06-11|
    US20190239380A1|2019-08-01|
    CN109792851A|2019-05-21|
    WO2018060392A1|2018-04-05|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US20060082970A1|2004-10-19|2006-04-20|Walz Andrew A|Electrical module and support therefor with integrated cooling|
    FR2974682A1|2011-04-26|2012-11-02|Airbus Operations Sas|ELECTRIC DISTRIBUTION HEART AND VEHICLE COMPRISING SUCH A HEART|
    WO2014198957A1|2013-06-15|2014-12-18|Latelec|Method for integrating a detachable interconnection module in a cabinet, cabinet thus fitted, and aircraft comprising a bay consisting of such cabinets|
    JP3298738B2|1994-05-19|2002-07-08|富士通株式会社|Communication device|
    FR2927222B1|2008-02-05|2010-10-15|Thales Sa|ARRANGEMENT OF AVIONIC RACK|
    CN203851408U|2014-04-29|2014-09-24|晋锋科技股份有限公司|Heat dissipating module with turbo fan|
    FR3028133B1|2014-11-04|2018-02-16|Safran Electrical & Power|AVIONIC BAY|
    CN105836145B|2015-01-14|2018-08-10|空客直升机|The rotor craft of fuel tank with hanging below fuselage load-bearing middle layer|FR3057112B1|2016-09-30|2018-11-02|Safran Electronics & Defense|ELECTRONIC UNIT WITH INVERSE MODULES|
    CN110636741A|2018-06-22|2019-12-31|世倍特集团有限责任公司|Device having a housing and power electronics arranged therein on the bottom of the housing|
    DE102019207971A1|2019-05-29|2020-12-03|Robert Bosch Gmbh|Electronic unit for a hand machine tool|
    CN112492846B|2020-11-27|2021-12-10|中国商用飞机有限责任公司|Aircraft electronic equipment cabin ventilation system|
    法律状态:
    2017-08-21| PLFP| Fee payment|Year of fee payment: 2 |
    2018-04-06| PLSC| Publication of the preliminary search report|Effective date: 20180406 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 3 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 4 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1659469|2016-09-30|
    FR1659469A|FR3056964B1|2016-09-30|2016-09-30|AIRCRAFT WITH COMPUTERS DISTRIBUTED IN THE FUSELAGE|FR1659469A| FR3056964B1|2016-09-30|2016-09-30|AIRCRAFT WITH COMPUTERS DISTRIBUTED IN THE FUSELAGE|
    PCT/EP2017/074726| WO2018060392A1|2016-09-30|2017-09-28|Aircraft having computers distributed in the fuselage|
    US16/338,358| US20190239380A1|2016-09-30|2017-09-28|Aircraft having computers distributed in the fuselage|
    EP17777048.4A| EP3520586A1|2016-09-30|2017-09-28|Aircraft having computers distributed in the fuselage|
    CN201780060154.1A| CN109792851B|2016-09-30|2017-09-28|Aircraft with computers distributed in the fuselage|
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