Electronic module for aircraft embedded system

Abstract

This description relates to an aircraft electronic module (22) comprising: - a housing (220) defining a cavity; - an electronic component (60) housed in the cavity, the electronic component (60) comprising a face (61) having conductive tracks (62); and - a capsule (40) fixed to the housing, the capsule (40) comprising a support and a deformable conductive element mounted in the support, the deformable conductive element (42) being electrically connected to the conductive tracks (62), and the rigid support comprising mechanical mounting means with an additional module (23) comprising additional conductive tracks (52) such that a connection of the support with the additional module (23) has the effect of deforming the deformable conductive element (62) and electrically connecting the conductive tracks (62) to the additional conductive tracks (52). FIG. 4

Description

Title of the invention: Electronic module for an aircraft embedded system. Technical field

[0001] The present presentation relates to embedded systems for an aircraft, in particular modules. STATE OF THE ART

[0002] For reasons of space, some embedded systems are obtained by inserting electronic components into a small package, which is particularly the case for aircraft embedded systems. Reference may be made to French patent FR 3 080 509, which illustrates an example of such an embedded system.

[0003] However, these systems are not suitable for modular assembly. Indeed, once disassembled, they cannot be easily reassembled, either electrically or mechanically. This makes maintenance operations difficult. Replacing or even adding electronic components, for example to acquire different aircraft data, is also difficult. Furthermore, the stacked electronic components can rotate relative to one another, causing premature wear of the conductive tracks of the components in contact with each other in the stack.

[0004] Furthermore, these systems are not suitable for installation in a harsh environment such as an aircraft. Indeed, certain gaps in the stacking are not sufficiently reduced and can cause damage to the onboard system in the event of vibrations or shocks. GENERAL STATEMENT

[0005] One aim of this presentation is therefore to improve the assembly of modular systems, for example, aircraft embedded systems, in order to better withstand harsh environments such as those found in aircraft. Secondarily, an objective of this presentation is to improve the modularity of these systems, particularly with regard to accessibility and maintenance.

[0006] To this end, according to a first aspect of this presentation, an aircraft electronic module is proposed comprising: - a casing delimiting a cavity; - an electronic component housed in the cavity, the electronic component comprising a face with conductive tracks; and - a capsule fixed to the housing, the capsule comprising a support and a deformable conductive element mounted in the support, the deformable conductive element being electrically connected to the conductive tracks and the rigid support including mechanical mounting means with an additional module including additional conductive tracks such that a connection of the support with the additional module has the effect of deforming the deformable conductive element and electrically connecting the conductive tracks to the additional conductive tracks.

[0007] Some preferred but non-limiting features of the electronic module according to the first aspect are the following, taken individually or in combination: • The capsule is mounted in a free end of the housing. • the deformable conductive element comprises a deformable pad in which conductive wires are embedded, said conductive wires having a first end electrically connected to the conductive tracks and a second end configured to be electrically connected to the additional conductive tracks; • the mechanical mounting means of the support include protrusions configured to cooperate with complementary recesses of the additional module; • the electronic module further includes threads mounted on an external face of the module and configured to cooperate with a ring so as to lock the additional module relative to the module; • The electronic module also includes a keying feature configured to position the module relative to the additional module; and / or • the housing further includes an additional capsule fixed to the housing opposite the capsule, the additional capsule comprising a support and a deformable conductive element mounted in the support, the deformable conductive element being electrically connected to the conductive tracks and the rigid support comprising mechanical mounting means with a second additional module comprising additional second conductive tracks such that a connection of the support with the second additional module has the effect of deforming the deformable conductive element and electrically connecting the conductive tracks to the additional second conductive tracks.

[0008] According to a second aspect, an aircraft data acquisition device is proposed comprising: - an electronic module according to the first aspect; and - an additional electronic module comprising an additional support including complementary mechanical mounting means for the support and additional conductive tracks, so that a connection of the support of the electronic module with the additional support of the additional module has the effect of deforming the conductive element and electrically connecting the conductive tracks of the electronic module to the additional conductive tracks of the additional electronic module.

[0009] Some preferred but non-limiting features of the data acquisition device according to the second aspect are the following, taken individually or in combination: • The data acquisition device further includes means for locking the electronic module relative to the additional electronic module; and / or • the electronic module includes threads extending from an external face of the module and the additional electronic module includes a stop extending from an external face of the additional module, the locking means including a threaded ring mounted configured to cooperate with the thread and the stop so as to lock the additional module relative to the module.

[0010] According to a third aspect, an aircraft onboard system is proposed comprising: - a data acquisition device according to the second aspect; and - a sensor electrically connected to the electronic component of the electronic module DESCRIPTION OF THE FIGURES

[0011] Other features, purposes and advantages will become apparent from the following description, which is purely illustrative and not limiting, and which should be read in conjunction with the accompanying drawings on which:

[0012] [Fig.1] [Fig.1] illustrates an aircraft;

[0013] [Fig.2] [Fig.2] illustrates an instrumented aircraft turbomachine;

[0014] [Fig.3] [Fig.3] illustrates a data acquisition device of a system embedded;

[0015] [Fig.4] [Fig.4] illustrates an exploded view of the acquisition device;

[0016] [Fig.5a]

[0017] [Fig. 5b] [Fig. 5a] illustrates one face of an electronic component of a module electronics and [Fig.5b] illustrates an electronic module including the electronic component shown in [Fig.5a];

[0018] [Fig.6a]

[0019] [Fig. 6b] [Fig. 6a] illustrates another example of an electronic module and [Fig. 6b] is an exploded view of [Fig.6a];

[0020] [Fig.7a]

[0021] [Fig. 7b] [Fig. 7a] illustrates one face of an electronic component of the module electronics of figures 6a and 6b and [Fig.7b] illustrates the electronic module with the visible electronic component;

[0022] [Fig.8a]

[0023] [Fig.8b] [Fig.8a] illustrates a capsule and [Fig.8b] is an exploded view of [Fig.8a];

[0024] [Fig.9a]

[0025] [Fig.9b] [Fig.9a] illustrates a cross-sectional view of the ring of the acquisition device and [Fig.9b] is a partial cross-sectional view of the acquisition device. DETAILED DESCRIPTION

[0026] An aircraft 1 is a device configured to rise and move through the air, and may, for example, be a civil or military airplane, or even a helicopter or an airship. According to an example in [Fig. 1] illustrating an aircraft 1 in the case of an airplane, the aircraft 1 comprises an airframe 11 consisting of a fuselage, wings, tail assemblies, control surfaces, and landing gear. The aircraft 1 further comprises a propulsion system 10 to provide it with the thrust necessary for its rise and movement through the air. Of course, the aircraft 1 may comprise a plurality of propulsion systems 10, for example, one propulsion system 10 per wing, as illustrated by way of example in [Fig. 1].

[0027] A turbomachine 10 has a main direction extending along a longitudinal axis X and typically comprises, from upstream to downstream in the direction of gas flow, a fan 102, a primary casing having a compression section that may include a low-pressure compressor 103 and a high-pressure compressor 104, a combustion chamber 105, and a turbine section that may include a high-pressure turbine 106 and a low-pressure turbine 107. In one embodiment, the fan 102 may be shrouded and housed in a retaining casing and includes a nacelle 101 defining an aerodynamic envelope of the engine. Alternatively, the fan may be unshrouded. The airflow entering the turbomachine 10 splits into a primary flow configured to pass through the primary casing and a secondary flow that bypasses the primary casing and is compressed by the fan 102.

[0028] In addition, the turbomachine 10 can be enclosed and comprise more than two bodies.

[0029] The high-pressure turbine 106 is configured to drive the high-pressure compressor 104 via a high-pressure shaft 109.

[0030] The low-pressure turbine 107 is configured to drive the low-pressure compressor 103 via a low-pressure shaft 108. The turbine low pressure 107 also drives the blower 102, either directly or via a reduction mechanism which may include an epicyclic gear reducer, for example of the epicyclic type ('planetary' in English) or of the planetary type ('star' in English), which is interposed between the low pressure shaft 108 and a blower drive shaft.

[0031] The turbomachine includes a sensor 30, typically a speed sensor connected to one of the high-pressure shafts 109 or low-pressure shafts 108 configured to measure the rotational speed of the shaft 108, 109. Other sensors 30 may be connected to the turbomachine, including another speed sensor for the high-pressure shaft 109 or low-pressure shaft 108 that is not already instrumented. If the sensor 30 includes a speed sensor, the sensor may be a tachometer generator or an incremental encoder.

[0032] An electrical harness 31 electrically connects the sensor 30 to a data acquisition device 20. The harness, the sensor and the acquisition device form an on-board system 200 of the aircraft 1.

[0033] The data acquisition device 20 comprises two electronic modules 21, 22 mechanically and electrically connected. An example of such a device is illustrated in [Fig. 3]. In this example, the acquisition device is mounted in the aircraft 1 using flanges 24, for example hose clamps, typically mounted on a turbomachine, and the modules are inserted into the flanges.

[0034] The electronic modules 21, 22 can, for example, be respectively an electronic measurement module configured to collect data from the sensor and an electronic control module configured to process the data from the electronic measurement module, for example for sending the data obtained by the electronic measurement module to the aircraft network or to a control tower.

[0035] The electronic modules 21, 22 each comprise a housing 210, 220 defining a cavity. The modules may have a generally cylindrical shape adapted to reduce the overall size of the device, for example, a cylindrical shape of revolution (tubular). In what follows, the invention will be described assuming the modules are tubular for the sake of simplicity. However, the modules 21, 22 may have any other suitable shape, particularly depending on the available space in their area of ​​use.

[0036] One of the modules 21, 22 comprises threads extending over an external face of the housings 210, 220. The other module 21, 22 comprises a stop extending over an external face of the housing 210, 220. It may be provided that each of the modules 21, 22 comprises threads extending over the external face of the housings 210, 220. A threaded ring 23 cooperates with the stop and / or the threads of the modules so as to lock the modules 21, 22 relative to each other when assembled and unlocking them when separating the modules.

[0037] Each module 21, 22 further comprises an electronic component 50, 60 housed in the cavity. The electronic component 50, 60 of each module 21, 22 has a generally tubular support comprising a face 51, 61 having conductive tracks 52, 62. The conductive tracks 52 of the face 51 of a first 21 of the modules 21, 22 are configured to be electrically connected with the conductive tracks 62 of the face 61 of a second 22 of the modules 21, 22, for example by contact, when the modules 21, 22 are assembled.

[0038] The first electronic component 50 is pressed into the cavity of the housing so as to extend a distance from the free end of the housing. The face 51 of the first electronic component 50 is substantially perpendicular to the axis of revolution of the housing. The inner surface of the housing 211 also has grooves 212 configured to receive tabs 54 of the first electronic component 50, which extend radially from the support of the electronic component 50. The inner surface of the housing 211 therefore comprises as many grooves 212 as the support of the first electronic component has tabs 54, for example, three. The first electronic component 50 is inserted into the housing 210 along the cylindrical surface 211 until the tabs 54 of the first electronic component 50 abut against the grooves 212.Thus, the first electronic component 50 is positioned in the housing 210 of the first electronic module 21 and is prevented from rotating by the complementary shape of the lugs 54 with the grooves 212. In this configuration, the first electronic component 50 is generally centered with respect to the axis of revolution of the housing. A ring 53 is also inserted into the housing 210 and placed against the face 1 of the first electronic component 50, for example by means of screws passing through the ring 53 and bearing against the housing 210 or by screwing the ring 53 onto a thread formed on the surface 211. Thus, the ring 53 acts as an axial stop for the first electronic component 50 so that the first electronic component 50 is held in the housing in an axial position by the ring 53 and prevented from rotating by the lugs 54.

[0039] The housing 220 of the second electronic module 22, an example of which is illustrated in Figures 6a, 6b, and 7b, has a generally tubular internal surface. The internal surface of the housing 220 also has at least one projecting rib 221 configured to receive a groove formed in a slice of the support for the second electronic component 60. The internal surface of the housing 221 therefore comprises as many ribs 221 as the support for the second electronic component 60 has grooves, for example, one. The second electronic component 60 is inserted into the housing 220 of the second electronic module 22 along its surface internal and is prevented from rotating by the complementary shape of the rib 211 with the groove. In addition, the groove acts as a mechanical keying device to prevent a reversal of polarities between face 51 of the first electronic component 50 and face 61 of the second electronic component 60, which is electrically connected to face 51 of the first electronic component 50, when the modules 21, 22 are assembled.

[0040] The second electronic module 22 further comprises a capsule 40 fixed to the housing 220 of the second electronic module 22. The capsule can, for example, be press-fitted onto a free end of the housing 220 until it abuts against the face 61 of the second electronic component 60. The capsule 40 then forms a translational stop for the second electronic component 60, which allows the second electronic module 22 to be handled without risk of the second electronic component 60 coming out of the housing 220, particularly when the second electronic module 22 is detached from the first electronic module 21. The press-fitting also forms a removable assembly of the capsule 40 with the housing 220 of the second electronic module 22, which allows the second electronic component 60 to be easily replaced inside, for example, for maintenance of the second electronic module 22.

[0041] The capsule 40, illustrated by way of example in Figures 6a, 6b and 8a, 8b, comprises a rigid support, illustrated in detail in an example in Figures 8a and 8b, having a base 410 and a projection 411 extending from the base 410 so as to form an additional thickness. At least one groove, complementary in shape to the shape of the rib(s) 221, is formed in a slice of the capsule so as to guide the positioning of the capsule 40 relative to the face 62 of the second electronic component 60. The capsule 40 comprises as many grooves as the housing comprises ribs 221.

[0042] The second electronic module 22 is mounted on the first electronic module 41 by complementary shape of the protrusion with the cylindrical surface 211 of the second module 22 (see the annotated drawing P in [Fig. 9b]). The protrusion 411 is configured to fit into the cavity so as to contact the face 51 of the first electronic component 50, while the base 41 contacts the ring 53.

[0043] The support 41 further comprises serrated orifices 412 forming teeth 413 extending laterally from the orifice 412 (see, for example, [Fig. 8b]). Each orifice 412 is configured to receive a deformable conductive element 42, the teeth 413 being configured to retain the deformable conductive element 42 in the orifice 412 by friction.

[0044] The capsule 40 further comprises deformable conductive elements 42 inserted into the orifices 412 of the support 4L. The deformable conductive elements 42 are then mounted in the orifices 412 of the support 40 and are held in place by the teeth 413 of the orifices 412. Thus the deformable conductive elements 42 can be easily replaced, for example in case of maintenance.

[0045] In one embodiment, the deformable conductive elements 42 each comprise a pad 422 in which conductive wires 423 are embedded. The pad 422 is then pressed into the holes 412 and held in position by the teeth 413. The pad 422 is made of a deformable material, for example, deformable by 15%, or even up to 30%, between a rest position and a deformed position of the pad 422, typically an elastomer. The conductive wires 423 have a first end 424 configured to be electrically connected to the conductive tracks 52 of the face 51 of the first electronic component 50 and a second end 425 configured to be electrically connected to the conductive tracks 62 of the face 61 of the second electronic component 60. The conductive wires 423 are preferably substantially straight between their ends.

[0046] Each pad 422 protrudes slightly on either side of the orifice 412, for example less than one millimeter, on each side of the orifice 412. Thus, when the ring 43 is tightened, the pads 422 and the conductive wires 423 of each deformable conductive element 42 deform upon contact with the face 51 of the first electronic component 50 and the face 61 of the second electronic component 60. The face 51 of the first electronic component 50 and the face 61 of the second electronic component 60 in contact with the pads 422 each apply an additional stress in the assembly, which has the effect of reducing the play in the assembly and thus makes the data acquisition device 20 more robust to disturbances in the equipment's environment, typically in the aircraft 1, such as shocks or vibrations.Furthermore, by deforming, the pads 422 block the rotation of the first and second electronic components 50, 60 by friction of pads 422 on the faces 51,61 of the first and second electronic components 50, 60, which prevents premature wear of the conductive tracks 52, 62 of the faces 51,61 of the first and second electronic components 50, 60.

[0047] The deformable conductive elements 42 inserted into the support 40 may, in particular, be of the "JTA" type, a standard known to those skilled in the art and commonly available commercially. Thus, the capsule 40 has a standardized electrical connection interface; the capsule 40 is therefore "universal," that is to say, suitable for any type of electrical connection without requiring a unique design of the second electronic module 22 for each type of electrical connection envisaged in the aircraft 1.

[0048] According to one variant, the acquisition device may be provided to include a third module interposed between the two modules 21, 22, in particular to supply the two modules with a battery housed in the third module.

[0049] From then on, the two modules 21, 22 have an architecture similar to that of the first module 21 and the third module to that of the second module 22. The third module further includes an additional capsule similar to the capsule 40 previously described fixed in an additional free end of the housing of the third module similar to the free end of the housing 220 of the second module 42 and opposite to the free end of the third module.

[0050] Of course, this description can be applied to other harsh environments than that of an aircraft without departing from the scope of this application.

Claims

Demands

1. Aircraft electronic module (22) comprising: - a housing (220) delimiting a cavity; - an electronic component (60) housed in the cavity, the electronic component (60) comprising a face (61) having conductive tracks (62); and - a capsule (40) fixed to the housing, the capsule (40) comprising a support and a deformable conductive element mounted in the support, the deformable conductive element (42) being electrically connected to the conductive tracks (62) and the rigid support comprising mechanical mounting means with an additional module (23) comprising additional conductive tracks (52) such that a connection of the support with the additional module (23) has the effect of deforming the deformable conductive element (62) and electrically connecting the conductive tracks (62) to the additional conductive tracks (52).

2. Electronic module (22) according to claim 1 in which the capsule (40) is mounted in a free end of the housing (220).

3. Electronic module according to any one of claims 1 and 2, wherein the deformable conductive element (42) comprises a deformable pad (422) in which conductive wires (423) are embedded, said conductive wires having a first end electrically connected to the conductive tracks (62) and a second end configured to be electrically connected to the additional conductive tracks (52).

4. Electronic module according to any one of claims 1 to 3, wherein the mechanical mounting means of the support include protrusions (54, 211) configured to cooperate with complementary recesses (221) of the additional module (23).

5. Electronic module according to any one of claims 1 to 4, further comprising threads mounted on an external face of the module and configured to cooperate with a ring so as to lock the additional module (23) relative to the module.

6. Electronic module according to any one of claims 1 to 5, further comprising a keying device (221) configured to position the module relative to the additional module (23).

7. Electronic module (22) according to any one of claims 1 to 6, wherein the housing (220) further comprises an additional capsule (40) fixed to the housing opposite the capsule (40), the additional capsule (40) comprising a support and a deformable conductive element mounted in the support, the deformable conductive element (42) being electrically connected to the conductive tracks (62) and the rigid support comprising mechanical mounting means with a second additional module (23) comprising additional second conductive tracks (52) such that a connection of the support with the second additional module (23) has the effect of deforming the deformable conductive element (42) and electrically connecting the conductive tracks (62) to the additional second conductive tracks (52).

8. Aircraft data acquisition device (20) comprising: - an electronic module (22) according to any one of claims 1 to 7; and - an additional electronic module (21) comprising an additional support comprising mechanical mounting means complementary to the mechanical mounting means of the support and additional conductive tracks (52), such that a connection of the support of the electronic module (22) with the additional support of the additional module (21) has the effect of deforming the conductive element and electrically connecting the conductive tracks (62) of the electronic module to the additional conductive tracks (52) of the additional electronic module.

9. Data acquisition device (20) according to claim 8, further comprising means for blocking (23) the electronic module with respect to the additional electronic module.

10. Aircraft embedded system (200) comprising: - a data acquisition device (20) according to one of claims 8 and 9; and - a sensor (30) electrically connected to the electronic component of the electronic module (22).

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