FR3040582A1 - AVIONIC CALCULATOR AND MOUNTING METHOD - Google Patents

Abstract

The avionics calculator comprises a set of electronic cards including: a row of cards (6) arranged parallel to one another, the card row comprising at least a first card (10) and at least a second card (12), a card interconnection (14) for connecting the cards of the rows of cards together, and an aircraft connecting board (16) for connecting the computer to the avionics system of an aircraft. Each first board (10) is plugged only on the interconnect board (14) among the interconnect board (14) and the aircraft board (16), and each second board (12) is plugged by an edge ( 12A) on the interconnection board and by another edge (12B) on the aircraft connection board (16).

Description

AVIONIC CALCULATOR AND MOUNTING METHOD

The present invention relates to the field of avionics calculators embedded in aircraft and intended to be integrated into an avionics system.

An avionics calculator includes a set of electronic boards received in a computer case.

It is possible to provide an avionics calculator comprising a plurality of computer cards plugged into an interconnection card allowing a signal exchange between the computer cards and carrying an aircraft connector for connecting the computer to the avionics system of the aircraft. The aircraft connector is for example compliant with the ARINC600 standard so that the avionics computer meets this standard. Nevertheless, in view of the presence of pins of the aircraft connector passing through the interconnection card, the computation cards can not be plugged on the interconnection card to the right of the aircraft connector and are plugged on the interconnection card on the part and other aircraft connector. Inside the computer housing, a space located opposite the aircraft connector remains unused at the expense of the compactness of the avionics computer and its lightness.

It is possible to provide an aircraft connection card parallel to the interconnection card and plugged on the interconnection card on the opposite side to the calculation cards, the aircraft connector card carrying the aircraft connector. The interconnection card is then devoid of aircraft connector. This makes it possible to insert calculation cards on the interconnection card opposite the aircraft connector of the aircraft connection card. Nevertheless, the presence of an aircraft connection card and an interconnection card side-by-side limits the remaining available length for the computation cards inside the computer case.

In addition, depending on the number of computer cards plugged into the interconnection card, it may be difficult to provide protection devices against electromagnetic interference and protection against electromagnetic interference on the interconnection card. It is then necessary to provide these protection devices against lightning and protection against electromagnetic interference on the computer boards, which complicates the design of the avionics computer.

One of the aims of the present invention is to provide an avionics calculator that can be compact while facilitating the design of the avionics calculator. For this purpose, the invention proposes an avionics calculator comprising a set of electronic cards including: a row of cards arranged parallel to one another, the row of cards comprising at least a first card and at least a second card, an interconnection card for connecting the cards of the rows of cards together, and an aircraft connection card for connecting the computer to the avionics system of an aircraft, in which each first card is inserted only on the interconnection card among the interconnection card and the aircraft connection board, and each second board is plugged by an edge on the interconnection board and by another edge on the aircraft connection board.

The avionics computer optionally comprises one or more of the following characteristics, taken separately or in any technically possible combination: the aircraft connection board carries an aircraft connector, preferably complying with the ARINC 600 standard; - a second card is located at one end of the card row; it comprises two second cards arranged at both ends of the main card row; - he understands exactly two second cards; at least one second card has a protection device for lightning protection and / or protection against electromagnetic interference; two adjacent cards in the row each have, on their faces facing each other, a wide connector and a narrow connector, the wide connector of each of the two cards being opposite the narrow connector of the other among the two cards; it comprises a computer box in which the set of electronic cards is received, the interconnection card being arranged along a face of the computer box accessible when the computer is installed under the operational conditions in the aircraft; and - it comprises a computer box in which the set of electronic cards is received, the computer box having a front face and an opposite rear face, the interconnection card being arranged along the front face, the card of aircraft connection being arranged along the rear face, the rear face being removable and / or the front face is irremovable. The invention also relates to a method of mounting an avionics computer as defined above, comprising the steps of mounting the interconnection card in a computer box, plug each first card and each second on the interconnection card , then insert the aircraft connection card on each second main board. The invention and its advantages will be better understood on reading the following description, given solely by way of nonlimiting example, and with reference to the appended drawings, in which: FIG. 1 is a diagrammatic view of an avionics calculator; FIG. 2 is a schematic perspective view of a set of electronic boards of the avionics computer of FIG. 1; 3 is a diagrammatic view of the avionic calculator of FIGS. 1 and 2 according to FIG. 2; - Figure 4 is a view similar to that of Figure 1 illustrating the avionics computer in a maintenance configuration; - Figure 5 is a schematic perspective view of a set of electronic cards of a avionics computer according to a variant.

The avionics computer 2 of FIGS. 1 and 2 comprises a computer box 4 (FIG. 1) and a set of electronic cards 6 received inside the computer box 4.

In the rest of the description, the terms "card" and "electronic card" are used as synonyms. In addition, a card "plugged" on another is a card carrying a connector engaged with a complementary connector carried by the other card. In addition, a card is plugged "by an edge" on another card when this card is inserted on the other card with a connector disposed on this board. The set of cards 6 comprises a row of cards 8 arranged parallel to each other and side by side. The row of cards 8 comprises at least a first card 10 and at least a second card 12. The set of cards 6 comprises an interconnection card 14 on which are inserted each first card 10 and each second card 12. The card interconnection is configured for the exchange of signals between the first (s) and second (s) cards 10, 12 plugged on this interconnection card 14. The set of cards 6 includes an aircraft connection card 16 to connect the avionics computer 2 to an avionics system of an aircraft. The aircraft connection board 16 carries at least one aircraft connector 18 for connecting the computer to the avionics system of an aircraft. Each aircraft connector 18 is for example compliant with the ARINC600 standard.

Each first card 10 is inserted only on the interconnection card 14 among the interconnection card 14 and the aircraft connection card 16. Each first card 10 is plugged on the interconnection card 14 without being plugged on the connection card aircraft 16.

Each first card 10 is plugged by one of its edges 10A on the interconnection card 14. The edge 10A of each first card 10 is adjacent to the interconnection card 14.

Each first card 10 carries on its edge 10A at least a first connector 20A, 20B engaged with a first complementary connector 22A, 22B carried by the interconnection card 14.

Each second card 12 is plugged by one of its edges 12A on the interconnection card 16 and by another of its edges 12B on the aircraft connection card 16.

The edges 12A and 12B of each second card 12 are distinct. The edge 12A of each second card 12 is adjacent to the interconnection card 14 and the edge 12B of each second card 12 is adjacent to the aircraft connection card 16.

Each second card 12 carries on its edge 12A at least one first connector 20 engaged with a first complementary connector 22 carried by the interconnection card 14, and on its other edge 12B at least one connector.

Each second card 12 carries on its edge 12B at least a second connector 24 engaged with a second complementary connector 26 carried by the aircraft connection card 16.

Each second card 12 is provided to ensure a signal exchange between the interconnection card 14 and the aircraft connection card 16.

A signal received by the avionics computer 2 and intended for a first card 10 passes successively through the aircraft connection card 16, by a second card 12 and by the interconnection card 14 to reach the first card 10 receiving the signal. Each signal received by the avionics computer 2 is conveyed from the aircraft connection card 16 to a first signal destination card via a second card 12 and the interconnection card 14.

Similarly, a signal transmitted by a first card 10 to the outside of the avionics computer 2 passes successively through the interconnection card 14, by a second card 12 and by the aircraft connection card 16. Each signal transmitted by a first board 10 to the outside of the avionics computer 2 is conveyed to the aircraft connection board 16 via the interconnection board 14 and a second board 12.

Preferably, the first boards 10 are the main boards (or calculation boards) of the avionics calculator 2 and are configured to perform the calculation functions of the avionics calculator 2, and the second boards 12 are auxiliary boards configured to perform auxiliary functions useful to the main maps.

This makes it possible to preserve the space of the first boards 10 for the hardware components for carrying out the calculation functions, and to place the hardware components for carrying out the auxiliary functions on the second boards 12, by rationalizing the design of the avionics calculator 2 and preserving its compactness and lightness.

Advantageously, the auxiliary functions are communalised for the first cards 10. Thus, a second card 12 performs an auxiliary function for several first cards 10.

Advantageously, each second card 12 comprises a protection device 30 for lightning protection and / or protection against electromagnetic interference, capable of processing a signal received by the avionics computer 2 and intended for at least a first card 10 before the transmission of this signal to the interconnection card 14 and to a first recipient card.

It is possible to provide other auxiliary functions common to the first cards 10 and made by the second cards 12. It is possible, for example, to have, on the second cards 12, common input / output (I / O) stages. to the first cards 10.

The second cards 12 arranged parallel to the first cards 10 and ensuring the exchange of signals between the aircraft connection card 16 and the interconnection card 14, have dimensions comparable to those of the first cards 10, which facilitates the installation of the components performing the auxiliary functions.

As illustrated in FIGS. 1 and 2, the edges 12A, 12B of each second card 12 by which this second card 12 is respectively inserted on the interconnection card 14 and the aircraft connection card 16, are two opposite edges of FIG. this second card 12.

The interconnection card 14 and the aircraft connection card 16 are here parallel to each other. The interconnection card 14 and the aircraft connection card 16 are spaced apart, and the first cards 10 and the second cards 12 are received between the interconnection card 14 and the aircraft connection card 16. The interconnection card 14 and the aircraft connection card 16 delimit between them a space in which are received the first cards 10 and the second cards 12.

The first cards 10 and the second cards 12 are perpendicular to the interconnection card 14 and the aircraft connection card 16. The first cards 10 and the second cards 12 extend transversely between the interconnection card 14 and the card. aircraft connection 16.

The interconnection card 14 extends along a front face 4A of the computer casing 4, being adjacent and parallel to this front face 4A, and the aircraft connection card extends along a rear face. 4B of the computer housing 4, being adjacent and parallel to this rear face 4B.

The rear face 4B has an opening 29 for engaging the aircraft connector 18 with a complementary connector of the aircraft through this opening 29.

Preferably, at least one of the front face 4A and the rear face 4B is removable to allow the cards to be mounted inside the computer housing 4.

In one embodiment, the rear face 4B is removable for mounting the cards inside the computer housing 4. The front face 4A is then removable or irremovable.

The first and second cards 10, 12 are shown on the interconnection card 14 in a first direction D1. The first direction D1 is perpendicular to the interconnection card 14.

The second cards 12 are displayed on the aircraft connection card 16 in a second direction D2. The second direction D2 is perpendicular to the aircraft connection card.

In the embodiment of Figures 1 and 2, the first direction D1 and the second direction D2 are parallel and opposite. The first direction D1 is here directed towards the front of the avionics computer 2 and the second direction D2 is directed towards the rear of the avionics computer 2.

As illustrated in Figures 1 and 2, each second card 12 is disposed at one end of the card row 6. The card row 6 here comprises two second cards 12 disposed at both ends of the card row 6, each first card 10 being arranged between the two second cards 12.

The second complementary connectors 26 are offset on the aircraft connector board 16 with respect to the aircraft connector 18. The second cards 12 are thus offset with respect to the aircraft connector 18. The second cards 12 are not opposite the aircraft connector 18. The first cards 10 are here arranged between the second cards 12, facing the aircraft connector 18.

As illustrated in FIG. 3, the first cards 10 are arranged in pairs 31 of adjacent first cards 10 bearing on their faces 32 opposite the first connectors 20 for plugging the first cards 10 onto the interconnection card 14.

In each pair 31, each first card 10 includes a first wide connector 20A and a first narrow connector 20B. The first connector 20A has a width strictly greater than that of the first connector 20B narrow. The width of each interconnect connector corresponds to the size of this connector taken perpendicularly to the extension plane of the first card.

The number of contacts of the connector depends in particular on the width of the connector. The first connector 20A wide is for example an eight-contact connector over the width of the connector, and the second connector 20B narrow is for example a connector with five contacts over the width of the connector.

The first wide connector 20A of each first card 10 of each pair 31 is arranged opposite the first narrow connector 20B of the other first card 10 of this pair 31.

This makes it possible to provide each first card 10 with a first connector 20A wide and a first connector 20B narrow to optimize the size of the connectors, to the benefit of the lightness of the computer, with a reduced spacing between the first cards 10 d a pair 31, to the benefit of the compactness and lightness of the calculator.

If the avionics computer 2 is of the separate control channel and control channel type (COM / MON type avionic computer), it is desirable to segregate the signals intended for the control channel and the control channel.

It is possible to provide, in each pair 31 of the first cards 10, a first card 10 configured for the implementation of the control channel (first COM card) and the other first card 10 for the implementation of the channel control (first MON card). The arrangement of the card set 4 facilitates the segregation of the signals between the different first cards from the aircraft connector.

Thus, preferably, each second card 12 is dedicated to a pair 31 of first cards 10 respectively making a control channel and a control channel for computing the same computer data, and comprises electronic components dedicated to the signals of each first card 10 distinct from those dedicated to the signals of the other first card 10.

As illustrated in FIG. 4, the set of cards 6 of the avionics computer 2 makes it easy to carry out maintenance or verification operations on the computer.

The interconnection card 14 disposed along a front face 4A of the computer housing 4 which makes it easy to connect an external card located outside the computer housing to the interconnection card 14.

For this purpose, preferably, the first complementary connectors 22A, 22B carried by the interconnection card 14 have contacts crossing the interconnection card 14, which makes it possible to connect an external card 34 to the interconnection card 14 on the face of the interconnection card 14 turned towards the outside of the avionics computer 2 opposite the first and second cards 10, 12.

An external card is for example a card intended to perform qualification or maintenance tests of the avionics computer 2.

In the configuration shown in FIG. 4, a first card 10 has been removed from the avionics computer 2 and an external card 34 is connected to the interconnection card 14 in place of the first card 10 which has been removed by the intermediate parts of the first complementary connectors 22A, 22B associated with this first card 10 which cross the interconnection card 16.

The external card 34 is here connected to the interconnection card 14 via an intermediate card 36 connected on one side to the interconnection card 14 and on the other side to the external card 34.

To allow access to the connection board from outside the housing, it is possible to provide a removable front panel 4A separable from the rest of the computer housing 4 or, as illustrated, a front panel 4A which is provided with openings next to the first complementary connectors 22A, 22B. In the second case, the front face 4A is removable or irremovable.

In the embodiment of FIGS. 1 and 2, each second card 12 is plugged on the interconnection card 14 and on the aircraft connection card 16 by two opposite edges 12A, 12B of the second card 12.

The avionics computer 2 of FIG. 5 differs from that of FIGS. 1 and 2 in that each second card 12 is plugged on the interconnection card 14 and on the aircraft connection card 16 by two edges 12A, 12B which are adjacent. The two adjacent edges 12A, 12B are two mutually perpendicular edges.

The aircraft connection board 16 and the interconnection board 14 are not arranged parallel to each other, but perpendicular to each other. They are parallel to the first and second cards 10, 12.

As illustrated in FIG. 5, each second card is plugged by a rear edge 12B on the aircraft connection card 16 and by a lower edge 12A on the interconnection card 14. The interconnection card 14 is disposed of below the first (s) and second (s) cards 10, 12.

The first direction D1 and the second direction D2 are perpendicular to each other. The first direction D1 is directed vertically downwards, and the second direction D2 is directed horizontally towards the rear.

In a possible variant, each second card 12 is plugged by its rear edge 12B on the aircraft connection board and by its upper edge 12D on the interconnection card 14. The interconnection card 14 is then placed above the first and second cards 10, 12. The first direction D1 is in this case directed vertically upwards.

In the embodiments illustrated in FIGS. 1, 2 and 5, two second 12 cards are arranged at the ends of the row of cards 6, the first cards 10 being placed between the two second cards 12.

This makes it possible to arrange the second cards 12 plugged on the aircraft connection board 16 on either side of the aircraft connector 18, and to arrange the first boards 10 which are only plugged on the interconnection board 14, opposite the Aircraft connector 18 to use this space and preserve the compactness and lightness of the avionics computer 2. Other arrangements are possible.

In a variant, a second card 12 is arranged in the row of cards in an intermediate position, for example between two first cards 10 or between a first card 10 and a second card 12. In particular, it is possible to arrange a second card 12 between the first cards 10 for which this second card 12 ensures the transmission of signals between the aircraft connection card 16 and the interconnection card 14. The arrangement of the electronic cards in the avionics computer 2 makes it easier to mount the computer avionics 2.

An advantageous mounting method of an avionic computer 2 as described above comprises the steps of: - mounting the interconnection card 14 in the computer housing 4; - Plug each first card 10 and each second 12 on the interconnection card 14, then; - Insert the aircraft connection card 16 on each second card 12.

In such a mounting method, the first cards 10 and the second cards 12 are easily plugged on the interconnection card 14, one by one, without difficulty and without significant effort. Then, the aircraft connection card 14 is easily plugged onto the second cards 12, with limited effort since it only plugs into the second cards 12 which are limited in number, and it does not plug in with the first cards 10.

Claims (10)

An avionics calculator comprising a set of electronic cards including: a row of cards (6) arranged parallel to each other, the card row comprising at least a first card (10) and at least a second card (12), a card interconnection circuit (14) for connecting the cards of the card rows to one another, and an aircraft connecting card (16) for connecting the computer to the avionics system of an aircraft, in which each first card (10) is plugged in only on the interconnect board (14) among the interconnect board (14) and the aircraft connection board (16), and each second board (12) is plugged by an edge (12A) on the interconnect board and by another edge (12B) on the aircraft connecting board (16). 2. - Calculator according to claim 1, wherein the aircraft connection board carries an aircraft connector, preferably compliant with the standard ARINC 600. 3. - Calculator according to any one of the preceding claims, wherein a second card (12) is located at one end of the row of cards. 4. - computer according to any one of the preceding claims, comprising two second cards (12) arranged at both ends of the main card row. 5. - Calculator according to any one of the preceding claims, comprising exactly two second cards (12). 6. - computer according to any one of the preceding claims, wherein at least a second card (12) has a protection device for lightning protection and / or protection against electromagnetic interference. 7. - computer according to any one of the preceding claims, wherein two adjacent cards (10) of the row (6) each have on their faces facing a wide connector (20A) and a narrow connector (20B), the wide connector of each of the two cards being vis-à-vis the narrow connector of the other of the two cards (10). 8. - Calculator according to any one of the preceding claims, comprising a computer housing (4) in which is received the set of electronic cards, the interconnection card (14) being arranged along one side (4A ) of the computer box (4) accessible when the computer is installed in the operational conditions in the aircraft. 9. - computer according to any one of the preceding claims, comprising a computer housing (4) in which the set of electronic boards is received, the computer housing (4) having a front face (4A) and a rear face. (4B), the interconnection card (14) being arranged along the front face (4A), the aircraft connection board (16) being arranged along the rear face (4B), the rear face being removable and / or the front face is irremovable. 10. A method of mounting an avionics computer according to any one of the preceding claims, comprising the steps of: - mounting the interconnection card in a computer housing; - insert each first card and each second card on the interconnection card, then; - insert the aircraft connection card on each second main board.