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Electrical distribution system for an aircraft

A power distribution system and aircraft technology, applied in the direction of instruments, power distribution, electrical components, etc., can solve the problems of doubling design and logistics costs

Active Publication Date: 2016-03-02
SAFRAN ELECTRICAL & POWER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0022] During development or the aircraft's service life, in the case of retrofit systems, both types of boards would need to be retrofitted and possibly upgraded by the aircraft manufacturer or operator, doubling the design and logistical costs each time

Method used

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  • Electrical distribution system for an aircraft
  • Electrical distribution system for an aircraft
  • Electrical distribution system for an aircraft

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Embodiment Construction

[0040] From now on, the current development of the protection board architecture can envisage the replacement of the hitherto single use of each protected path microprocessor by a set of at least two microprocessors for controlling all protected paths (that is to say, For example, 16 microprocessors for a 16-way protection board). figure 2The main elements of such a fender are shown. It can be seen that the two redundant microprocessors (5a, 5b) control the control means (6a, 6b) of the power units of the protected path via intermediary means (7a, 7b, 7n) for determining the instructions to be transmitted , 6n), wherein the intermediary device is able to determine which microprocessor instruction has to be transferred. The aforementioned microprocessors are each connected to means for measuring the status of the protected path, and to the aircraft bus (4a, 4b).

[0041] Such a protective board allows a substantial reduction in the number of microprocessors used (while reduc...

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PUM

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Abstract

Electrical distribution system for an aircraft comprising at least one electrical supply path comprising at least one power unit capable of opening or closing the connection between at least one electrical energy source and at least one device of the aircraft. The system comprises protection cards (2b, 2n) each comprising at least two microcontrollers each capable of sending a command to each power unit of the electrical supply paths protected by each protection card and, among the set of microcontrollers of the protection cards, at least two microcontrollers are provided with a communication and computation function with all of the microcontrollers of the protection cards (2b, 2n).

Description

technical field [0001] The technical field of the present invention relates to the power distribution system of an aircraft, and in particular to a control method for such a system. Background technique [0002] Typically, an aircraft has an electrical system including, inter alia, a primary power distribution system and a secondary power distribution system. The secondary power distribution system is capable of protecting and distributing electric power from internal power sources such as generators or batteries or external power sources such as ground power units. [0003] The secondary distribution system described above consists of a number of circuit boards, notably a communication and computing board (EDMU) and a protection board (SSPC). [0004] figure 1 A secondary distribution system according to the prior art is shown. The system consists of two types of boards: a communication and computing board called the Electrical Distribution Management Unit ("EDMU" for sh...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02J13/00H02J4/00
CPCG06F13/36H02J3/0073H02J2310/44H02H1/0061H02J4/00B64D2221/00G06F1/28H02J9/00H02J13/00
Inventor 让·克莱尔·普拉迪耶
Owner SAFRAN ELECTRICAL & POWER