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System for controlling an aircraft electrical network

A control system and aircraft technology, applied in electrical components, power distribution, aircraft parts, etc., can solve problems such as alternator safety catastrophic events

Pending Publication Date: 2021-10-29
SAFRAN ELECTRICAL & POWER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] However, paralleling of alternators is a catastrophic event in terms of safety if no synchronizing device is specified

Method used

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  • System for controlling an aircraft electrical network
  • System for controlling an aircraft electrical network
  • System for controlling an aircraft electrical network

Examples

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Embodiment Construction

[0031] figure 1 Applied to the previous reference shown by the first example Figure 4 The principle of the control system of the invention is described for a known architecture, namely with four distribution boxes LDB1, LDB3, RDB4 and RDB2, and two power electronics boxes LPEB, RPEB.

[0032] The control system that controls the electrical grid and drives the different motors of the aircraft includes several electronic boards, control boards and power supply units. The six electronic boards 60L, 62L, 64L; 60R, 62R, 64R are so-called universal LCMM1, LCMM2, LCMM3; RCMM1, RCMM2, RCMM3, because they are interchangeable (in case of failure of one electronic board, unlike prior art , the functions supported by them can be disabled or loaded into another board, in the prior art each board associated with a given function cannot be reconfigured). The other six electronic boards 66, 68, 70, 72, 74, 76 are called local CIBs and are associated with each of the distribution boxes LDB1...

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PUM

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Abstract

System for controlling an aircraft electrical network comprising at least a first propulsion assembly having at least one left-hand starter-generator (SG1, SG3) and a second propulsion assembly having at least one right-hand starter-generator (SG2, SG4) and other electric motors (ECS1, EC2, ECS3, ECS4), which system comprises: - first and second power electronics boxes (LPEB, RPEB) each including at least two what are called "generic" control circuit boards (60L, 62L, 64L; 60R, 62R, 64R) for controlling the electrical network, each of these at least two generic control circuit boards being connected by fast communication links to distinct first and second data switches (90-1, 90-2; 91-1, 91-2), the first and second data switches (90-1, 90-2) of the first power electronics box (LPEB) being connected, respectively, to the first and second data switches (91-1, 91-2) of the second power electronics box (RPEB) by a first fast communication bus (92).

Description

technical field [0001] The present invention relates to the field of aircraft electrification, and more particularly relates to a system for controlling an aircraft power grid. Background technique [0002] The ever-increasing electrification of commercial aircraft (air conditioning, landing gear, thrust reversers, deicing, etc.) places ever higher demands on electrical systems (increased power, increased availability, multiple operating modes). [0003] Therefore, aircraft manufacturers have developed decentralized structures that can optimize the quality of power cables by placing distribution boxes as close as possible to the load. [0004] However, these architectures have a negative impact on systems that control power distribution, as they result in an increased number of electronic boards and the wiring associated with these boards, as Figure 4 shown, said Figure 4 The current electrical architecture of a commercial aircraft with two propulsion assemblies is schemat...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02J4/00B64D41/00B64C13/50
CPCH02J4/00B64D41/00H02J2310/44B64D2221/00B64D33/00Y02T50/50B64D31/14
Inventor 尼古拉斯·卡尔菲利普·德尔博斯
Owner SAFRAN ELECTRICAL & POWER