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Electrical links including electrical protection devices

A protection device and electric chain technology, applied in the field of electric links, can solve the problems of electric continuity damage of electric links and achieve the effect of ensuring safety

Active Publication Date: 2019-10-25
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Circuit breaker devices of the prior art are not suitable for detecting a break in the electrical continuity of an electrical link

Method used

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  • Electrical links including electrical protection devices
  • Electrical links including electrical protection devices
  • Electrical links including electrical protection devices

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0027] refer to figure 1 , the aircraft 10 includes electrical installations having a high voltage electrical power source 270 connected to user equipment 250 via an electrical link 290 including an electrical protection device 200 associated with the electrical link 290 .

[0028] Furthermore, an electrical power source 270 is linked to the user device 250 through a current return line 260 .

[0029] The high voltage electrical power supply 270 supplies a DC voltage HV of the order of + or -270 volts DC, or 540 volts DC.

[0030] Furthermore, the aircraft 10 includes conductive structures (not shown) formed by any metallic / conductive elements of the aircraft that are at a reference potential and form earth.

[0031] refer to Figure 2 to Figure 4 , and according to the present invention, the electrical link 290 includes an electrical conductor 240 surrounded by an insulating covering 320 (eg, a plastic sleeve), and the electrical protection device 200 configured to test the...

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PUM

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Abstract

The invention relates to an electrical link for linking a DC high voltage power supply to user equipment (250) comprising an electrical conductor (240) surrounded by an insulating covering and an electrical protection device (200) comprising: - Conductive a sleeve (280), which is arranged to surround the insulating covering; - a circuit breaker (210), which is arranged on the electrical conductor (240) and is configured to interrupt the current transmitted through the conductor, the electrical protection device (200) Also comprising: - a biasing module (245) configured to voltage bias the conductive sleeve (280) with a DC voltage called a test voltage (V_TEST_PSS); - for limiting the bias of the conductive sleeve A device (250a) for setting a voltage, which has a limiting voltage (Vlim) smaller than the test current (V_test_PSS); a detection module (220), which is connected to the conductive sleeve (280) and is configured to detect The limiting means (250a) limits or lack of limiting the bias voltage of the conductive sleeve and commands the circuit breaker (210) based on the detection.

Description

technical field [0001] The invention relates to an electrical link for transmitting DC high voltage to user equipment, the link comprising electrical protection means for supplying electrical power in a safe manner. Background technique [0002] Conventionally, the electrical installations on board an aircraft include an electrical power source linked to user equipment supplied with electrical power through electrical links formed by electrical conductors covered with insulating coverings. The electrical link includes circuit breaker means for monitoring parameters of electrical signals transmitted over the link between the power source and the user equipment in order to interrupt overload or short circuit currents in the conductors. [0003] The power consumption on aircraft is constantly increasing. This trend inevitably leads to an increase in the voltage levels of the electrical power supply systems on board the aircraft, typically 115 volts AC (AC means alternating cur...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H02H3/087G01R31/58
CPCH02H3/087H02H3/202H02H7/226G01R31/008G01R31/58G01R31/54B64D45/00B64D2221/00G01R19/0038H02H1/0007H02H5/10
Inventor 帕特里克·奥姆斯
Owner AIRBUS OPERATIONS (SAS)