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System and method for dissipating electric energy regenerated by actuators

An electric actuator, electric energy technology, applied in electric braking system, deceleration device of DC motor, deceleration device of AC motor, etc. The effect of high availability

Active Publication Date: 2018-01-02
SAFRAN ELECTRICAL & POWER
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, if the dissipation system fails, the regenerated electrical energy produced by one of the electric actuators will no longer be dissipated, making it possible to damage or even destroy the other actuators and / or power supplies of the aircraft, damaging the DC voltage increases related to the connection
[0016] However, it has been observed that prior art energy dissipation systems do not have the availability to dissipate the regenerative electrical energy of several electric actuators

Method used

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  • System and method for dissipating electric energy regenerated by actuators
  • System and method for dissipating electric energy regenerated by actuators
  • System and method for dissipating electric energy regenerated by actuators

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Embodiment Construction

[0074] image 3 An energy dissipation system 10 according to one embodiment of the invention is shown.

[0075] The energy dissipation system includes a resistor R called a "dissipation resistor". The dissipating resistor R is capable of dissipating energy through the Joule effect. The energy dissipation system also includes two arms designated "switching arms" 12 and 13 . Each switching arm 12, 13 is connected in series with a dissipation resistor R. The two switching arms 12, 13 are connected in parallel with each other.

[0076] Each switching arm 12, 13 comprises two switches Q1, Q2 and Q3, Q4 connected in series with each other. Each switch includes two terminals B 11 , B 12 , B 21 , B 22 , B 31 , B 32 , B 41 , B 42 . Each switch includes a control gate G1, G2, G3, G4. Between the two switches Q1, Q2 and Q3, Q4 of the same arm there is located a point designated as the "midpoint" P1, P2.

[0077] Each switch is controllable. In fact, each switch Q1, Q2, Q3,...

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Abstract

The invention relates to a system for dissipating (10) regenerated electric energy produced by an electric actuator (1) of an aircraft, the dissipating system (10) including: a resistor (R); two switching arms (12, 13), each switching arm (12, 13) being connected in series with the resistor (R), the two switching arms (12, 13) being connected together in parallel, each switching arm (12, 13) including two switches (Q1, Q2, Q3, Q4) connected to one another in series, each switch (Q1, Q2, Q3, Q4) including two terminals and a control grid, each switch (Q1, Q2, Q3, Q4) being capable of being controlled by controlling the potential applied to the control grid (G1, G2, G3, G4) thereof; and measurement means (MM1, MM2, MM3, MM4) capable of measuring the voltage at the terminals of each switch (Q1, Q2, Q3, Q4).

Description

technical field [0001] The present invention relates to a system and method for dissipating electrical energy regenerated by electrical actuators of an aircraft. Background technique [0002] As stated in the preamble of patent application FR2967847, the electric actuators of the aircraft can be operated according to two modes: [0003] Motor mode, in which the aircraft's power supply provides them with energy. This power supply usually must be a DC power supply. To achieve this, the aircraft usually includes an AC power supply and a rectifier making it possible to convert the AC voltage current supplied by the aircraft's power supply into a DC voltage current; the rectifier may also be located in the actuator itself; [0004] Generator mode, in which electric actuators generate electricity. This energy is often referred to as "regenerated electrical energy". Regenerative electrical energy is generated, for example, during in-flight maneuvers of an aircraft, during which...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02P3/12H02P3/22B60L7/02
CPCB60L7/02H02P3/12H02P3/22Y02T10/64
Inventor 劳伦·卡尔塔耶班诺特·米肖
Owner SAFRAN ELECTRICAL & POWER
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