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Method and system for supplying an aircraft with electrical power

A technology for power supply systems and aircraft, applied in power distribution, emergency power supply arrangements, electrical components, etc., can solve problems such as energy waste, difficulty in using energy management systems, and reducing energy efficiency of aircraft, so as to improve energy efficiency, reduce the risk of interruption, and greatly The effect of using flexibility

Inactive Publication Date: 2015-09-30
MICROTURBO SA
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Problems solved by technology

As a result, the capacity of each energy source must greatly exceed the consumption for which that energy source is responsible, which is a waste of energy and reduces the energy efficiency of the aircraft
[0010] Furthermore, the use of energy management systems according to the prior art is difficult because there are different reload modules for loads requiring more than 15 amperes and for loads requiring less than 15 amperes
One disadvantage is that the reprint must take into account the compatibility of the source and the load

Method used

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  • Method and system for supplying an aircraft with electrical power
  • Method and system for supplying an aircraft with electrical power

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Embodiment Construction

[0030] refer to figure 1 Illustrating the present invention, the figure shows an aircraft comprising an electrical energy supply system and a plurality of loads C1 , C2 , C3 and C4 to be powered. The power supply system is equipped with a plurality of energy sources S1, S2, S3.

[0031] The energy sources S1 , S2 , S3 are of different or the same kind and may for example take the form of a propulsion engine generator of the aircraft, preferably a main power unit of the engine stage. It goes without saying that other types of energy sources may be suitable.

[0032] In addition, the energy sources S1, S2, S3 can provide electrical energy in the form of direct current or alternating current, pneumatic energy in the form of compressed air, and mechanical energy in the form of torque and power transmitted by the power shaft. Storage of these energy types is ensured by devices such as batteries or supercapacitors providing electrical energy, pressure vessels providing pneumatic e...

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Abstract

A method and system for supplying an aircraft with electrical power, said aircraft being provided with a plurality of loads (C1-C4) to be powered, said power supply system comprising a plurality of power sources (S1, S2, S3) and an onboard power management module, the power management module (MG) being electrically connected to said power sources (S1, S2, S3) and to said loads (C1-C4) to be powered. The power management module (MG) is arranged to order the powering of at least one of said loads (C1-C4) by at least two different power sources (S1, S2, S3) in parallel in the case of an increase in the power requirements, said load (C1-C4) initially being powered by a single power source (S1, S2, S3).

Description

technical field [0001] The invention relates to the field of power supply of aircraft, in particular to a method and system for managing the power supply system of an aircraft. Background technique [0002] Aircraft typically include an electrical power supply system to power the various devices of the aircraft (mechanical actuators, flight controls, passenger seat multimedia systems, cabin ventilation, etc.). From an electrical point of view, aircraft equipment can be considered as a load that consumes electrical energy. [0003] In order to allow centralized management of electrical energy in the electrical supply system, loads are of two possible types: loads important for the operation of the aircraft are called "essential" loads (flight controls, etc.), and Important loads are referred to as "non-essential" loads (passenger seat multimedia system, cabin ventilation, etc.). Loads are also divided according to where they are installed so that they are powered by the clo...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H02J4/00B64D41/00
CPCH02J4/00B64D41/00B64D2221/00H02J2310/44H02J9/00H02J9/06H02J11/00H02J13/00B60R16/03
Inventor 让-弗朗索瓦·里迪弗洛伦特·德尔马斯
Owner MICROTURBO SA
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