EP-4736310-A1 - METHOD FOR REGULATING AN ELECTRIC MACHINE IN MOTOR MODE BY PARALLEL HYBRIDISATION OF AN AUXILIARY ELECTRICAL NETWORK

Abstract

The invention relates to an electrical system for an aircraft, comprising a main network (110) and an auxiliary network (120) connected to the main network (110) and a device for regulating the rotary electric machine (111), the regulating device comprising: - a first regulating member (131) for regulating the voltage of the main network (110) connected to the control unit (113), the first regulating member (131) being configured to regulate the induction current of the rotor of the rotary electric machine (111); - a second member (132) for regulating the current at the terminals of the rotary electric machine (111) connected to the control module (123), the second regulating member (132) being configured to control the current generated by the converter (122), the electrical system being configured to adopt: - a generator configuration in which the rotary electric machine (111) transmits an electric current to the at least one electric component (200); and - a motor configuration in which the value of the current at the output of the converter (122) is greater than the value of the current of the at least one electric component (200), the electrical system switching from the generator configuration to the motor configuration, and vice versa, by controlling the regulating device (123).

Inventors

• ALLARD, Dimitri
• DEVAUTOUR, JOEL
• KARIM, Jawad

Assignees

• Safran Electrical & Power

Dates

Publication Date

20260506

Application Date

20240626

Claims (1)

1. CLAIMS 1. Electrical system (100) for an aircraft comprising a main network (110) and an auxiliary network (120) connected to the main network (110), the main network (110) comprising: - A drive system (112), A rotating electrical machine (111) connected to the drive system (112), the rotating electrical machine (111) being connected to at least one electrical component (200), the rotating electrical machine (111) comprising a rotor and a stator, the rotor being driven into motion by the drive system (112), A control unit (113) of the rotating electrical machine (111), the auxiliary network (120) comprising: at least one battery (121), supplying direct current to the at least one electrical component (200), a converter (122) connected to the at least one battery (121) and to the at least one electrical component (200), configured to convert the direct current into an alternating current, - a control module (123) of the converter (122) connected to the converter (122), configured to measure a voltage between the rotating electrical machine (111) and the at least one electrical component (200) and to measure a voltage between the converter (122) and the at least one electrical component (200), the electrical system further comprising a device for controlling the rotating electrical machine (111), the control device comprising: a first control member (131) for controlling the voltage of the main network (110) connected to the control unit (113), the first control member (131) being configured to control the induction current of the rotor of the rotating electrical machine (111) so that the rotating electrical machine (111) is maintained at an imposed rotation speed, a second control member (132) for controlling the current at the terminals of the rotating electrical machine (111) connected to the control module (123), the second control member (132) being configured to control the current generated by the converter (122) when the induction current of the rotor of the rotating electrical machine (111) is regulated by the first voltage control member (131) of the main network (110), the electrical system being configured to take: a generator configuration in which the rotating electrical machine (111) transmits an electric current to the at least one electrical component (200), and an engine configuration in which the value of the current at the output of the converter (122) is greater than the value of the current of the at least one electrical component (200), the electrical system switching from the generator configuration to the engine configuration, and vice versa, by controlling the control device (123). 2. An aircraft electrical system (100) according to claim 1, wherein the drive system (112) is a rotary drive system. 3. An aircraft electrical system (100) according to claim 1 or 2, wherein the main network (110) and the auxiliary network (120) are three-phase networks. 4. Electrical system for aircraft (100) according to one of claims 1 to 3, comprising a filter (124) arranged between the converter (122) and the at least one electrical component (200). 5. Electrical system for aircraft (100) according to one of claims 1 to 4, in which the converter (122) is an inverter.

Description

DESCRIPTION Title of the invention: Method for controlling an electric machine in motor mode by parallel hybridization of an auxiliary electrical network. [0001] The invention relates to the field of on-board electrical systems and rotating electrical machines generating electrical energy for consumer components inside an aircraft. More generally, the invention relates to the field of electrical networks and hybridization. [0002] The invention relates to an electrical system for an aircraft comprising in particular a device for controlling an electrical machine and at least one electrical energy storage assembly. More particularly, the invention is an electrical system comprising a device for parallel hybridization of single or multiple stage electrical machines with a static generator for providing engine torque and ensuring the generation needs of the aircraft network. [0003] The electrical machines of an aircraft are alternators - motors. The motor function is currently only used in the context of starting a reactor (traditionally by a ground-based energy source). Recent developments in energy storage systems make it possible to envisage re-boarding new energy sources in aircraft. The latter will make it possible to perform hybridization functions of these machines according to certain flight phases in order to optimize the fuel consumption of the reactor for low-efficiency regimes. [0004] In addition, turbulence in flight causes variations in mechanical power which force the aircraft's reactors to be oversized in order to avoid reaching an unstable regime. [0005] In addition, aircraft today increasingly carry electrical components, particularly inverters, to perform the electric starting function. However, these inverters are not reused after the flight and can then be considered as dead weight. [0006] Finally, the electrical power network of the aircraft system, when the components are in current generation mode, must be permanently powered. However, this need is a brake on hybridization solutions because [0007] the main rotating electrical machines cannot generate power to the aircraft electrical grid and provide torque to the reactor at the same time. [0008] Some documents such as document EP 4087079 A1 deal with this problem in the field of aeronautics. Document EP 4087079 A1 only allows current regulation at the converter level in the aircraft network. However, since the load required in the aircraft network is variable, the power of the latter cannot be compensated by regulation. In other words, document EP 4087079 A1 allows regulation of the current at the converter output but does not provide information on a supply from energy storage systems to the aircraft's rotating machine. [0009] Document WO 2016/133503 A1 proposes a device facilitating the starting of aircraft propulsion systems by means of a coupling between the mechanical drive systems and the rotating electrical machines of the aircraft. However, document WO 2016/133503 A1 proposes to relieve the transmission shaft of its main load, namely the propulsive torque, by transmitting engine torque assistance. However, in a starter mode as disclosed, the device according to document WO 2016/133503 A1 does not seek to maintain the network voltage in the aircraft at a certain value, which is essential during the flight phase of the aircraft. [0010] The invention aims to overcome all or part of the problems mentioned above by proposing a device for controlling the power flows of rotating electrical machines by two separate controls: An initial check of the aircraft network voltage at a constant value by controlling the rotor current of the rotating electrical machine. A second control of the powers linked to the rotating electrical machine by the current source of the hybridization network connected in parallel with the main network. [0011] To this end, the invention relates to an electrical system for aircraft comprising a main network and an auxiliary network connected to the main network, the main network comprising: A drive system, A rotating electrical machine connected to the drive system, the rotating electrical machine being connected to at least one electrical component, the rotating electrical machine comprising a rotor and a stator, the rotor being driven into motion by the drive system, A control unit for the rotating electrical machine, the auxiliary network comprising: at least one battery, supplying direct current to the at least one electrical component, a converter connected to the at least one battery and to the at least one electrical component, configured to convert the direct current into an alternating current, a control module of the converter connected to the converter, configured to measure a voltage between the rotating electrical machine and the at least one electrical component and to measure a voltage between the converter and the at least one electrical component, the electrical system further comprising a device