Electrical generation system for an aircraft and associated method

Abstract

An electrical generation system to supply at least one electrical network of an aircraft, the electrical generation system comprising a control device configured to receive a general operating instruction and to issue a first parameter instruction (PCONS1) for the first converter (C1) and a second parameter instruction (PCONS2) for the second converter (C2), each parameter instruction (PCONS1, PCONS2) being either a voltage regulation instruction (RegU) to control the converter (C1, C2) to a distribution voltage or an auxiliary regulation instruction (RegA) of the turbomachine, the control device being configured to issue a parameter instruction relating to an auxiliary transition (TransA) with a stabilization delay relative to a parameter instruction relating to a voltage transition (TransU) so as to prolong the voltage regulation (RegU) during an auxiliary transition (TransA).Figure from the summary: Figure 9.

Description

Electrical generation system (1) according to claim 4, wherein the stabilization delay (Ts) is less than three times the maximum parasitic delay. Electrical generation system (1) according to claim 5, wherein the stabilization delay (Ts) is substantially equal to twice the maximum parasitic delay. Electrical generation system (1) according to any one of claims 1 to 6, wherein the control device (2) comprises a regulation block (20) configured to calculate a deviation (A) between a measurement of the distribution voltage (VDC) and a voltage setpoint

Claims

distribution (VDC*), the control block (20) comprising a gain parameter (Ki) which depends proportionally on the deviation (A).

8. Aircraft comprising at least one aircraft turbomachine (T) comprising a low pressure shaft (LP) and a high pressure shaft (HP) configured to be driven in rotation, at least one electrical generation system (1), according to any one of claims 1 to 7, supplying at least one aircraft electrical network (REA).

9. A method for generating electricity to supply at least one aircraft electrical network (AAN) from an electrical generation system (1) according to any one of claims 1 to 7, the aircraft comprising at least one aircraft turbomachine (T) comprising a low-pressure shaft (LP) and a high-pressure shaft (HP) configured to be driven in rotation, the method comprising steps of: • Receiving a general operating instruction (PECug) defining a hybridization strategy, • From the general operating instruction (PECug),issue a first parameter setting instruction (Pconsi) for the first converter (Cl) and a second parameter setting instruction (PCons2) for the second converter (C2) • a parameter setting instruction relating to an auxiliary transition (TransA) being issued with a stabilization delay (Ts) relative to a parameter setting instruction relating to a voltage transition (TransU) in order to prolong the voltage regulation (RegU) during an auxiliary transition (TransA).

10. A computer program-type product, comprising at least one sequence of instructions stored and readable by a processor and which, once read by that processor, causes the execution of the steps of the process of claim 9. [Fig. 2] [Fig. 3] PCONSI PCONSI FIG. 6 [Fig. 8] People Pcons, = TransA ..................... PcoNS2 = TransU ................................... -.........> PcoNsa-TransU Pqonsi - TransA [Fig. 9] FIG. 8 U-shaped base FIG. 9 [Fig. 10] <• <— Ts TB C1 C2 Tp <--------------1> P C0NS2 = TransU Pconsi = TransA Basque Basque FIG. 12

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