Abstract: The invention relates to an architecture for a hydraulic circuit associated with actuators (100), such as actuators for airplane brakes, the architecture comprising a main hydraulic circuit (C) having hydraulic components (4, 5 101, 6) and adapted to convey hydraulic fluid pressurized by at least one pressure generator (2) associated with a main supply (1) to the actuators (100). The architecture includes an emergency system comprising an auxiliary supply (8) permanently fed by a return circuit (R) collecting the returns from all of the hydraulic components (4, 5,101, 6), the auxiliary supply (8) being connected to the main supply (1) via a relief valve (9). The emergency system further comprising an electrically driven pump unit (10) arranged to take fluid from the auxiliary supply (8) and to inject it into the main circuit (C) downstream from a general check valve (3).

Abstract: The invention relates to an architecture for a hydraulic circuit associated with actuators (100), such as actuators for airplane brakes, the architecture comprising a main hydraulic circuit (C) having hydraulic components (4, 5 101, 6) and adapted to convey hydraulic fluid pressurized by at least one pressure generator (2) associated with a main supply (1) to the actuators (100). According to the invention, the architecture includes an emergency system comprising an auxiliary supply (8) permanently fed by a return circuit (R) collecting the returns from all of the hydraulic components (4, 5, 101, 6), the auxiliary supply (8) being connected to the main supply (1) via a relief valve (9), said emergency system further comprising an electrically driven pump unit (10) arranged to take fluid from the auxiliary supply (8) and to inject it into the main circuit (C) downstream from a general check valve (3).

Abstract: The invention relates to an architecture for a hydraulic braking system suitable for an aircraft of the type having at least one group of main landing gear units, each landing gear unit comprising a determined number of wheels each provided with a hydraulically actuated brake, the or each landing gear group being associated with a hydraulic circuit provided with hydraulic equipment and adapted to deliver hydraulic fluid under pressure to all of the brakes of the landing gear group, the hydraulic fluid being pressurized by at least one aircraft pressure generator system associated with an aircraft hydraulic fluid supply. According to the invention, accumulators are connected on the or each circuit in sufficient number for each accumulator to feed two pairs of brakes, each pair of brakes being mounted on a distinct landing gear unit, and an electrically-driven pump being arranged to maintain a predetermined pressure level in all of the accumulators of the circuit in question.

Abstract: The invention relates to an architecture for a hydraulic braking system suitable for an aircraft of the type having at least one group of main landing gear units, each landing gear unit comprising a determined number of wheels each provided with a hydraulically actuated brake, the or each landing gear group being associated with a hydraulic circuit provided with hydraulic equipment and adapted to deliver hydraulic fluid under pressure to all of the brakes of the landing gear group, the hydraulic fluid being pressurized by at least one aircraft pressure generator system associated with an aircraft hydraulic fluid supply. According to the invention, accumulators are connected on the or each circuit in sufficient number for each accumulator to feed two pairs of brakes, each pair of brakes being mounted on a distinct landing gear unit, and an electrically-driven pump being arranged to maintain a predetermined pressure level in all of the accumulators of the circuit in question.