Power supply architecture for aircraft brakes fitted with electromechanical actuators
View Patent ↗The invention relates to an architecture for powering aircraft brakes for an aircraft having at least two undercarriages, each having a certain number of wheels (L 1 , L 2 ; R 1 , R 2 ), each of the wheels being fitted with a brake having a certain number of electromechanical braking actuators ( 1, 2, 3, 4 ). The architecture has at least four power supply units that power groups of actuators taken from complementary groups of wheels.
1. A power supply architecture for powering aircraft brakes for an aircraft having at least two undercarriages, each having a certain number of wheels (L 1 , L 2 ; R 1 , R 2 ), each of the wheels being fitted with a brake having a certain number of electromechanical braking actuators ( 1 , 2 , 3 , 4 ), wherein the architecture includes at least first, second, third, and fourth power supply units, the first and third power supply units (B 1 , B 3 ) being powered by a first power supply source (AC 1 ), the second and fourth power supply units (B 2 , B 4 ) being powered by a second power supply source (AC 2 ), the wheels on each of the undercarriages being grouped into first and second complementary groups (L 1 ; R 1 ; L 2 ; R 2 ) and the power supply units powering complementary groups of braking actuators in each of the groups of wheels as follows:
the first power supply unit (B 1 ) powers a group of actuators ( 1 , 2 ) of the first group of wheels (L 1 ) of the first undercarriage, and a group of actuators ( 1 , 2 ) of the first group of wheels (R 1 ) of the second undercarriage;
the second power supply unit (B 2 ) powers a complementary group of actuators ( 3 , 4 ) of the first group of wheels (L 1 ) of the first undercarriage, and a group of actuators ( 1 , 2 ) of the second group of wheels (R 2 ) of the second undercarriage;
the third power supply unit (B 3 ) powers a group of actuators ( 1 , 2 ) of the second group of wheels (L 2 ) of the first undercarriage, and a complementary group of actuators ( 3 , 4 ) of the second group of wheels (R 2 ) of the second undercarriage; and
the fourth power supply unit (B 4 ) powers a complementary group of actuators ( 3 , 4 ) of the second group of wheels (L 2 ) of the first undercarriage, and a complementary group of actuators ( 3 , 4 ) of the first group of wheels (R 1 ) of the second undercarriage.
2. A power supply architecture according to claim 1 , adapted to an aircraft having exactly two main undercarriages, each provided with two braked wheels (L 1 , L 2 ; R 1 , R 2 ) such that on each undercarriage each group of wheels is constituted by one of the wheels carried by the undercarriage.
3. A power supply architecture according to claim 1 , wherein each group of actuators of a given group of wheels has a number of actuators equal to the number of actuators of the complementary group of actuators, or differing therefrom by no more than one.
4. A power supply architecture according to claim 1 , wherein each of the two groups of actuators powered by a given unit is powered by means of a distinct cable.
5. A power supply architecture according to claim 1 , wherein each actuator is dimensioned to develop, at least occasionally, a braking force equivalent to the force developed by two actuators of a brake in which all of the actuators are powered during braking taking the corresponding wheel to its locking limit during a landing on a dry runway.