Electro-hydraulic braking system for the wheels of an aircraft
First Claim
1. An electro-hydraulic braking system for the wheels of an aircraft landing gear in which the wheels are distributed in two groups disposed symmetrically on either side of the longitudinal midplane of the aircraft, each wheel being fitted with a brake that is actuated from brake pedals, via an associated braking and anti-skid servo-valve electrically controlled by a control unit that obtains measurement data corresponding to depression of said pedals and to each speed of the wheel, the system including two sources of hydraulic pressure, each feeding a corresponding hydraulic circuit leading via braking control stages having two inlets to the brakes of two groups of the wheels, with a first circuit connecting the first inlet of each of the braking control stages, via two shuttle valves each associated with the brakes of one group of wheels, either to a first solenoid valve electrically controlled by the control unit or else to a double metering valve that is mechanically controlled by the brake pedals and with a second circuit directly connecting the second inlet of each of the braking control stages to a second solenoid valve likewise electrically controlled by the control unit, each braking control stage being organized about two symmetrical internal circuits each including one said servo-valve per associated brake, said two internal circuits additionally being cross-connected via a respective controlled valve so that in the event of a breakdown in one or the other of the two hydraulic circuits, the servo-valves associated with the other hydraulic circuit enable braking and anti-skid control to be performed in a paired tandem mode, with reconfiguration being automatic.
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Accused Products
Abstract
The invention relates to an electro-hydraulic braking system for the wheels of aircraft landing gear. The system comprises two hydraulic pressure sources each feeding a hydraulic circuit that leads to the brakes of two groups of wheels via a single braking control stage. A circuit connects either a solenoid valve electrically controlled by the control unit or else a double metering valve mechanically controlled by the brake pedals via two shuttle valves, to one inlet of each control stage. A second circuit directly connects a solenoid valve to a second inlet of each of said control stages. Each control stage includes two symmetrical internal circuits having one servo-valve per corresponding brake, which servo-valves are cross-connected by means of a respective corresponding controlled valve. In the event of one of the circuits breaking down, the servo-valves associated with the other circuit then serve, after automatic reconfiguration, also to provide braking and anti-skid control in a paired tandem mode.
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Citations
10 Claims
- 1. An electro-hydraulic braking system for the wheels of an aircraft landing gear in which the wheels are distributed in two groups disposed symmetrically on either side of the longitudinal midplane of the aircraft, each wheel being fitted with a brake that is actuated from brake pedals, via an associated braking and anti-skid servo-valve electrically controlled by a control unit that obtains measurement data corresponding to depression of said pedals and to each speed of the wheel, the system including two sources of hydraulic pressure, each feeding a corresponding hydraulic circuit leading via braking control stages having two inlets to the brakes of two groups of the wheels, with a first circuit connecting the first inlet of each of the braking control stages, via two shuttle valves each associated with the brakes of one group of wheels, either to a first solenoid valve electrically controlled by the control unit or else to a double metering valve that is mechanically controlled by the brake pedals and with a second circuit directly connecting the second inlet of each of the braking control stages to a second solenoid valve likewise electrically controlled by the control unit, each braking control stage being organized about two symmetrical internal circuits each including one said servo-valve per associated brake, said two internal circuits additionally being cross-connected via a respective controlled valve so that in the event of a breakdown in one or the other of the two hydraulic circuits, the servo-valves associated with the other hydraulic circuit enable braking and anti-skid control to be performed in a paired tandem mode, with reconfiguration being automatic.
Specification