Differential braking system
View Patent ↗A braking system for the landing gear of an aircraft, which landing gear includes a bogey containing at least four wheels, each equipped with a brake, with the bogey having at least two axles that are connected to the aircraft by a telescoping strut, wherein when the aircraft makes a low-speed turn around a center of rotation, the straight line linking the center of rotation of the turn to the barycenter of the landing gear does not pass between the front wheels and the rear wheels of the landing gear which system further includes means for applying differential braking between the front wheels and the rear wheels of the landing gear.
1. A braking system for an aircraft comprising a landing gear which landing gear includes bogeys containing at least four wheels, each equipped with a brake, with the bogey comprising at least two axles that are connected to the aircraft by a telescoping strut, which system further includes means for applying differential braking between wheels of the landing gears and wherein the means include a differential braking calculator making it possible to select, from among the different wheels of each landing gear, the wheels to be braked and those not to be braked when the aircraft makes a turn, in accordance with the centering of the wheels of the landing gear in relation to the straight line linking the center of rotation of the turn to the barycenter of the landing gear of the aircraft said differential braking calculator being adapted to adapt a differential braking when a straight line linking the center of rotation and the barycenter of the landing gear passes between the front and rear wheels of the bogeys to brake the wheels nearest to the center of the turn and to adapt a differential braking when a straight line linking the center of rotation and the barycenter of the landing gear does not pass between the front and rear wheels of the bogeys to brake front or rear wheels of the bogeys while the respective rear or front wheels are remaining free of braking.
2. An aircraft including at least two sets of landing gear, with each landing gear including at least four wheels, and with each of the wheels being equipped with a brake that is actuated by means of an actuator in order to control the opening or closing of a valve located between a hydraulic fluid distributor and a hydraulic brake line feeding the brake, which actuator is activated remotely by brake controls located in the cockpit, wherein the actuator for each brake is connected to the brake controls by means of the differential braking calculator of the differential braking system according to claim 1 .
3. An aircraft according to claim 2 , wherein the actuator for each brake is an electrically controlled actuator that controls the opening or closing of a valve located between the brake line and of the hydraulic fluid distributor.
4. A method for reducing torque applied to a strut of an aircraft landing gear during turning wherein said aircraft comprises a braking system for the landing gear, which landing gear includes several bogeys containing at least four wheels, each equipped with a brake, with the said bogeys consisting of at least two axles that are connected to the aircraft by a telescoping strut, which system further includes means for applying differential braking between wheels of the said bogeys, wherein when the aircraft makes a low-speed turn around a center of rotation, for which the straight line linking the center of rotation of the turn to the barycenter of the landing gear does not pass between the front wheels and the rear wheels of a bogey, said braking system applies a differential braking between the front wheel and the rear wheels of said bogey and wherein when the aircraft makes a low-speed turn around a center of rotation, for which the straight line linking the center of rotation of the turn to the barycenter of the landing gear passes between the front wheels and the rear wheels of a bogey said braking system applies a differential braking between wheels closer and farther from the center of the turn.
5. The method according to claim 4 , wherein the means including a differential braking calculator, said process comprises selecting, from among the different wheels of each landing gear, the wheels to be braked and those not to be braked when the aircraft makes a turn, in accordance with the centering of the wheels of the landing gear in relation to the straight line linking the center of rotation of the turn to the barycenter of the landing gear of the aircraft.
6. The method according to claim 4 wherein said aircraft includes at least two bogeys, with each bogey including at least four wheels, and with each of the wheels being equipped with a brake that is actuated by means of an actuator in order to control the opening or closing of a valve located between a hydraulic distributor and a hydraulic brake line and the said actuator for each brake is connected to the said brake controls by means of the differential braking calculator of the differential braking system wherein feeding the brakes, which actuator is activated remotely by brake controls located in the cockpit.
7. The method according to claim 6 , wherein said actuator for each brake being an electrically controlled actuator, control of the opening or closing of a valve located between the said brake line and of the said hydraulic distributor is done through said electrically controlled actuator.
8. The method according to claim 4 wherein when the center of rotation of the turn to the barycenter of the landing gear passes between the front wheels and the rear wheels of a further bogey, said braking system applies a differential braking between the front wheel and the rear wheels of said further bogey.