Abstract: A device for controlling the braking of a wheel train is disclosed and includes an actuating mechanism for alternating actuating symmetrically disposed groups of wheel brakes, temperature sensors disposed or at least one wheel brake in each of the groups of wheel brakes with the control mechanism actuating the coolest group of wheel brakes several times when the temperature difference between the groups of wheel brakes reaches a threshold temperature difference and for actuating the groups of wheel brakes cyclically so long as the threshold temperature difference is not reached.

Abstract: The system in accordance with the invention provides braking while an aircraft (1) is being towed on the ground by a tractor vehicle (2) which is mechanically connected to the aircraft and which is fitted with a brake device under the control of a brake pedal (27), with the aircraft being fitted with a braking circuit. The system comprises a towing brake member (7) disposed in the aircraft's braking circuit line (34) for connecting the brake control member (27) of the vehicle to the towing brake member (7) of the aircraft.

Abstract: A pulse generator in which a magnetic circuit is closed by a portion of a wall (5) of a cylindrical part rotating about its axis and coupled at one of its ends to a drive member (7). The wall portion and a fixed part (1) together define an air gap which varies depending on the relative angular positions of the wall portion and the fixed part such that during rotation magnetic field variations are generated at a frequency proportional to the speed of rotation of the rotating part. The generator includes an electrically conductive winding (4) in which the field variations generate electrical pulses, and the rotating cylindrical part (5) includes at least one longitudinal slot (8).

Abstract: A carbon disk brake rotor (1) has n trapezium-shaped drive notches (3) around its periphery and a plurality of reinforcing riders (2), with the drive faces (6) of each notch (3) being at an angle A of (360/2n) degrees relative to the midplane (3a) of the notch, and with the riders (2) completely covering the projecting portions (7) between consecutive notches (3) which have parallel fitting faces (9).

Abstract: A hydraulic circuit for aircraft braking, the circuit including wheel brakes (11) fed with hydraulic fluid by servovalves (8, 22) mounted in a normal circuit and in an emergency circuit. The normal circuit and the emergency circuit are selectively connected to the wheel brakes by switching devices (9) and protected from excessive loss of hydraulic fluid by hydraulic fuses (6, 24). The servovalves of the normal circuit are associated in pairs. The hydraulic fuses (6) of the normal circuit are disposed upstream from the servovalves (8) on lengths of line (5) which are common to each pair of servovalves. The devices (9) for switching from the normal circuit to the emergency circuit are disposed downstream from the servovalves (8).

Abstract: Thermal insulators (40,50) are each made of a material based on carbon fibers and subjected to low temperature heat treatment. One insulator (40) is disposed between a thrust means actuator (18) and a first brake stator (28a), and the other insulator (50) is disposed between a last brake stator (28b) and a brake retaining plate (30). The insulator (40) associated with the first stator (28a) is of comparable size to the stator.

Abstract: The method of controlling braking on a wheeled vehicle (such as an aircraft during landing) is applied to at least one wheel of the vehicle, which wheel has brakes and means for measuring the wheel speed. The method consists in a repeated two-period cycle comprising:a measuring period (0-t1, t2-t3) in which the wheel brakes are not applied and in which the true speed (A) of the vehicle is measured by measuring the linear speed (D2) of the wheel; anda braking period (t1-t2, t3- ) in which the said measured true speed is used in conjunction with a decleration value to estimate an approximate value of the vehicle speed (B1, B2), and in which the wheel brakes are applied in such a manner that the linear speed (D1, D3) of the wheel is caused to be less than the estimated speed of the vehicle by a predetermined function.

Abstract: The method of controlling aircraft braking during landing on a runway as soon as the running gear of the main landing gear has made runway contact and prior to the nose gear making contact, comprises: determining the value of the nose-up angle .DELTA. of the aircraft as soon as it makes runway contact with its main landing gear; providing a signal representative of the value of the nose-up angle; and controlling braking of the aircraft by any appropriate braking apparatus as a function of a magnitude representative of the signal to ensure acceptable variation of said nose-up angle.

Abstract: The braking control system includes a generator for generating a first electrical control signal, a controllable fluid source suitable for delivering the fluid at a predetermined pressure at an outlet from the source, a slide valve for connecting the outlet of the source to a brake actuator, a circuit for measuring the value of the pressure at the outlet from the source, a circuit being suitable for delivering a second signal having a value representative of the measured pressure, and a controller for controlling the source of fluid as a function of the first and second signals in such a manner that the fluid pressure at the outlet from the source has a value which is a function of the first signal as corrected by the second signal.