Abstract: The invention relates to an aircraft brake for braking a wheel received on an axle presenting in succession a large-diameter cylindrical upstream portion, a conical portion, and a smaller-diameter cylindrical downstream portion suitable for receiving the wheel, the brake comprising: a stack of disks; a structural engaged on the axle and having the disks mounted thereon, the structural part comprising a support member for receiving braking actuators and including a centering portion for centering the structural part on the upstream cylindrical portion of the axle; and a torsion tube receiving the disks, the torsion tube being made integrally with the support member and the centering bearing surface and extending substantially to extend the centering bearing surface in register with the conical portion of the axle; and a braking force takeup member separably fitted on a free end of the torsion tube remote from the centering bearing surface.

Abstract: The invention relates to a wheel-and-brake assembly for an aircraft, the assembly comprising: a wheel having a rim for mounting on an aircraft axle; and a brake comprising a stack of disks with alternating stator disks that are stationary in rotation and rotor disks mounted to rotate with the wheel. According to the invention, the assembly comprises a drum extending around the disks to be interposed between the disks and the rim, the drum including drive means for driving the rotor disks in rotation and fastener means for fastening the drum to the rim of the wheel.

Abstract: The invention relates to an aircraft brake for braking a wheel received on an axle presenting in succession a large-diameter cylindrical upstream portion, a conical portion, and a smaller-diameter cylindrical downstream portion suitable for receiving the wheel, the brake comprising: a stack of disks; a structural engaged on the axle and having the disks mounted thereon, the structural part comprising a support member for receiving braking actuators and including a centering portion for centering the structural part on the upstream cylindrical portion of the axle; and a torsion tube receiving the disks, the torsion tube being made integrally with the support member and the centering bearing surface and extending substantially to extend the centering bearing surface in register with the conical portion of the axle; and a braking force takeup member separably fitted on a free end of the torsion tube remote from the centering bearing surface.

Abstract: The invention relates to a brake system for braking aircraft wheels, the brake system being of the type which, for each wheel, comprises a stator central portion coaxially surrounding a wheel axle on which a rotor annular portion is mounted to rotate, and a succession of brake disks disposed between the stator central portion and the rotor annular portion with alternate disks being constrained to rotate with one and the other of said portions, said stator central portion being provided with a brake collar equipped with a plurality of sets of pistons and, rigidly secured to said collar, a torsion tube internally provided with a transverse annular web, a centering bearing being interposed between the annular web and the axle. According to the invention the centering bearing has structural characteristics that vary circumferentially in a distribution configuration suitable for generating different bearing stiffnesses along two orthogonal axes contained in a plane that is perpendicular to the axis of the axle.

Abstract: The invention relates to a brake system for braking aircraft wheels, the brake system being of the type which, for each wheel, comprises a stator central portion coaxially surrounding a wheel axle on which a rotor annular portion is mounted to rotate, and a succession of brake disks disposed between the stator central portion and the rotor annular portion with alternate disks being constrained to rotate with one and the other of said portions, said stator central portion being provided with a brake collar equipped with a plurality of sets of pistons and, rigidly secured to said collar, a torsion tube internally provided with a transverse annular web, a centering bearing being interposed between the annular web and the axle. According to the invention the centering bearing has structural characteristics that vary circumferentially in a distribution configuration suitable for generating different bearing stiffnesses along two orthogonal axes contained in a plane that is perpendicular to the axis of the axle.

Abstract: The invention relates to an arrangement of carbon brake disks for an aircraft brake unit comprising stators coupled to a torsion tube alternating with rotors coupled to the corresponding wheel. The arrangement is organized in two configurations corresponding to operation over two successive wear strokes of the pistons of the brake ring, with a first of the configurations comprising a central group of rotors and stators arranged between a front lateral stator and a rear lateral stator, and with a second of the configurations comprising the same front lateral stator and the same rotors and stators of the central group, but arranged between a spacer disk of thickness less than the wear stroke of the pistons, and a new rear lateral stator of thickness greater than that of the preceding rear lateral stator.