The B. F. Goodrich Company

Goodrich Corporation

John Joseph Enright

William Terry Holzworth

Jerry Miller

Joshua Craig Houser

Louis C Hrusch

Charles Wheater

Jerry L Miller

A brake stack comprises a stator having an annular, inner periphery section disposed substantially along a first radial plane extending normal to an axis of a wheel, and a stator side wall having a first stator contact surface, the first stator contact surface including a sloped portion which deviates away from the radial plane defined by the annular, inner periphery section. The brake stack further comprises a rotor having an annular, outer periphery section disposed substantially along a second radial plane extending normal to the axis of the wheel, and a rotor side wall having a first rotor contact surface shaped complementary to the first stator contact surface, wherein the stator and the rotor are interleaved. A brake disk may comprise a first radius of a friction surface at a first axial position and a second radius of the friction surface at a second axial position, where the first radius is different than the second radius. The brake disk may further comprise an axis of rotation orthogonal to a plane of rotation, wherein the brake disk rotates substantially in the plane of rotation, and wherein the friction surface is at an acute angle to the plane of rotation. An aircraft brake system comprises an aircraft rotor oriented orthogonally with respect to an axis of rotation and an aircraft stator configured to nest with the aircraft rotor, where a stator friction surface is non-orthogonal to the axis of rotation. The aircraft brake system may further comprise a pressure plate and an end plate configured to nest with the aircraft rotor and/or aircraft stator, and an actuator may be utilized to effectuate braking of the aircraft braking system.

Tapered brake disk

A wheel and brake assembly () having a torque bar () supported at a mid-span location. The torque bar () can be pre-loaded at a mid-span location. The pre-load can be effected by a spacer block () that is interposed between the wheel well and the torque bar (). The method and device of the present invention can be used with existing wheel and brake assemblies. The spacer block can be a two-part spacer block.

Wheel and brake assembly

The invention relates to the field of damping in load-carrying members, particularly those load-carrying members that carry a load between a plurality of masses that are subject to induced cyclic distortion or vibration. According to an aspect of the invention, a damped structural member is provided that carries a load between a first mass and a second mass. The damped structural member comprises a load-carrying member that carries the load between the first and second masses, and at least one damping member nested with the load-carrying member. The damping member and the load-carrying member move relative to each other during cyclic distortion of the load-carrying member thereby dissipating distortion energy at a damping interface between the damping member and the load-carrying member. The damping member bears essentially only cyclic loads induced by cyclic bending mode movement of load-carrying member. A method for damping a structural member is also provided.

Nested damping device with relative motion

The invention is in the field of dynamometer testing of aircraft wheel and brake assemblies and, more particularly, relates to the simulation of brake and landing gear vibration dynamics on a dynamometer. The test apparatus and method according to the invention employ a pitch beam that simulates bogie pitch motion, and a walk beam that simulates landing gear walk.

Dynamometer test apparatus for aircraft brakes

The invention relates to the field of braking systems, particularly those braking systems that utilize linkages to transmit brake-generated loads from a wheel and brake assembly to a braked vehicle. According to an aspect of the invention, a damped brake rod is provided for attachment to a structure, the structure having at least one wheel and brake assembly. The damped brake rod comprises a rod-like member for attachment to the brake assembly and the structure to resist rotation of the brake assembly relative to the structure, and a bending mode coulomb damper attached to the brake rod that damps cyclic bending mode movement of the rod-like member during braking. The bending mode coulomb damper bears essentially only cyclic loads induced by cyclic bending mode movement of the rod-like member generated during braking. A method of damping a brake rod is also provided.

Brake rod having a bending mode coulomb damper

The invention is directed to a damped brake rod for use in an aircraft landing gear, the landing gear comprising a strut and a wheel and brake assembly carried on the strut. The brake rod connects the wheel and brake assembly to the strut and bears an axial load during braking. The brake rod is laterally damped to dissipate lateral vibrations imparted to the brake rod during braking.

Aircraft braking system with damped brake rod

A method for making a rotor for a caliper brake with a disc mounted on a cylindrical adaptor. The disc includes a coiled metal strip having a rectangular cross section with edge surfaces aligned to provide friction faces for engagement by friction lining carriers of the brake while decreasing the vibration and noise during braking. The ends of the coiled strip are welded to the disc and the overlapping surfaces of the coils are brazed together.

Method of making a caliper brake rotor

A rotor for a caliper brake with a disc mounted on a cylindrical adaptor. The disc includes a coiled metal strip having a rectangular cross section with edge surfaces aligned to provide friction faces for engagement by friction lining carriers of the brake while decreasing the vibration and noise during braking.

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Troy, OH, United States of America

John Joseph Enright