Abstract: Torque tubes with better total failure performance is provided. The torque tube comprises a plurality of reinforcement members made from a second material with a higher temperature strength than the first material. In preferred embodiments, the reinforcement members are tungsten rods. The reinforcement members are located concentrically around a central axis of the torque tube and each reinforcement member spans a center line of a central tube of the torque tube and spans a majority of a longitudinal length of the torque tube. In preferred embodiments, the reinforcement members are drive keys.

Abstract: A torque tube and conical back plate for aircraft brakes including a torque tube having a truncated back plate of thin metal construction extending from the outboard end thereof. The conical back plate is characterized by inner and outer reinforcing rings, such rings providing a compressive force at opposite ends of the truncated cone of the back plate, thus allowing the back plate to resist bending and deflection. In accordance with the invention, the cross sectional centers of mass of the inner and outer reinforcing rings are shifted outboard from a projection of the center plane of the conical back plate, such positioning enhancing the stiffening and reinforcing capabilities of the reinforcing rings.

Abstract: A torque tube and conical back plate for aircraft brakes including a torque tube having a truncated back plate of thin metal construction extending from the outboard end thereof. The conical back plate is characterized by inner and outer reinforcing rings, such rings providing a compressive force at opposite ends of the truncated cone of the back plate, thus allowing the back plate to resist bending and deflection. In accordance with the invention, the cross sectional centers of mass of the inner and outer reinforcing rings are shifted outboard from a projection of the center plane of the conical back plate, such positioning enhancing the stiffening and reinforcing capabilities of the reinforcing rings.

Abstract: A metallic aircraft brake disk having thermal relief slots therein is provided. The brake disk is of an annular shape with force bearing slots in one of the circumferential surfaces thereof to engage the disk with a portion of the aircraft. A plurality of thermal relief slots extend from an opposite circumferential surface of the annular brake disk. The thermal relief slots are in the shape of a dual armed hook anchors and are configured to minimize the amount of material removed to form each slot, while maximizing certain radii of the slot head. Particularly, an elongated radial slot terminates in a slot head, the slot head being formed of a number of interconnected curvate surfaces. The radii of the curvate surface opposite the end of the radial slot is maximized.

Abstract: Brake disc assemblies and methods for making the same which allow for increased carbon utilization. In one embodiment of the invention, worn or spent discs from a carbon brake disc assembly are used to fabricate new brake discs. The separate discs, individually unsuited for further use in a brake assembly, are secured together with like wear material and subjected to chemical vapor infiltration to configure a disc suitable for use as a new disc. In other embodiments, previously used discs or new carbon material is employed to configure wear pads or wear discs which are affixed to opposite sides of a carrier plate and then subsequently used in a brake disc assembly. In all of the embodiments, carbon screws or threaded rods are employed to hold the components of the disc together. Such carbon screws or threaded rods are fabricated from otherwise worn or spent carbon discs or from new carbon.

Abstract: A torque tube for an aircraft wheel and brake assembly is characterized by an annular, substantially cone-shaped, radially-extending backplate flange having a plurality of stiffening ribs which extend axially inboardly as radial extensions of various key surfaces, the key surfaces being adapted for engagement with alternating disks of a brake disk stack of the assembly. The stiffening ribs exhibit an axial dimension as may be defined by a pair of acute angles, a first acute angle establishing an outboard straight line surface of revolution which is continuous about the outboard end of the tube while a second acute angle establishes an inboard straight line surface of revolution in only the areas of the stiffening ribs. The backplate flange exhibits an axial dimension between the ribs as may be defined by a third acute angle which establishes a straight line surface of revolution between the adjacent ribs.