Abstract: An inflation valve having overpressure protection has an inflation core which is coaxial with an exhaust port, both of which are coaxial with an exhaust plenum maintained within a body portion of the inflation valve. The inflation core communicates with a circular chamber which also communicates with radial passages extending within the base portion to an annular chamber which communicates with radial passages which interconnect with the wheel entry port. The exhaust plenum is sealed from the wheel entry port and the pressure of the associated tire by a rupture disk. Exhaust ports extend through the body portion of the valve from the exhaust plenum to atmosphere. When an overpressure condition exists within the tire, exceeding the characteristic pressure of the rupture disk, the rupture disk opens and allows the pressure within the tire envelope to escape through the wheel entry port, exhaust plenum, and exhaust ports.

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: An apparatus for making carbon discs for brake disc assemblies by feeding continuous strands of fibrous carbon material from spools into a die, the volume of the carbon material so dispensed being continuously monitored. A cutter terminates the dispensing operation and a debulking plate urges all of the fibrous carbon material so dispensed into the die alone. The material is compressed within a cylindrical annular die and, in one embodiment, is submitted to a convection curing oven where the preform is cured. Subsequently, the preform is carbonized, densified, and machined to form a final carbon disc brake. In another emobodiment, a dry preform is fabricated, obviating the need for curing and carbonizing.

Abstract: A brake disk for an aircraft brake assembly, the assembly comprising a multi-disk stack of alternating stator and rotor brake disks wherein each disk is comprised of a carbon composite material and a specific volume of a phase change material is encapsulated within the core of the disk between its brake wear faces and distributed so as to function to enhance brake energy capacity in the operation of the brake assembly.

Abstract: A wheel and brake assembly is provided for use with an aircraft. A landing gear strut depends from the aircraft and an axle is mounted to the strut. At least one brake assembly housing is mounted to the axle, on either side of the strut. One or more torque take-out pins are provided on the strut to be received in mating sockets provided in the brake assembly housing. Torque from the brake assembly housing is transferred to the strut or a stationary member by way of the pins and sockets. At least one tie rod member engages lug members provided on at least one brake assembly housing and the strut or stationary member. At least two brake assembly housings mounted on opposite sides of the strut may be interconnected by at least one tie rod member. Thus, the brake assembly housing is interconnected and may be drawn toward the strut or stationary member by selective adjustment of a turnbuckle incorporated into the tie rod member.

Abstract: A pressure balanced brake disc stack provides brake discs of greater thickness at the ends and center of the stack and of a lesser thickness at the areas in between the centrally disposed disc and the discs at the end of the stack. The increased thickness of the discs at the end of the stack prevent deflection or distortion of those discs to more evenly distribute the braking pressure applied thereto throughout the stack so as to provide a higher braking coefficient. Additionally, the unique configuration of the brake stack allows for effective heat dissipation at the discs adjacent to the end discs of the stack.

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.

Abstract: A thermally balanced brake disc stack provides brake discs of greater mass at the center of the stack and of lesser mass at the opposite ends of the stack. The temperature of the high mass discs in the center of the stack will rise to a lower level than the thinner discs at the ends of the stack. However, the heat dissipation rate at the ends of the stack exceeds that at the center of such that all of the discs cool to a predetermined temperature concurrently.

Abstract: This invention provides an improved aircraft wheel rim wherein a demountable tire bead flange has an annular chamfer within the outboard end of the flange bore, and a split lockring which cooperates to maintain the flange on the wheel rim body has an outer surface chamfer which matches the flange bore chamfer, the angle of the flange bore and lockring surface chamfers being determined by the coefficient of friction of the material comprising the wheel rim assembly such that a compressive wedge-locking load force exists at the chamfer joint as may be imposed by inflation of a rim-mounted tire.

Abstract: An electrical brake pressure limiter and controller is provided for negating the characteristic high amplitude initial torque peak of carbon brakes. The system sets an initial level of brake pressure and then controls the rate of growth of brake pressure to obtain smooth and efficient braking. A brake pedal transducer presents a signal to a microprocessor which is indicative of brake pedal position. The microprocessor compares this signal with an output signal to the brake and, dependent upon such comparison, it modifies the brake signal within controlled limits.

Abstract: A coupler interconnecting a wheel speed transducer with a rotating wheel of an aircraft. A cylindrical housing has a pair of orthogonal passages extending therethrough. One of such passages communicates with a slot within one end of the housing, the slot being adapted to slidingly receive a blade from a drive cap of the wheel. The other of the passages slidingly receives a member having a hub extending therefrom for engagement with the rotatable shaft of the wheel speed transducer. Various types of possible misalignment are accommodated and corrected by the capability of the blade to slide within the slot and of the member to slide within its passage. The coupler substantially eliminates backlash and accommodates high temperature operation.

Abstract: An aircraft deceleration brake control system receives deceleration command signals from left and right brake pedals of an aircraft. An amplifier generates the difference between the two command signals while an inertial navigation system of the aircraft provides a signal corresponding to the instantaneous deceleration of the aircraft. First and second control signals, corresponding to the respective command signals, are generated as a function of the difference in value between the command signals and the amplitude of the instantaneous deceleration signal.

Abstract: A dynamic wheel bearing test system employs a motor and fly wheel interconnected through a drive shaft and clutch or speed control with a wheel portion mounted upon a fixed axle with test bearings interposed therebetween. The drive shaft is received by and rotates within a load reaction block to which are connected hydraulic actuators operating in three orthogonal planes to impart loads to the bearings. A first set of actuators provides radial loads to the bearings, a second provides side loading of the bearings, while a third set of actuators simulates a drag upon the aircraft employing the wheel and bearings under test.

Abstract: The invention provides an integral brake disk comprised of two brake disks each having a disk thickness of one-half the design required disk thickness and these two disks are clamped together in planar face-to-face orientation by fasteners to form the integral brake disk. The integral brake disk has an inboard-facing brake wear surface provided by a wear surface of a first of the combined brake disks and an outboard-facing brake wear surface provided by the second of the combined brake disks. The integral brake disk is put into braking service for a first period after which refurbishment is required. The integral brake disk is refurbished by declamping the two disks and grinding the worn wear surfaces to planar specification. The two disks are recombined at the ground planar surfaces and reclamped to form a new integral brake disk.

Abstract: A telescopic brake piston includes a cylindrical housing and a pair of concentric pistons. A first hydraulic cavity is provided between an outer piston and the housing, while a second hydraulic cavity, communicating with a source requesting the application of brake force, communicates with both pistons. Passages in the outer piston allow the two cavities to communicate with each other. As the associated brake disc stack wears, the outer piston progressively extends from the housing as the passages are exposed by the inner piston. The actual brake force is attained by the inner piston alone.

Abstract: A generally cylindrical heat shield is provided for attachment to the wheel of an aircraft for encircling a brake disc stack. The cylindrical shield is configured from a plurality of interleaved arcuate sectors. The sectors are interconnected by means of a slip joint which allows each of the sectors a degree of lateral or circumferential movement with respect to each other to accommodate thermal expansion and contraction. Each of the sectors includes a plurality of layers, typically a pair of outer skins having an inner layer therebetween. A spaced relationship between the skins and the inner layer is maintained by spacers which laterally engage the skins, holding them in fixed spaced relationship, while allowing lateral movement at the spacers to accommodate thermal expansion and contraction. The inner layer is maintained in positional relationship with respect to the skins by spacers in one embodiment, or by detents in the skins engaging the layer in another.

Abstract: This invention provides brake clamping and declamping in response to a position feedback controlled brake actuator in which an electric torque motor drives a rotating member of a reciprocating drive mechanism to axially move another member into out of engagement with a brake pressure plate of a multi-disk brake assembly. A microprocessor controller receives electric signals indicative of (i) a pilot's command for braking, (ii) a command for brake release and antiskid braking, (iii) the position of the torque motor rotor at any instant, and (iv) the initiation of brake clamping of the multi-disk brake. The controller generates a feedback control signal to the torque motor which adjusts the motor rotor position, in revolutions, to increase or decrease brake clamping in accordance with the pilot signal and to effect brake release in accordance with an overriding antiskid signal.

Abstract: The invention is directed to a system for increasing and/or extending the operation service life of an aircraft brake disk stack by selectively limiting the number of brake assemblies which comprise the aircraft landing gear configuration and which are put into operation during the time the aircraft is on the ground and subject to low speed taxi braking cycles while also providing that all of the brake assemblies of the total available on the aircraft are operational during other portions of the landing and takeoff cycle of the aircraft.

Abstract: The invention is directed to a method of increasing and/or extending the operational service life of an aircraft brake disk stack by selectively limiting the number of brake assemblies which comprise the aircraft landing gear configuration and which are put into operation during the time the aircraft is on the ground and subject to taxi-snub braking cycles while also providing that all of the brake assemblies of the total available on the aircraft are operational during landing of the aircraft.