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: 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.