Abstract: A system for controlling the torque developed by a fluid actuated brake as it slows an aircraft wheel. In one embodiment, the system includes a strain gauge (62) for sensing the load applied to a brake metering valve (16). In another embodiment, the pressure of the hydraulic fluid output from the brake metering valve is sensed by a pressure transducer (42). Depending upon the sensor used, the system is operative to control the pressure applied to a brake assembly (54) of an aircraft as a function of the mechanical load or pressure. The system includes a torque control (50,120) connected to control one or more valves (22, or 83 and 102), modulating the pressure of hydraulic fluid applied to the brake assembly; the valves may be part of an antiskid control system. A torque sensor (46) is disposed on a torque reaction arm (36) and produces a signal indicative of the torque developed by the brake assembly.

Abstract: A brake control system particularly suited for use on aircraft having hydraulically applied carbon disc brakes.Braking is controlled by displacing a foot pedal. A first transducer, connected to the pedal, measures the magnitude of displacement and produces a first electrical signal. A second transducer, connected to wheel means, measures the speed of the wheel means during braking and produces a second electrical signal. The first and second electrical signals are transmitted to control circuit means which compares them. If the second signal indicates that wheel means deceleration is not substantially proportional to foot pedal displacement, the control circuit means sends a control signal to electrically operate a pressure control valve which meters hydraulic fluid pressure to operate the brakes such that wheel means deceleration is substantially directly proportional to foot pedal displacement.

Abstract: An airplane braking system includes a torque control circuit for control torque developed in a braked landing wheel. The torque control circuit is responsive to a torque signal from a transducer located in the torque equalizing links of the landing gear assembly. The torque signal is compared with a reference signal and passed through an integrator, a differentiator and proportional gain amplifier in the torque control circuit to provide a torque control signal. The torque control signal is applied to a brake pressure relief valve to reduce brake pressure. The torque control circuit is advantageously integrated with an antiskid circuit responsive to wheel speed to thereby preventskidding as well as excessive torque conditions.

Abstract: A limited-slip brake control system includes a basic deceleration control circuit responsive to a wheel deceleration signal and to a selected reference deceleration signal to provide a first brake control signal which is used to modulate brake pressure applied to a braked wheel of a vehicle in order to maintain the vehicle deceleration at a selected reference deceleration representing a level of brake force generally lying in the nonslip portion of a characteristic Mu/slip curve for the vehicle.