Abstract: A system and a method for generating a signal to control a steering mechanism and an aircraft using the system are disclosed. A tiller module includes a moveable tiller base configured to moveably respond to a steering signal. The tiller module also includes a tiller coupling configured to couple the tiller with the moveable tiller base and further configured to generate a tiller differential signal indicative of a steering force applied to the tiller relative to a position of the moveable tiller base. A tiller controller is configured to receive the tiller differential signal and a steering mechanism position signal. The tiller controller is further configured to generate the steering signal to direct a steering mechanism to conform with the steering force and to direct the moveable tiller base of each tiller module to a feedback position representative of a current position of the steering mechanism.

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 method for measuring resistance of an electromagnetic servovalve associated with a brake torque limiting control system. The servovalve is controlled by two parallel connected controllers, one a current driver controller and the other a voltage driver controller whose output is dependent upon the resistance value being measured. The method includes a short series of sequential steps and computation executed by the voltage driver controller.

Abstract: An aircraft automatic braking system having a signal processor (20) for generating an autobrake valve control current (320) in response to deceleration selection switching means (30), main landing gear air/ground sensing switching means (60), and an inertial reference system (140) to control and limit the level of deceleration produced in the aircraft automatic braking system during the period after landing touchdown on the main gear and prior to nose-gear touchdown.

Abstract: Left and right main gear wheel speed signals are processed by a circuit which is a model of aircraft rigid body motion to provide a synthesized nose wheel velocity representative signal.

Abstract: Left and right main gear wheel speed signals are processed by a circuit which is a model of aircraft rigid body motion to provide a synthesized nose wheel velocity representative signal.