transdutor de força de frenagem para freios elétricos

An electric brake actuator (10) for the brake system of an aircraft includes a piston (28) driven by a cylindrical nut and screw arrangement (16,18), driven by an appropriate motor of the actuator. Application of brake force results in a reaction force that deflects the top cover (12) of the actuato...

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Bibliographische Detailangaben
Hauptverfasser:	KURT BURKHALTER, MICHAEL P. OSBURN, HAROLD R. BOOHER, KEVIN M. DALTON
Format:	Patent
Sprache:	por
Schlagworte:	AEROPLANES AIRCRAFT AVIATION BLASTING BRAKES CLUTCHES COSMONAUTICS COUPLINGS FOR TRANSMITTING ROTATION DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR ENGINEERING ELEMENTS AND UNITS FLUID-PRESSURE ACTUATORS FLUID-PRESSURE ACTUATORS, e.g. SERVO-MOTORS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HELICOPTERS HYDRAULICS OR PNEUMATICS IN GENERAL LIGHTING MECHANICAL ENGINEERING PERFORMING OPERATIONS SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	An electric brake actuator (10) for the brake system of an aircraft includes a piston (28) driven by a cylindrical nut and screw arrangement (16,18), driven by an appropriate motor of the actuator. Application of brake force results in a reaction force that deflects the top cover (12) of the actuator. The axial component of this deflection correlates directly with the brake force applied. A beam (38) is interposed between this cover (12) and a top cap (34), such that deflection of the beam correlates to applied brake force. Piezo-resistive devices are connected to the beam (38) and, through a Wheatstone bridge, provide an electrical output signal correlating to applied brake force.