Abstract: A system and method of controlling aircraft brakes in an aircraft that includes a brake pedal and an electric brake actuator. An aircraft operational state is determined and an application force that is supplied to the brake pedal is determined. When the determined aircraft operational state is a ground-idle state and the determined application force is greater than a set force magnitude, an actuator brake is moved to engage the electric brake actuator and the electric brake actuator is de-energized.

Abstract: An aircraft brake system electromechanical actuator is provided. The actuator is configured with features that allow the electric motor to be a line replaceable unit. One such feature is a foreign-object-damage shield that inhibits dust, debris, and/or other particulate contaminants from entering the electromechanical actuator during electric motor removal and replacement.

Abstract: A system and method of controlling aircraft brakes in an aircraft that includes a brake pedal and an electric brake actuator. An aircraft operational state is determined and an application force that is supplied to the brake pedal is determined When the determined aircraft operational state is a ground-idle state and the determined application force is greater than a set force magnitude, an actuator brake is moved to engage the electric brake actuator and the electric brake actuator is de-energized.

Abstract: An aircraft brake system electromechanical actuator is provided. The actuator is configured with features that allow the electric motor to be a line replaceable unit. One such feature is a foreign-object-damage shield that inhibits dust, debris, and/or other particulate contaminants from entering the electromechanical actuator during electric motor removal and replacement.

Abstract: The present invention pertains to carbon-carbon composites what are reinforced with PAN-based carbon fibers and which have an all pyrocarbon matrix deposited via chemical vapor infiltration and/or chemical vapor deposition. The uniquely low wear life of the C—C composites of this invention is achieved via a high initial heat treatment of the preforms made from PAN-based carbon fibers—providing a high modulus to the fibers, making them less abrasive—followed by CVI/CVD of the pyrocarbon matrix. No final heat treatment is needed to achieve the balance of hardness in the fiber and matrix. The composites of the present invention do not have pitch-based fibers or matrices nor do they have resin-based matrices.