Abstract: An aircraft includes a brake lever for receiving a pilot braking input as a lever travel of the brake lever, a braking wheel operatively coupled with the brake lever to brake the aircraft based on the lever travel, a brake actuator operatively coupled with the braking wheel to apply a braking force in response to a braking pressure provided to the brake actuator, and a brake pressure circuit. The brake pressure circuit is configured for: estimating a maximum braking pressure above which the braking wheel will skid with respect to a ground surface; scaling a lever gain of the brake lever to command the maximum braking pressure at a full travel of the brake lever such that a remaining brake lever travel indicates the amount of braking capability remaining for the aircraft; and braking the braking wheel based on the lever gain and the lever travel.

Abstract: An aircraft includes a first landing gear assembly, a second landing gear assembly, a braking circuit, a brake control circuit, and a braking capability circuit. The landing gear assemblies each include a first braking wheel and a second braking wheel. The braking circuit may apply brakes independently to each of the braking wheels. The brake control circuit actuates braking of the first braking wheels in response to initial receipt of a braking command in a first braking phase and restrict braking at the second braking wheels during the first braking phase until the first braking wheels reach an anti-skid limit at an end of the first braking phase. The braking capability circuit determines a braking capability of the aircraft based on an amount of braking applied to reach the anti-skid limit at the first braking wheels.

Abstract: The aircraft take-off awareness system predicts and informs the pilot about where on the runway certain safety speeds will be achieved. A processor coupled to receive inertial data from the aircraft computes an aircraft weight estimate based at least in part upon the inertial data. The processor then computes a future acceleration prediction based on the computed aircraft weight estimate. Using the future acceleration prediction, the processor then computes the position of various warning reference distances corresponding to predicted positions on the runway at which said certain safety speeds will be achieved. The processor generates a display that it dynamically updates as the reference distances change as the aircraft proceeds down the runway during take-off or aborted take-off.

Abstract: The aircraft take-off awareness system predicts and informs the pilot about where on the runway certain safety speeds will be achieved. A processor coupled to receive inertial data from the aircraft computes an aircraft weight estimate based at least in part upon the inertial data. The processor then computes a future acceleration prediction based on the computed aircraft weight estimate. Using the future acceleration prediction, the processor then computes the position of various warning reference distances corresponding to predicted positions on the runway at which said certain safety speeds will be achieved. The processor generates a display that it dynamically updates as the reference distances change as the aircraft proceeds down the runway during take-off or aborted take-off.

Abstract: An aircraft includes a first landing gear assembly, a second landing gear assembly, a braking circuit, a brake control circuit, and a braking capability circuit. The landing gear assemblies each include a first braking wheel and a second braking wheel. The braking circuit may apply brakes independently to each of the braking wheels. The brake control circuit actuates braking of the first braking wheels in response to initial receipt of a braking command in a first braking phase and restrict braking at the second braking wheels during the first braking phase until the first braking wheels reach an anti-skid limit at an end of the first braking phase. The braking capability circuit determines a braking capability of the aircraft based on an amount of braking applied to reach the anti-skid limit at the first braking wheels.

Abstract: An aircraft includes a brake lever for receiving a pilot braking input as a lever travel of the brake lever, a braking wheel operatively coupled with the brake lever to brake the aircraft based on the lever travel, a brake actuator operatively coupled with the braking wheel to apply a braking force in response to a braking pressure provided to the brake actuator, and a brake pressure circuit. The brake pressure circuit is configured for: estimating a maximum braking pressure above which the braking wheel will skid with respect to a ground surface; scaling a lever gain of the brake lever to command the maximum braking pressure at a full travel of the brake lever such that a remaining brake lever travel indicates the amount of braking capability remaining for the aircraft; and braking the braking wheel based on the lever gain and the lever travel.