Abstract: A system and method for verifying the response capabilities of a control effector include processing, in a test module, at least command data and sensor data associated with the control effector to generate control effector health data representative of control effector health. The control effector health data are processed in a reasoner to selectively indict and clear one or more faults, determine a failure is uncertain based on the one or more indicted faults, determine one or more test excitation signals to supply to the control effector to verify whether the uncertain failure is present or absent, and supply the one or more test excitation signals to a controller that is in operable communication with the control effector.

Abstract: Systems and methods for airspeed estimation using actuation signals are provided. In one embodiment, an on-board avionics airspeed estimation system is provided. The system comprises: a flight control surface for an aircraft; a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and drives the flight control surface into a position based on the actuator control output signal; a wind estimator coupled to a plurality of aircraft sensors, wherein the plurality of aircraft sensors output a set of aircraft measurements to the wind estimator and wherein the actuator control output signal is further provided to the wind estimator; wherein the wind estimator calculates a wind speed estimate by applying the actuator control output and the set of aircraft measurements to an onboard aircraft model.

Abstract: A diagnostic method performed onboard an aircraft is provided. The method obtains aircraft state data during landing of the aircraft, via a plurality of avionics and aircraft systems; and determines a landing surface friction condition based on the aircraft state data, using at least one of the plurality of avionics and aircraft systems. A method of evaluating landing surface data onboard an aircraft is also provided. The method receives landing surface friction condition data, prior to landing; computes a required landing distance, based on the received landing surface friction condition data; and when the required landing distance is more than a predetermined threshold, performs a designated task.

Abstract: Systems and methods for airspeed estimation using actuation signals are provided. In one embodiment, an on-board avionics airspeed estimation system is provided. The system comprises: a flight control surface for an aircraft; a control surface actuator coupled to the flight control surface, wherein the control surface actuator receives an actuator control output signal from an actuator control system and drives the flight control surface into a position based on the actuator control output signal; a wind estimator coupled to a plurality of aircraft sensors, wherein the plurality of aircraft sensors output a set of aircraft measurements to the wind estimator and wherein the actuator control output signal is further provided to the wind estimator; wherein the wind estimator calculates a wind speed estimate by applying the actuator control output and the set of aircraft measurements to an onboard aircraft model.

Abstract: A system and method for verifying the response capabilities of a control effector include processing, in a test module, at least command data and sensor data associated with the control effector to generate control effector health data representative of control effector health. The control effector health data are processed in a reasoner to selectively indict and clear one or more faults, determine a failure is uncertain based on the one or more indicted faults, determine one or more test excitation signals to supply to the control effector to verify whether the uncertain failure is present or absent, and supply the one or more test excitation signals to a controller that is in operable communication with the control effector.