Abstract: A method and a system are disclosed for detecting, isolating and estimating a degradation of a corresponding component of an actuator controlled by an actuator command signal, the method comprising obtaining a control signal of the actuator; obtaining a signal indicative of a displacement of the actuator; computing an envelope of admissible values for the displacement of the actuator; determining if the displacement of the actuator is outside the computed envelope and in the case where the displacement of the actuator is outside the computed enveloped computing an estimation of each parameter and state of the actuator; identifying at least one corresponding parameter responsible for causing the actuator displacement to be outside the computer envelope and providing an indication of the at least one corresponding parameter.

Abstract: A method and system for determining an estimation of an anemometric parameter of an aircraft. The anemometric parameter including an angle of attack, a sideslip angle and a calibrated airspeed. The method including obtaining an indication of a secondary surface state of the aircraft; obtaining a position indication of a horizontal primary surface; obtaining a load applied estimation on a corresponding actuator using the position indication of the horizontal primary surface and the position of the corresponding actuator; accessing a lookup table with the indication of the secondary surface state of the aircraft, the load estimation applied on the corresponding actuator, and the position of the corresponding actuator; obtaining an estimation of the anemometric parameter associated with the horizontal primary surface; providing the estimation of the anemometric parameter associated with the horizontal primary surface and wherein the lookup table is generated during a learning phase.

Abstract: A method and a system are disclosed for detecting, isolating and estimating a degradation of a corresponding component of an actuator controlled by an actuator command signal, the method comprising obtaining a control signal of the actuator; obtaining a signal indicative of a displacement of the actuator; computing an envelope of admissible values for the displacement of the actuator; determining if the displacement of the actuator is outside the computed envelope and in the case where the displacement of the actuator is outside the computed enveloped computing an estimation of each parameter and state of the actuator; identifying at least one corresponding parameter responsible for causing the actuator displacement to be outside the computer envelope and providing an indication of the at least one corresponding parameter.

Abstract: A method and system for determining an estimation of an anemometric parameter of an aircraft. The anemometric parameter including an angle of attack, a sideslip angle and a calibrated airspeed. The method including obtaining an indication of a secondary surface state of the aircraft; obtaining a position indication of a horizontal primary surface; obtaining a load applied estimation on a corresponding actuator using the position indication of the horizontal primary surface and the position of the corresponding actuator; accessing a lookup table with the indication of the secondary surface state of the aircraft, the load estimation applied on the corresponding actuator, and the position of the corresponding actuator; obtaining an estimation of the anemometric parameter associated with the horizontal primary surface; providing the estimation of the anemometric parameter associated with the horizontal primary surface and wherein the lookup table is generated during a learning phase.