Method and system for determining an estimation of an anemometric parameter in an aircraft

A system for determining an estimation of an anemometric parameter of an aircraft, the anemometric parameter selected from a group comprising at least one of an angle of attack, a sideslip angle and a calibrated airspeed, the system comprising:

• a state indication sensor, obtaining an indication of a state of at least one secondary surface of the aircraft and providing the indication of a state of at least one secondary surface of the aircraft;
• a load estimation controller receiving an indication of a position of a corresponding horizontal primary surface and a position of a corresponding actuator used for actuating the horizontal primary surface, the load estimation controller for providing an estimation of the load applied on the corresponding actuator used for actuating the horizontal primary surface of the aircraft using at least the indication of the position of the horizontal primary surface and the position of the corresponding actuator;
• a non-transitory storage medium comprising at least one lookup table for associating a given estimation of a load applied on a corresponding actuator, a given indication of the state of the at least one secondary surface, a corresponding position of the corresponding actuator with a corresponding estimation of the anemometric parameter;
• a processor receiving the estimation of the load applied on the corresponding actuator, the indication of the state of at least one secondary surface of the aircraft and the position of the corresponding actuator and accessing the at least one lookup table with the indication of the state of the at least one secondary surface of the aircraft, the estimation of the load applied on the corresponding actuator used for actuating the horizontal primary surface of the aircraft and the position of the corresponding actuator and obtaining a corresponding estimation of the anemometric parameter of the aircraft associated with the horizontal primary surface;
• the processor further providing the corresponding estimation of the anemometric parameter of the aircraft associated with the horizontal primary surface, the processor being operatively connected to each of the state indication sensor, the load estimation controller and the non-transitory storage medium;
• wherein the at least one lookup table is generated during a learning phase.

A non-transitory computer readable storage medium for storing computer-executable instructions which, when executed, cause a processor to perform a method for determining an estimation of an anemometric parameter of an aircraft, the anemometric parameter selected from a group comprising at least one of an angle of attack, a sideslip angle and a calibrated airspeed, the method comprising:

• obtaining, from at least one state indication sensor operatively connected to the processor, an indication of a state of at least one secondary surface of the aircraft;
• obtaining an indication of a position of a horizontal primary surface;
• obtaining an estimation of the load applied on a corresponding actuator used for actuating the horizontal primary surface of the aircraft using at least the indication of the position of the horizontal primary surface and the position of the corresponding actuator;
• primary surface of the aircraft, and the position of the corresponding actuator;
• computing a corresponding estimation of the anemometric parameter of the aircraft said computing comprising accessing at least one lookup table with the indication of the state of the at least one secondary surface of the aircraft, the estimation of the load applied on the corresponding actuator used for actuating the horizontal primary surface;
• providing the corresponding estimation of the anemometric parameter of the aircraft;
• and
• wherein the at least one lookup table is generated during a learning phase.