System and method for airspeed determination
A method for determining airspeed of an aircraft that includes determining a rotor model relating a power coefficient of a propeller of the aircraft to an axial inflow velocity through the propeller as a function of a set of rotor operating parameters; determining the set of rotor operating parameters by sampling an electronic control signal associated with an electric motor actuating the propeller; computing the axial inflow velocity through the propeller based on the set of rotor operating parameters using the rotor model; and determining the airspeed based on the axial inflow velocity.
1. An aircraft based system for determining airspeed, said system comprising:
an aircraft;
one or more rotor assemblies, the rotor assemblies comprising:
a propeller; and
an electric motor;
a control system housed within the aircraft, the control system configured to determine a set of rotor operating parameters by sampling an electronic control signal associated with an electric motor actuating a propeller, compute the axial inflow velocity through the propeller based on the set of rotor operating parameters using a rotor model, and compute the airspeed based on the axial inflow velocity to generate a first determined airspeed.
2. The system of claim 1 wherein said control system is further configured to measure the airspeed using an auxiliary airspeed measurement device to generate a second determined airspeed, compare the first determined airspeed to the second determined airspeed to generate a validation metric, and validate at least one of the first determined airspeed and the second determined airspeed to based on the validation metric.
3. The system of claim 1 wherein the control system is further configured to determine a second set of rotor operating parameters by sampling a second electronic control signal associated with a second electric motor actuating a second propeller, compute the second axial inflow velocity through the second propeller based on the second set of rotor operating parameters using the rotor model, wherein computing the airspeed comprises averaging the axial inflow velocity and the second inflow velocity to generate the first determined airspeed.
4. The system of claim 3 wherein the set of rotor operating parameters comprises a tilt angle of the propeller, and wherein the second set of rotor operating parameters comprises a second tilt angle of the second propeller, and wherein computing the airspeed further comprises dividing the axial inflow velocity by the cosine of the tilt angle and dividing the second axial inflow velocity by the cosine of the second tilt angle prior to averaging the axial inflow velocity and the second axial inflow velocity to generate the first determined airspeed.
5. The system of claim 1 wherein the set of rotor operating parameters comprises:
a blade pitch angle of each blade of the propeller;
a shaft torque applied to the propeller by the electric motor; and
an RPM value of the propeller.
6. The system of claim 5 wherein the set of rotor operating parameters further comprises a tilt angle of the propeller, and wherein computing the airspeed further comprises dividing the axial inflow velocity by the cosine of the tilt angle to generate the first determined airspeed.
7. The system of claim 1 wherein sampling the electronic control signal comprises sampling a feedback signal generated by the electric motor.