System and method for aircraft noise mitigation
A system and method for reducing a psychoacoustic penalty of acoustic noise emitted by an aircraft, including a plurality of propulsion assemblies coupled to the aircraft, wherein each of the plurality of propulsion assemblies includes a motor, and a plurality of blades defined by a propeller, wherein the plurality of blades can define an asymmetric blade spacing; a control subsystem coupled to the aircraft and communicatively coupled to the motor of each of the plurality of propulsion assemblies, wherein the control subsystem is operable to rotate each of the plurality of propulsion assemblies at a different frequency to modulate the acoustic power distribution of the emitted acoustic signature.
1. A method for reducing a psychoacoustic penalty of acoustic noise emitted by an aircraft, comprising:
providing a plurality of propulsion assemblies, wherein each of the plurality of propulsion assemblies comprises:
a motor, and
a plurality of blades defined by at least a first propeller;
at an onboard control system of the aircraft, controlling the plurality of propulsion assemblies of the aircraft to generate thrust, wherein the plurality of propulsion assemblies generates an acoustic signature defining an acoustic power distribution, and wherein the plurality of propulsion assemblies generates a thrust distribution about the aircraft;
determining acoustic signature data at the onboard control system; and
controlling the acoustic power distribution of the acoustic signature, comprising simultaneously:
rotating each of the plurality of propulsion assemblies at different rotation frequencies based on the acoustic signature data, comprising increasing the rotation frequency of at least one of the plurality of propulsion assemblies, and
substantially maintaining the thrust distribution about the aircraft, comprising adjusting a pitch angle of each of the plurality of propulsion assemblies based on the respective rotation frequency.
2. The method of claim 1 , wherein the plurality of blades of each of the plurality of propulsion assemblies defines an asymmetric blade spacing.
3. The method of claim 2 , wherein the asymmetric blade spacing of the plurality of blades of each of the plurality of propulsion assemblies is identical.
4. The method of claim 2 , further comprising adjusting the asymmetric blade spacing of the plurality of blades of at least one of the plurality of propulsion assemblies during operation.
5. The method of claim 1 , wherein the rotation frequency of each of the plurality of propulsion assemblies is separated from the rotation frequency of at least one other of the plurality of propulsion assemblies by at least a predetermined threshold of at least 5% of the rotation frequency.
6. The method of claim 1 , further comprising receiving the acoustic signature data at the onboard control system from an acoustic sensor, and adjusting the rotation frequency of at least one of the plurality of propulsion assemblies based on the acoustic signature data.
7. The method of claim 6 , wherein the acoustic sensor is arranged at a ground-based infrastructure component.
8. The method of claim 6 , wherein the acoustic sensor is arranged at and coupled to the aircraft.
9. The method of claim 1 , further comprising modulating the thrust distribution based on the acoustic signature data in response to receiving a command instruction at the onboard control system.
10. The method of claim 1 , wherein the plurality of blades of least one propulsion assembly is further defined by a second propeller coaxial with the first propeller, and further comprising rotating the first propeller and second propeller in a same direction to generate thrust, wherein the first propeller is shifted by an azimuthal phase shift from the second propeller while rotating the first propeller and second propeller.
11. The method of claim 10 , further comprising adjusting the azimuthal phase shift based on the acoustic signature data.