Adaptive Phase Control Architecture for Reduction of Community Noise from Distributed Propulsion Vehicles

A phase generator module for use in adaptive phase control of a distributed propulsion (DP) aircraft having a flight controller configured, responsive to a set of optimized relative phase angles, to output corresponding phase commands to propulsors of the DP aircraft, the phase generator module comprising:

• a source noise generator block configured to derive an estimated source noise level of the propulsors using an acoustic model;
• a noise propagator block configured, in response to the estimated source noise level, to estimate a ground noise level of the propulsors in a predetermined low-noise area located on a ground plane proximate a flight path of the DP aircraft;
• and
• a phase optimizer block configured to determine the optimized set of relative phase angles using an optimizer function, wherein the optimized set of relative phase angles is sufficient for minimizing the estimated ground noise level at a plurality of observer locations on the ground plane, and to transmit the optimized set of relative phase angles to the flight controller.

A distributed propulsion (DP) aircraft comprising:

• an aircraft body;
• a plurality of propulsors distributed with respect to each other and the aircraft body;
• a flight controller in communication with the propulsors and configured, responsive to a set of optimized phase angles, to output corresponding phase commands to the propulsors;
• and
• a phase generator module in communication with the flight controller and configured to:
• derive, in response to a set of input signals, an estimated source noise level of the propulsors with respect to a designated low-noise area located on a ground plane proximate a flight path of the DP aircraft;
• estimate a ground noise level at a plurality of observer locations, including generating individual ray paths between each of the propulsors and each of the observer locations to thereby account for atmospheric propagation effects on the estimated source noise level;
• responsive to the estimated ground noise level, determine an optimized set of relative phase angles of the propulsors, wherein the optimized set of relative phase angles is sufficient for reducing the estimated ground noise level;
• and
• transmit the optimized set of relative phase angles to the flight controller;
• wherein the flight controller is configured, responsive to the optimized set of relative phase angles, to establish the optimized set of relative phase angles via phase control of the propulsors.