System and methods for implementing regional air transit network using hybrid-electric aircraft

A flight control system for an aircraft, the aircraft having a plurality of electric propulsors distributed laterally relative to a longitudinal axis of the aircraft, the flight control system comprising:

• (a) a flight control interface to receive a pilot or autopilot input;
• (b) at least one sensor to provide aircraft state data, the aircraft state data including at least data indicative of an attitude of the aircraft derived from the at least one sensor;
• and
• (c) a Powertrain Optimization and Control System (POCS) communicatively coupled to the flight control interface, the at least one sensor and the plurality of electric propulsors, the POCS to receive the pilot or autopilot input and the aircraft state data, and in response, provide primary or supplemental aircraft control by allocation of a power command across the plurality of electric propulsors to produce a differential thrust moment.

A method for providing flight control for an aircraft, the aircraft having a plurality of electric propulsors distributed laterally relative to a longitudinal axis of the aircraft, the method comprising:

• (a) receiving, at a Powertrain Optimization and Control System (POCS), a pilot or autopilot input from a flight control interface;
• (b) receiving, at the POCS, aircraft state data derived from at least one sensor, the aircraft state data including at least data indicative of an attitude of the aircraft;
• and
• (c) in response to the pilot or autopilot input and the data, providing, by the POCS, primary or supplemental aircraft control by allocating a power command across the plurality of electric propulsors to produce a differential thrust moment.

A non-transitory computer-readable medium storing computer-readable instructions that, when executed by one or more processors of a Powertrain Optimization and Control System (POCS) of an aircraft, the aircraft having a plurality of electric propulsors distributed laterally relative to a longitudinal axis of the aircraft, to:

• (a) obtain a pilot or autopilot input received from a flight control interface;
• (b) obtain aircraft state data derived from at least one sensor, the aircraft state data including at least data indicative of an attitude of the aircraft;
• and
• (c) in response to the pilot or autopilot input and the aircraft state data, provide primary or supplemental aircraft control by allocation of a power command across the plurality of electric propulsors to produce a differential thrust moment.