Methods and systems for flight control configured for use in an electric aircraft

A system for flight control configured for use in an electric aircraft, the system comprising:

• at least one sensor attached to at least one flight component and configured to detect signal datum from the at least one flight component;
• an inertial measurement unit, the inertial measurement unit configured to:
• detect at least an aircraft angle;
• and
• detect at least an aircraft angle rate;
• and
• a flight controller configured to generate an autonomous function, the flight controller comprising:
• an outer loop controller, the outer loop controller configured to:
• receive at least an input datum;
• receive at least the aircraft angle from the inertial measurement unit;
• and
• generate a rate setpoint as a function of at least the input datum;
• an inner loop controller, the inner loop controller configured to:
• receive at least the aircraft angle rate;
• receive the rate setpoint from the outer loop controller;
• and
• generate a moment datum as a function of the rate setpoint;
• and
• a mixer, the mixer configured to:
• receive the moment datum from the inner loop controller;
• receive the signal datum from the at least one sensor;
• perform a torque allocation as a function of the moment datum and the signal datum;
• and
• generate at least a motor command datum as a function of the torque allocation.