Electric distributed propulsion anti-torque redundant power and control system

An anti-torque system for a helicopter comprising:

• two or more generators connected to a main gearbox transmission;
• at least a first and a second plurality of variable speed motors connected to the two or more generators, wherein the first and second plurality of variable speed motors is arranged in a first matrix pattern and mounted on a tail boom of the helicopter, wherein each of the first plurality of variable speed motors is connected to one or more fixed pitch blades attached to each of the plurality of first variable speed motors that provide anti-torque thrust;
• at least a first and a second yaw control computer independently connected to each of the at least first and second plurality of variable speed motors, wherein each of the first and second yaw control computer serves as a primary and a backup yaw control computer to provide redundant control to both the first and second plurality of variable speed motors;
• and
• a logic in a flight control computer for controlling at least one of:
• the speed, the direction, or both the speed and direction, of the one or more of the plurality of first variable speed motors to reduce or eliminate torque from a main rotor.

A method of operating a helicopter, the method comprising:

• providing two or more generators connected to a main gearbox transmission;
• connecting at least a first and a second plurality of variable speed motors arranged in a first matrix pattern and mounted on a tail boom of the helicopter, wherein each of the first plurality of variable speed motors is connected to one or more fixed pitch blades attached to each of the plurality of first variable speed motors that provide anti-torque thrust;
• and
• independently connecting at least a first and a second yaw control computer to each of the at least first and second plurality of variable speed motors, wherein each of the first and second yaw control computer serves as a primary and a backup yaw control computer to provide redundant control to both the first and second plurality of variable speed motors.

A helicopter comprising:

• two or more generators connected to a main gearbox transmission;
• at least a first and a second plurality of variable speed motors arranged in a first matrix pattern and mounted on a tail boom of the helicopter, wherein each of the first plurality of variable speed motors is connected to one or more fixed pitch blades attached to each of the plurality of first variable speed motors that provide anti-torque thrust;
• and
• at least a first and a second yaw control computer independently connected to each of the at least first and second plurality of variable speed motors, wherein each of the first and second yaw control computer serves as a primary and a backup yaw control computer to provide redundant control to both the first and second plurality of variable speed motors;
• and
• wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.