Electric distributed propulsion with different rotor rotational speeds
An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.
1. An electric distributed propulsion system, the system comprising:
a plurality of motors controlled by speed, wherein the plurality of motors comprise a first pair of motors and a second pair of motors;
an input control connected to the plurality of motors to provide control to the plurality of motors to produce a desired net thrust;
a logic connected to the input control and the plurality of motors, the logic for controlling the plurality of motors with different rotational speeds to achieve the desired net thrust and to avoid a motor speed condition by operating the first pair of motors in a first direction and operating the second pair of motors in a second direction;
wherein the electric distributed propulsion system is an anti-torque system in a helicopter;
wherein the motor speed condition comprises at least one of:
a speed dead band of the plurality of motors;
separating a tonal frequency of each of the plurality of motors by varying the rotational speed of each of the plurality of motor's speed to achieve a preferred overall acoustic signature;
a resonant frequency of the plurality of motors; and
a resonant frequency of a structure connected to the plurality of motors.
2. The system of claim 1 , wherein none of the plurality of motors is operated at a motor speed within the speed dead band.
3. The system of claim 1 , wherein one or more of the plurality of motors is operated at a first rotational speed that is different from the motor speed condition and another one or more of the plurality of rotors is operated at a second rotational speed that is different from the motor speed condition.
4. A helicopter, the helicopter comprising:
a main rotor;
an anti-torque system comprising a plurality of rotors that are individually controlled by motor speed of associated motors, wherein the plurality of rotors comprise a first pair of rotors and a second pair of rotors;
an input control connected to the associated motors to provide control to the plurality of rotors to produce a desired net thrust; and
a logic connected to the input control and the associated motors, the logic for controlling rotational speed of the plurality of rotors to achieve the desired net thrust and to avoid a motor speed condition by operating the first pair of rotors in a first direction and operating the second pair of rotors in a second direction;
wherein the motor speed condition comprises at least one of:
a speed dead band of the associated motors;
separating a tonal frequency of each of the plurality of rotors by varying the rotational speed to achieve a preferred overall acoustic signature;
a resonant frequency associated with the plurality of rotors; and
a resonant frequency of a structure connected to the plurality of rotors.
5. The helicopter of claim 4 , wherein none of the plurality of rotors is operated at a motor speed within the speed dead band.
6. The helicopter of claim 4 , wherein one or more of the plurality of rotors is operated at a first rotational speed that is different from the motor speed condition and another one or more of the plurality of rotors is operated at a second rotational speed that is different from the motor speed condition.
7. A helicopter comprising:
a main rotor;
an anti-torque system comprising a plurality of rotors that are individually controlled by motor speed of associated motors, wherein the plurality of rotors comprise a first pair of rotors and a second pair of rotors;
an input control connected to the associated motors to provide control to the plurality of rotors to produce a desired net thrust;
a logic connected to the input control and the associated motors, the logic for controlling rotational speed of the plurality of rotors to achieve the desired net thrust and to avoid a motor speed condition by operating the first pair of rotors in a first direction and operating the second pair of rotors in a second direction; and
wherein the motor speed condition comprises a speed dead band of the associated motors.
8. The helicopter of claim 7 , wherein none of the plurality of rotors is operated at a motor speed within the speed dead band.
9. The helicopter of claim 7 , wherein one or more of the plurality of rotors is operated at a first rotational speed that is different from the motor speed condition and another one or more of the plurality of rotors is operated at a second rotational speed that is different from the motor speed condition.