Distributed propulsion system

A method for distributed propulsion of an aircraft comprising:

• determining at least one of aerodynamics, propulsive efficiency, structural efficiency, and weight of the aircraft;
• selecting a number, size and type of hydraulic motors necessary to provide distributed propulsion for powered operations of the aircraft;
• and
• selecting a power source having sufficient energy density to power the hydraulic motors connected to constant pitch propellers to operate the aircraft;
• and
• providing a distributed propulsion system comprising:
• a frame;
• a plurality of variable displacement hydraulic motors disposed within or attached to the frame in a distributed configuration;
• a propeller operably connected to each of the variable displacement hydraulic motors;
• a source of hydraulic power disposed within or attached to the frame and coupled to each of the plurality of variable displacement hydraulic motors disposed within or attached to the frame, wherein the source of hydraulic power provides sufficient energy density for the aircraft to attain and maintain operations of the aircraft;
• a plurality of controllers, each controller coupled to the source of the hydraulic power, and to one of the variable displacement hydraulic motors via a mechanical shaft to control a speed and a torque of the variable displacement hydraulic motor by changing a displacement of the variable displacement hydraulic motor;
• and
• one or more processors communicably coupled to each controller that control an operation, the speed and the torque of the plurality of variable displacement hydraulic motors such that a pitch roll and yaw movement of the aircraft is controlled via differential and vectoring thrust without a rotor cyclic and collective controls.

An aircraft comprising:

• an airframe comprising one or more control surfaces;
• a plurality of variable displacement hydraulic motors disposed within or attached to the airframe in a distributed configuration;
• a constant pitch propeller operably connected to each of the variable displacement hydraulic motors;
• a source of hydraulic power disposed within or attached to the frame and coupled to each of the plurality of variable displacement hydraulic motors disposed within or attached to the airframe, wherein the source of hydraulic power provides sufficient energy density for the aircraft to attain and maintain operations of the aircraft;
• a plurality of controllers, each controller coupled to the source of the hydraulic power, and to one of the variable displacement hydraulic motors via a mechanical shaft to control a speed and a torque of the electric motor or the variable displacement hydraulic motor by changing a displacement of the variable displacement hydraulic motor;
• and
• one or more processors communicably coupled to each controller that control an operation, speed and the torque of the plurality of variable displacement hydraulic motors to attain and maintain flight such that a direction of the helicopter or aircraft is controlled via differential and vectoring thrust without a rotor cyclic and collective controls.

A method for distributed propulsion of an aircraft comprising:

• determining at least one of aerodynamics, propulsive efficiency, structural efficiency, and weight of the aircraft;
• selecting a number, size and type of variable displacement hydraulic motors necessary to provide distributed propulsion for powered operations of the aircraft;
• selecting a power source having sufficient energy density to power the variable displacement hydraulic motors connected to constant pitch propellers to operate the aircraft;
• and
• providing a distributed propulsion system comprising:
• an air frame;
• a plurality of variable displacement hydraulic motors disposed within or attached to the frame in a distributed configuration;
• a constant pitch propeller operably connected to each of the variable displacement hydraulic motors;
• a source of hydraulic power disposed within or attached to the frame and coupled to each of the plurality of variable displacement hydraulic motors disposed within or attached to the frame, wherein the source of hydraulic power provides sufficient energy density for the aircraft to attain and maintain operations of the aircraft;
• a plurality of controllers, each controller coupled to the source of the hydraulic power, and to one of the variable displacement hydraulic motors via a mechanical shaft to control a speed and a torque of the electric motor or the variable displacement hydraulic motor by changing a displacement of the variable displacement hydraulic motor;
• and
• one or more processors communicably coupled to each controller that control an operation the speed and torque of the plurality of variable displacement hydraulic motors via the controller to attain and maintain flight such that a direction of the helicopter or aircraft is controlled via differential and vectoring thrust without a rotor cyclic and collective controls.