Distributed propulsion system
The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.
1. A distributed propulsion system for an aircraft comprising:
a frame;
a plurality of hydraulic motors disposed within or attached to the frame in a distributed configuration;
a propeller operably connected to each of the hydraulic motors;
a source of hydraulic power disposed within or attached to the frame and coupled to each of the plurality of hydraulic motors disposed within or attached to the frame;
a plurality of hydraulic controllers, each hydraulic controller coupled to the source of hydraulic power, and connected to one of the hydraulic motors with a mechanical shaft to control a speed and a torque of the hydraulic motor; and
one or more processors communicably coupled to each controller.
2. The system of claim 1 , wherein the hydraulic motors are selected based on at least one of aerodynamics, propulsive efficiency, structural efficiency, aeroelasticity, or weight of the aircraft.
3. The system of claim 1 , wherein the source of hydraulic power comprises a turboshaft engine operably connected to a variable displacement hydraulic pump.
4. The system of claim 1 , wherein the source of hydraulic power comprises a piston engine operably connected to a variable displacement hydraulic pump.
5. The system of claim 1 , wherein the source of hydraulic power comprises one or more batteries operably connected to a variable displacement hydraulic pump.
6. The system of claim 1 , wherein the source of hydraulic power comprises one or more batteries operably connected to a piezo-hydraulic pump.
7. The system of claim 1 , wherein the plurality of hydraulic motors comprise 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, or 25 variable displacement hydraulic motors.
8. The system of claim 1 , wherein the propeller is at least one of a variable pitch, a constant pitch, a rear folding, or a forward folding propeller.
9. The system of claim 1 , wherein each controller is coupled to one of the hydraulic motors via a mechanical shaft.
10. The system of claim 1 , wherein the hydraulic motors are self-cooling.
11. A method for distributed propulsion of an aircraft comprising:
providing a distributed propulsion system comprising:
a frame;
a plurality of hydraulic motors disposed within or attached to the frame in a distributed configuration;
a propeller operably connected to each of the hydraulic motors;
a source of hydraulic power disposed within or attached to the frame and coupled to each of the plurality of hydraulic motors disposed within or attached to the frame;
a plurality of hydraulic controllers, each hydraulic controller coupled to the source of hydraulic power, and connected to one of the hydraulic motors with a mechanical shaft;
one or more processors communicably coupled to each controller; and
controlling an operation, a speed and a torque of each of the plurality of hydraulic motors using the one or more processors via one of the controllers.
12. The method of claim 11 , further comprising:
determining an aerodynamics, propulsive efficiency, structural efficiency, aeroelasticity or weight of the aircraft;
selecting a number, size and type of the hydraulic motors necessary to provide distributed propulsion for powered operations of the aircraft; and
selecting the source of hydraulic power having sufficient energy density to power the plurality of hydraulic motors connected to the propellers to operate the aircraft.
13. The method of claim 11 , further comprising controlling the aircraft using one or more control surfaces on or about the aircraft.
14. The method of claim 11 , wherein the aircraft is manned or unmanned.
15. The method of claim 11 , wherein the aircraft is a helicopter or a vertical take off and landing aircraft.
16. The method of claim 11 , further comprising controlling a pitch, roll and yaw movement of the aircraft via differential and vectoring thrust without a rotor cyclic and collective control.
17. The method of claim 11 , wherein the source of hydraulic power comprises a turboshaft engine operably connected to a variable displacement hydraulic pump.
18. The method of claim 11 , wherein the source of hydraulic power comprises a piston engine operably connected to a variable displacement hydraulic pump.
19. The method of claim 11 , wherein the source of hydraulic power comprises one or more batteries operably connected to a variable displacement hydraulic pump.
20. The method of claim 11 , wherein the source of hydraulic power comprises one or more batteries operably connected to a piezo hydraulic pump.
21. The method of claim 11 , wherein the aircraft is a closed wing aircraft.
22. The method of claim 11 , wherein the plurality of hydraulic motors comprise 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, or 25 variable displacement hydraulic motors.
23. The method of claim 11 , wherein the propeller is at least one of a variable pitch, a constant pitch, a rear folding, or a forward folding propeller.
24. The method of claim 11 , wherein the hydraulic motors are self-cooling.
25. An aircraft comprising:
an airframe;
plurality of hydraulic motors disposed within or attached to the airframe in a distributed configuration;
a propeller operably connected to each of the hydraulic motors;
a source of hydraulic power disposed within or attached to the frame and coupled to each of the plurality of hydraulic motors disposed within or attached to the frame;
a plurality of hydraulic controllers, each controller coupled to the source of hydraulic power, and connected to one of the hydraulic motors via a mechanical shaft to control a speed and a torque of the hydraulic motor.
26. The aircraft of claim 25 , further comprising one or more control surfaces on or about the aircraft.
27. The aircraft of claim 25 , wherein the aircraft is manned or unmanned.
28. The aircraft of claim 25 , wherein the aircraft is a helicopter or a vertical take off and landing aircraft.
29. The aircraft of claim 25 , wherein a pitch, roll and yaw movement of the aircraft is controlled via differential and vectoring thrust without a rotor cyclic and collective control.
30. The aircraft of claim 25 , wherein the aircraft is a closed wing aircraft.