Unmanned aerial vehicle optimization

1. A system for optimizing energy and aerodynamic efficiencies in an unmanned cargo-carrying aircraft, the system comprising:

an unmanned aerial vehicle (UAV) having a plurality of rotors for vertical flight and at least one wing assembly, one or more propellers, and a canard for horizontal flight, a communication system, and a hybrid drivetrain, the hybrid drivetrain mounted on the UAV, and the hybrid drivetrain including a combustion engine coupled to a motor/generator and to an electrical distribution system;

a detachable cargo container wherein the detachable cargo container is engaged by a retraction/extension mechanism supplied with power from the electrical distribution system;

a rotor-shrouding mechanism for each rotor mounted on the UAV having two clamshell doors, each clamshell door, when retracted, positioned substantially parallel to the relative airflow through which the UAV moves while in horizontal flight substantially conforming with a UAV shape limiting rotor downwash interaction and each clamshell door joining, when deployed, to shroud each rotor, and a front shroud positioned to mate with each clamshell door fully shrouding each rotor, the rotor-shrouding mechanism supplied with power from the electrical distribution system wherein responsive to the at least one wing assembly and canard generating sufficient lift to support the UAV in horizontal flight, each of the plurality of rotors are aligned with airflow through which the UAV moves in horizontal flight and shrouded by the two clamshell doors and the front shroud;

a processor mounted on the UAV, the processor capable of executing instructions and programmed to allocate power from the electrical distribution system and to operate a flight control system, and wherein the processor is communicatively coupled to the communication system, the hybrid drivetrain, the retraction/extension mechanism, and the rotor-shrouding mechanism.

2. The system of claim 1 , wherein the processor allocates power from the electrical distribution system according to information provided from the flight control system.

3. The system of claim 2 , wherein the flight control system senses UAV modes of movement and directs flight control and hybrid drivetrain functions using sensed UAV modes of movement.

4. The system of claim 1 , wherein the rotor-shrouding mechanism raises the two clamshell doors to cover each of the plurality of rotors when each of the plurality of rotors is not rotating.

5. The system of claim 4 , wherein each of the plurality of rotors are held in an indexed position when the rotor is not rotating.

6. The system of claim 1 , wherein the hybrid drivetrain supplies power to drive the plurality of rotors providing substantially vertical thrust and power to drive the one or more propellers providing substantially horizontal thrust.

7. The system of claim 6 , wherein power to drive the one or more propellers providing substantially horizontal thrust is either electrical power supplied by the electrical distribution system via a battery pack or mechanical power supplied by the combustion engine.

8. The system of claim 6 , wherein the flight control system controls a propeller clutch to engage or disengage from a gearbox the one or more propellers providing substantially horizontal thrust, as controlled by the flight control system.

9. The system of claim 8 , wherein the flight control system controls when the power to the gearbox sources from the motor/generator or from the combustion engine.

10. The system of claim 6 wherein the combustion engine drives the motor/generator thereby producing electrical power supplied to the electrical distribution system powering the one or more propellers providing substantially horizontal thrust.

11. The system of claim 1 , wherein the retraction/extension mechanism retracts or extends the detachable cargo container to or from the UAV, respectively, and upon suspension of the detachable cargo container apart from any ground contact by the retraction/extension mechanism, the retraction/extension mechanism determines a cargo container weight metric and cargo container balance metric.

12. The system of claim 11 , wherein responsive to the cargo container weight metric and the cargo container balance metric meeting a predetermined weight criteria and a predetermined balance criteria, the retraction/extension mechanism positions the detachable cargo container to a close engagement with the UAV sufficient for a coupling mechanism to fixedly attach the cargo container to the UAV.

13. The system of claim 12 , wherein the cargo weight metric and the cargo container balance metric form a loading profile, and responsive to the cargo weight metric and the cargo container balance metric meeting the predetermined weight criteria and the predetermined balance criteria, determining if the loading profile is within a UAV performance envelope and within an assigned mission profile.

14. The system of claim 1 , wherein the processor executes instructions performing a method for flight parameter balancing, the method comprising;

calculating necessary fuel weight requirements to fulfill a cargo delivery mission;

receiving the cargo container weight metric and the cargo container balance metric from the retraction/extension mechanism;

determining a maximum UAV takeoff weight and a maximum cargo container weight;

and calculating, using the cargo container weight metric and the cargo container balance metric, whether the UAV will remain within the predetermined weight criteria and the predetermined balance criteria for the entirety of the cargo delivery mission.