Autorotating payload delivery device

1 . A payload delivery device communication system configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination, the payload delivery device communication system comprising:

a payload delivery device removably attached to the aircraft deployed payload, the payload delivery device comprising:

a flight control and navigation system;

a flight stabilizer assembly mounted on a containerized payload assembly configured to enclose the aircraft deployed payload;

a rotor assembly attached to the flight stabilizer assembly and including a plurality of rotor blades under control of the flight control and navigation system to provide control input to the rotor assembly to navigate the aircraft deployed payload along the flight path to the predetermined landing destination, wherein each rotor blade of the plurality of rotor blades comprises a folding joint for each rotor blade to be stowed in an initial pre-deployment configuration before being deployed into an autorotating configuration; and

at least one rotor blade angular actuator configured to control rotation of a leading edge of at least one of the plurality of rotor blades with respect to a plane of rotation, wherein the at least one rotor blade angular actuator is further configured to control rotation of the leading edge of the at least one of the plurality of rotor blades to a first downward angle orthogonal to the plane of rotation, wherein the at least one rotor blade angular actuator provides co-planar control of the plurality of rotor blades such that the at least one rotor blade actuator is disposed in the plane of rotation; and

an aircraft master flight controller configured to communicate with the payload delivery device,

wherein the aircraft master flight controller and the flight control and navigation system are in bi-direction communication for at least a portion of the flight path,

wherein the aircraft master flight controller is configured to determine a launch trigger signal configured to deploy the payload delivery device from an aircraft based on an aircraft position and the predetermined landing destination.

2 . The payload delivery device communication system of claim 1 , wherein the bi-directional communication between the aircraft master flight controller and the flight control and navigation system includes course correction information, course deviation information and in-flight navigation telemetry parameters.

3 . The payload delivery device communication system of claim 1 , wherein the flight control and navigation system is further configured to be in at least unidirectional communication for at least another portion of the flight path with at least one mid-to-high earth orbit satellite.

4 . The payload delivery device communication system of claim 3 , wherein the at least unidirectional communication between the flight control and navigation system and the at least one mid-to-high earth orbit satellite includes global positioning data.

5 . The payload delivery device communication system of claim 1 , wherein the flight control and navigation system is further configured to be in at least unidirectional communication for at least another portion of the flight path with at least one of a low earth orbiting satellite or a networked system of low earth orbiting satellites.

6 . The payload delivery device communication system of claim 5 , wherein the unidirectional communication between the flight control and navigation system and the at least one of the low earth orbiting satellite or the networked system of low earth orbiting satellites includes at least one of tracking information and telemetry parameters.

7 . The payload delivery device communication system of claim 1 , wherein the flight control and navigation system is further configured to be in at least unidirectional communication for at least another portion of the flight path with a ground communication station proximate the predetermined landing destination.

8 . The payload delivery device communication system of claim 7 , wherein the at least unidirectional communication between the flight control and navigation system and the ground station includes at least one of atmospheric conditions, weather conditions and flight control and navigation parameters.

9 . The payload delivery device communication system of claim 1 , wherein the flight control and navigation system is further configured to be in at least unidirectional communication for at least another portion of the flight path with a second payload delivery device traveling along a second flight path.

10 . The payload delivery device communication system of claim 9 , wherein the unidirectional communication between the flight control and navigation system and the second payload delivery device includes at least one weather condition for a corresponding altitude.

11 . A payload delivery device communication system configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination, the payload delivery device communication system comprising:

a first payload delivery device comprising:

a flight control and navigation system;

a flight stabilizer assembly mounted on a containerized payload assembly configured to enclose the aircraft deployed payload;

a rotor assembly attached to the flight stabilizer assembly and including a plurality of rotor blades under control of the flight control and navigation system to provide control input to the rotor assembly to navigate the aircraft deployed payload along the flight path to the predetermined landing destination, wherein each rotor blade of the plurality of rotor blades comprises a folding joint for each rotor blade to be stowed in an initial pre-deployment configuration before being deployed into an autorotating configuration; and

at least one rotor blade angular actuator configured to control rotation of a leading edge of at least one of the plurality of rotor blades with respect to a plane of rotation, wherein the at least one rotor blade angular actuator is further configured to control rotation of the leading edge of the at least one of the plurality of rotor-blades to a first downward angle orthogonal to the plane of rotation, wherein the at least one rotor blade angular actuator provides co-planar control of the plurality of rotor blades such that the at least one rotor blade actuator is disposed in the plane of rotation; and

a second payload delivery device, wherein the first payload delivery device and the second payload delivery device are in at least unidirectional communication regarding weather condition data.

12 . The payload delivery device communication system of claim 11 , wherein the weather condition data is collected by an on-board sensor on at least the first or the second payload delivery device.

13 . The payload delivery device communication system of claim 12 , wherein the weather condition data further includes altitude data.

14 . A payload delivery device communication system configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination, the payload delivery device communication system comprising:

a payload delivery device comprising:

a flight control and navigation system;

a flight stabilizer assembly mounted on a containerized payload assembly configured to enclose the aircraft deployed payload;

a rotor assembly attached to the flight stabilizer assembly and including a plurality of rotor blades under control of the flight control and navigation system to provide control input to the rotor assembly to navigate the aircraft deployed payload along the flight path to the predetermined landing destination, wherein each rotor blade of the plurality of rotor blades comprises a folding joint for each rotor blade to be stowed in an initial pre-deployment configuration before being deployed into an autorotating configuration; and

at least one rotor blade angular actuator configured to control rotation of a leading edge of at least one of the plurality of rotor blades with respect to a plane of rotation, wherein the at least one rotor blade angular actuator is further configured to control rotation of the leading edge of the at least one of the plurality of rotor blades to a first downward angle orthogonal to the plane of rotation, wherein the at least one rotor blade angular actuator provides co-planar control of the plurality of rotor blades such that the at least one rotor blade actuator is disposed in the plane of rotation; and

a ground communication station proximate the predetermined landing destination,

wherein the first payload delivery device and the ground communication station are in at least unidirectional communication for at least a portion of the flight path.

15 . The payload delivery device communication system of claim 14 , wherein the flight control and navigation system is further configured to receive the at least unidirectional communication from the ground communication station to provide the control input to the rotor assembly to navigate the aircraft deployed payload along the flight path to the predetermined landing destination.

16 . The payload delivery device communication system of claim 15 , wherein the unidirectional communication being provided by the ground communication station includes flight control and navigation parameters for use by the flight control and navigation system of the payload delivery device.

17 . The payload delivery device communication system of claim 15 , wherein the unidirectional communication being provided by the ground communication station includes a local wind speed and direction vector and a weather condition proximate the ground communication station.