Autonomous thrust vectoring ring wing pod
An autonomous thrust vectoring ring wing pod is disclosed. A plurality of distributed propulsion element (thruster) layout within a self-articulating ring wing pod allows the pod to selectively control its thrust vector by controlling each propulsion element in the pod. This arrangement allows autonomous and independent control of the tilting of the ring wing relative to the aircraft. The ring wing pod acts as both a nacelle to house the propulsion elements as well as a lifting surface when in wing-borne flight. The autonomous thrust vectoring ring wing pod also provides superior aircraft attitude control in wing-borne flight, thus negating the need for conventional surface controls.
1. An autonomous pod, comprising:
a rotation member configured to rotate freely about a rotation axis;
a support member operably coupled to the rotation member, wherein the support member includes a first support member disposed on a first plane and a second support member disposed on a second plane different from the first plane, wherein the first support member and the second support member are disposed within a ring wing pod;
a plurality of thrusters operably coupled to the support member, each thruster configured to provide a variable thrust output, wherein a first group of the plurality of thrusters is operably coupled to the first support member and a second group of the plurality of thrusters is operably coupled to the second support member; and
a controller configured to vary the thrust output of each thruster to rotate the support member about the rotation axis.
2. The autonomous pod of claim 1 , wherein one or more of the plurality of thrusters are canted.
3. The autonomous pod of claim 2 , wherein the canted thrusters are canted non-orthogonally to the support member.
4. The autonomous pod of claim 1 , wherein each of the plurality of thrusters includes propellers configured to rotate in a first rotational direction and a second rotational direction about a rotation axis of each respective thruster of the plurality of thrusters.
5. The autonomous pod of claim 4 , wherein a first group of the plurality of thrusters rotate in the first rotational direction and a second group of the plurality of thrusters rotate in the second rotational direction.
6. The autonomous pod of claim 5 , wherein the first group of the plurality of thrusters rotate in the first rotational direction and the second group of the plurality of thrusters rotate in the second rotational direction to counteract the torque between the thrusters.
7. The autonomous pod of claim 1 , wherein a voltage supplied to each of the plurality of thrusters can be varied.
8. The autonomous pod of claim 7 , wherein the voltage supplied to each of the plurality of thrusters can be selectively varied to generate a thrust vector.
9. The autonomous pod of claim 8 , wherein the voltage supplied to each of the plurality of thrusters can be selectively varied to rotate the rotation member about the rotation axis.
10. The autonomous pod of claim 7 , wherein the controller can vary the voltage supplied to each of the plurality of thrusters.
11. The autonomous pod of claim 1 , wherein each thruster of the plurality of thrusters is canted at a different angle such that each thruster has a different pitch angle.
12. A method of autonomously controlling the orientation of an aircraft, comprising:
operating a plurality of thrusters operably coupled to a support member of an aircraft, each thruster configured to provide a variable thrust output, wherein the support member includes a first support member disposed on a first plane and a second support member disposed on a second plane different from the first plane, wherein a first group of the plurality of thrusters is operably coupled to the first support member and a second group of the plurality of thrusters is operably coupled to the second support member;
varying, via a controller, the thrust output of each thruster to rotate the support member about a rotation axis using only the thrust output of each thruster; and
coordinating, via the controller, the thrust output for each of the plurality of thrusters to control the flight orientation of the aircraft.
13. The method of claim 12 , wherein the controller can be a flight control computer.
14. The method of claim 12 , wherein the controller includes a first controller configured to control a first group of thrusters, and a second controller configured to control a second group of thrusters.
15. The method of claim 14 , wherein the first controller varies the thrust output of each thruster in the first group of thrusters and the second controller varies the thrust output of each thruster in the second group of thrusters.
16. The method of claim 14 , wherein a flight controller communicates with the first and second controllers.
17. The method of claim 16 , wherein the flight controller wirelessly communicates with the first and second controllers.
18. The method of claim 14 , wherein the first and second controllers are configured to communicate with each other.
19. The method of claim 12 , wherein one or more of the plurality of thrusters are canted.
20. The method of claim 19 , wherein the canted thrusters can be canted non-orthogonally to the support member.
21. The method of claim 12 , wherein each thruster of the plurality of thrusters is canted at a different angle such that each thruster has a different pitch angle.