Planetary de-rotation system for a shaft fairing system

1. A de-rotation system comprising:

a first ring gear defined about an axis;

a second ring gear defined about said axis;

a planetary gear set in meshing engagement with said first ring gear and said second ring gear;

a cage assembly which supports said planetary gear set; and

a shaft fairing mounted for rotation with said first ring gear to control a position of said shaft fairing about said axis of rotation, wherein said shaft fairing is located between a rotor hub and at least one of the first ring gear and the second ring gear.

2. The system as recited in claim 1 , wherein said second ring gear is fixed relative to said axis.

3. The system as recited in claim 1 , wherein said planetary gear set is in meshing engagement with an inner diameter of said first ring gear and an inner diameter of said second ring gear.

4. The system as recited in claim 1 , wherein said planetary gear set comprises a multitude of planet gear assemblies.

5. The system as recited in claim 4 , wherein each of said multitude of planet gear assemblies comprise an upper planet gear, a lower planet gear and a shaft that rotationally connects said upper planet gear and said lower planet gear.

6. The system as recited in claim 1 , further comprising a drive system which selectively rotates said second ring gear.

7. The system as recited in claim 6 , further comprising a control system in communication with said drive system to selectively rotate said second ring gear to azimuthally position said second ring gear in response to a flight control system.

8. The system as recited in claim 1 , wherein the shaft fairing is configured to reduce aerodynamic drag.

9. The system as recited in claim 1 , wherein the shaft fairing has a non-circular cross section.

10. The system as recited in claim 1 , wherein the shaft fairing has an elliptical cross section.

11. The system as recited in claim 1 , wherein the de-rotation system is configured to surround a rotor shaft on a rotary winged aircraft.

12. The system as recited in claim 1 , including an upper hub fairing defined about said axis.

13. The system as recited in claim 12 , including a lower hub fairing defined about said axis.

14. The system as recited in claim 13 , wherein the shaft fairing is mounted for relative rotation between the upper hub fairing and the lower hub fairing.

15. The system as recited in claim 13 , wherein the shaft fairing is located between the upper hub fairing and the lower hub fairing.

16. The system as recited in claim 1 , wherein the shaft fairing is configured to be exposed to an airflow.