초록 ▼

A drive system includes a planetary gear system. An input is affixed to a sun gear of the planetary gear system to rotate therewith and an output is affixed to the output ring gear to rotate therewith. A first brake system is selectively operable to rotationally lock an output ring gear of the plane

A drive system includes a planetary gear system. An input is affixed to a sun gear of the planetary gear system to rotate therewith and an output is affixed to the output ring gear to rotate therewith. A first brake system is selectively operable to rotationally lock an output ring gear of the planetary gear system, and a second brake system is selectively operable to rotationally lock the planet carrier of the planetary gear system. Rotary-wing aircraft implementations of the drive system are also disclosed.

대표청구항 ▼

1. A drive system comprising: a planetary gear system which includes a sun gear in meshing engagement with a multiple of planet gears, said multiple of planet gears supported on a planet carrier, said multiple of planet gears in meshing engagement with an output ring gear;an input affixed to said su

1. A drive system comprising: a planetary gear system which includes a sun gear in meshing engagement with a multiple of planet gears, said multiple of planet gears supported on a planet carrier, said multiple of planet gears in meshing engagement with an output ring gear;an input affixed to said sun gear of said planetary gear system to rotate therewith;an output affixed to said output ring gear to rotate therewith;a first brake system selectively operable to rotationally lock said output ring gear;a second brake system selectively operable to rotationally lock said planet carrier of said planetary gear system; anda translational thrust system driven by said output. 2. The drive system as recited in claim 1, wherein said second brake system includes a brake plate assembly fixed to said planet carrier. 3. The drive system as recited in claim 2, wherein said second brake system includes a clutch actuator configured to be fixed to ground, said clutch actuator selectively operable to rotationally lock said second brake plate assembly. 4. The drive system as recited in claim 3, wherein said second clutch actuator is configured to be fixed to an airframe of a rotary-wing aircraft. 5. The drive system as recited in claim 1, wherein said first brake system includes a brake plate assembly fixed to output ring gear. 6. The drive system as recited in claim 5, wherein said first brake system includes a brake actuator configured to be fixed to ground, said brake actuator selectively operable to rotationally lock said brake plate assembly. 7. The drive system as recited in claim 6, wherein said brake actuator is configured to be fixed to an airframe of a rotary-wing aircraft. 8. The drive system as recited in claim 1, further comprising a control module to selectively operate said second brake system and said first brake system. 9. The drive system as recited in claim 1, further comprising a main gearbox (MGB) which drives said input. 10. The drive system as recited in claim 9, further comprising a main rotor system driven by said main gearbox (MGB). 11. The drive system as recited in claim 10, wherein said main rotor system axis of rotation is transverse to said translational thrust system axis of rotation. 12. The drive system as recited in claim 10, wherein said translational thrust system extends from a tail of a rotary-wing aircraft. 13. The drive system as recited in claim 9, wherein said output extends in a direction opposite said main gearbox. 14. The drive system as recited in claim 1, wherein said first brake system and said second brake system are mechanically activated. 15. The drive system as recited in claim 1, wherein said first brake system and said second brake system are electrically activated. 16. The drive system as recited in claim 1, wherein said first brake system and said second brake system are hydraulically activated. 17. The drive system as recited in claim 1, wherein said first brake system and said second brake system are pneumatically activated. 18. The drive system as recited in claim 1, wherein the input affixed to said sun gear and the output affixed to said output ring gear extend in opposite axial directions. 19. The drive system as recited in claim 1, wherein the first brake system is axially spaced from the output ring gear. 20. The drive system as recited in claim 1, wherein said output extends towards a distal end of a tail of a rotary-wing aircraft. 21. The drive system as recited in claim 1, wherein said input extends in the same axial direction as said planet carrier.