Integrated transmission and rotor head
AssigneeThe Boeing Company
InventorJohn C. Mack
Life of this patent
Estimating the term…
Abstract
An integrated transmission and helicopter rotor head is disclosed. Lift and bending moments generated by the rotating hub are carried by non-rotating support structure. The rotating rotor shaft is adapted to carry only torque loads. Partial gear reduction takes place above the rotor shaft, thereby reducing its torque loading. The invention includes a planet gear assembly wherein the ring gear is connected to the rotating hub, while the rotor drive shaft causes rotation of the sun gear. The hub swashplate is located above the hub with its control rods passing through the planet gear assembly.
Claims1
A rotorcraft hub and transmission system, adapted to be driven by an engine which comprises:
- a non-rotatable housing connected to the rotorcraft;
- a rotor shaft having an upper end and a lower end for transmitting torque, said shaft being positioned within said housing;
- a bevel gear connected to the engine and connected to said lower end of said shaft adapted to cause rotation of said shaft, said shaft and said bevel gear interface being adapted to cause a first stage of gear reduction,
- a planet gear assembly including a ring gear, planet gears adapted to engage said ring gear, and a sun gear adapted to engage said upper end of said drive shaft and said planet gears, each of said planet gears being rotatably connected to a post, said posts forming a portion of said housing to prevent them from orbiting about said sun gear, said planet gear assembly being adapted to cause a second stage of gear reduction;
- a rotatable hub including rotor blades operably connected thereto, said blades being rotatable about a pitch axis, said ring gear forming an integral portion of said hub, and said hub being rotatably connected to said housing by bearing means which transmit axial loads and bending moments between said hub and said housing;
- and
- control means connected to a non-rotating portion of the rotorcraft and to said rotor blades for causing rotation of said blades about their pitch axis, said control means including control rods passing through said planet gears and said posts, and further including a swashplate positioned above the plane of rotation of said blades, said swashplate including a non-rotating portion tiltably and slidably connected to a stand pipe forming a portion of said housing, said stand pipe being connected to said posts, said swashplate further including a rotating portion connected to said blades so as to permit said swashplate to cause rotation of said blades about said pitch axis, said control rods being connected to said non-rotating portion of said swashplate;
- whereby the length of said rotor shaft may be minimized thereby permitting the height of the rotor above the rotorcraft to be minimized.
Dependencies are inferred from the claim text.