The Boeing Company

Other

Michael John McNulty

Robert Loftus

Nicklaus Cummings Kimball

Keith B Smith

Glenn Thomas Pyle

Donald J Hunter

Kevin D Henthorn

Tail boom drive systems for helicopters are described which utilize a fan internal to the tail boom to provide yaw control, and an external propulsor to provide forward thrust. In one embodiment, the tail boom drive system includes a shaft, a fan, and a propulsor. The shaft is disposed lengthwise within an interior space of the tail boom, and the shaft has a first end and a second end. The fan is mechanically coupled coaxially to the shaft within the interior space between the first end and the second end, and the fan generates a variable airflow directed towards the second end that is ejected from the interior space substantially perpendicular to the tail boom. The propulsor is external to the tail boom and is mechanically coupled coaxially to the shaft at the second end, and the propulsor generates a variable thrust directed towards the first end.

Anti-torque and propulsion system for rotorcraft

A system to manufacture an object includes a headstock, a tailstock, and a mandrel having a first end coupled to the headstock and a second end coupled to the tailstock. The system also includes an actuator coupled to one or more of the headstock, the tailstock, or the mandrel, the actuator operable to apply a force to the one or more of the headstock, the tailstock, or the mandrel, to oppose deformation of the mandrel.

Actuator-based compensation for deformation of a mandrel

A method is provided for alerting a rotorcraft crew member of a potential collision of a rotor blade of the rotorcraft having a rotor shaft and a rotor azimuth. The method comprises estimating a total rotor flapping value associated with the rotor blade during an operating condition of the rotorcraft. The estimated total rotor flapping value is relative to the rotor shaft as a function of the rotor azimuth. The method also comprises comparing the estimated total rotor flapping value to a rotor flapping limit value during the operating condition of the rotorcraft. The method further comprises sending a warning signal to a warning device when the estimated total rotor flapping value lies outside of the rotor flapping limit value to alert the rotorcraft crew member of a potential collision of the rotor blade of the rotorcraft.

Rotorcraft-mounted rotor blade collision warning system and method for alerting a rotorcraft crew member of a potential collision of a rotor blade

This invention provides convenient airframe vibration and tracking improvements of a helicopter rotor blade by use of an elastomer profile system that is attached through an adhesive system that allows convenient removal and relocation for use by the helicopter manufacturer or by the helicopter operator in a field environment.

Field installable and removable helicopter rotor blade vibration and blade tracking device

A system of adjustable balancing weights is provided for a helicopter main rotor blade. The trailing edge of the rotor blade is formed with a plurality of recesses that each receive an aerodynamically shaped weight to adjust and balance the weight of the rotor blade. A forward weight recess and a forward weight are also provided on the rotor blade adjacent the rotor blade leading edge. The lateral spacing between the weight adjacent the rotor blade leading edge and the weights adjacent the rotor blade trailing edge provides greater flexibility in balancing the mass of the rotor blade.

Trailing edge adjustable weight system for helicopter main rotor blades

A trim tab assembly for a helicopter rotor blade includes a plurality of metal panels that are secured to the trailing edge of a composite material helicopter blade. Each of the metal panels can be bent relative to the rotor blade to tune the aerodynamic properties of the rotor blade.

Growing community of inventors

Scottsdale, AZ, United States of America

Michael John McNulty