Sikorsky Aircraft Corporation

Sirorsky Aircraft Corporation

Brandon L Stille

Steven D Weiner

Michael Peter Strauss

Timothy Fred Lauder

Mark R Alber

Ashley DeVito

William Arthur Welsh

Mark Winfield Scott

William J Eadie

Joseph Pantalone, Iii

John S Chapkovich, Iii

Alfred Russell Smiley

Benjamin Reed Hein

Matthew J Tarascio

Patrick Boyle

Leslie Schweizer

An exhaust system for reducing infrared emissions of a rotary wing aircraft includes a manifold; an opening in the manifold, the opening configured to face upwards and away from the rotary wing aircraft; and a chimney including a wall positioned about the opening, the chimney configured to eject an emission of intermixed secondary air and engine exhaust upwards and away from the rotary wing aircraft.

Upturned exhaust system for rotary wing aircraft

A vertical takeoff and landing (VTOL) rotary-wing air-craft is sized and configured to match a payload container such as a standardized Joint Modular Intermodal Container (JMIC). The aircraft may be an Unmanned Air Vehicle (UAV) that is capable of autonomously engaging and disengaging the container so that the aircraft can pick up and drop off the JMIC with minimum human intervention.

Aerodynamic integration of a payload container with a vertical take-off and landing aircraft

A rotor control system including a collective control rod positioned internal to a rotor shaft, the rotor shaft for imparting torque to rotor blades; and a cyclic control rod positioned internal to and concentric with the collective control rod.

Concentric rotor control system

A tailwheel assembly for an aircraft includes a ventral fin including a fixed airframe portion of the ventral fin and a moveable tailwheel portion of the ventral fin. A tailwheel strut extends through the ventral fin and includes a fixed first strut portion and an extendable second strut portion having the moveable tailwheel portion of the ventral fin secured thereto. A tailwheel is secured to the extendable second strut portion. A method of operating a tailwheel assembly for an aircraft includes extending an extendable portion of a tailwheel strut from an airframe of the aircraft. The tailwheel strut has a tailwheel secured thereto and is located at least partially in a ventral fin of the aircraft. A tailwheel portion of the ventral fin is moved away from a fixed airframe portion of the ventral fin via extension of the extendable portion of the tailwheel strut.

Retracting tailwheel assembly and fin

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.

Combination brake clutch drive system and rotary-wing aircraft using same

Rotary wing aircraft

A rotor system includes a multiple of rotor blade yokes mounted to a rotor hub. A lead/lag damper is mounted to each of the rotor blade yokes and to a damper hub. An actuator system is operable to shift a damper hub axis of rotation relative the rotor axis of rotation to minimize 1P damper motions. A method of minimizing 1P damper motions within a rotor system includes shifting the damper hub axis of rotation relative the rotor axis of rotation to oscillate an inner connector of each lead/lag damper in phase with a 1P blade motion to minimize the 1P motion of the damper.

System and method of damping a 1P motion

An aircraft payload retention system includes a cable, a brake assembly, a hollow crushable member and a hollow structural member. The hollow structural member is fixed adjacent an aircraft internal cargo bay. In response to a high-G condition, the payload may break free from a tie-down system and move forward. The brake assembly engages the hollow crushable member within the hollow structural member and begins to crush the hollow crushable member as the cable is pulled therethrough to dissipate energy of the payload into the structure of the aircraft to arrest forward movement of the payload toward the cockpit.

Aircraft payload retention system for interior loads

Rigid coaxial rotor helicopter with auxiliary propulsion (large)

Rigid coaxial rotor helicopter with auxiliary propulsion (small)

Rigid coaxial rotor unmanned helicopter with auxiliary propulsion

Growing community of inventors

Cheshire, CT, United States of America

Brandon L Stille