Sikorsky Aircraft Corporation

Peter James Waltner

Jonathan Hartman

John R Herter

Timothy Fred Lauder

Joseph Lawrence Simonetti

Frederick L Bourne

Nicholas D Lappos

Glen A Knaust

Daniel Bazzani

Simon J Gharibian

Nikolas A Macko

Per Lars R Stubbendorff

Tad Arthur Mondell, Jr

An inter-spool energy transfer system is provided and includes a first spool, a second spool, which includes components that are rotatable at a different speed as compared to components of the first spool and an inter-spool interface system coupled to at least one of the components of the first spool and at least one of the components of the second spool. The inter-spool interface system includes a controller, which is configured to supply power to one of the first and second spools and to draw power from the other of the first and second spools.

Turbine inter-spool energy transfer system

A rotary wing aircraft includes an airframe, a stationary mast fixedly engaged to the airframe and extending along a first axis, and an electric motor. The electric motor includes a stator assembly engaged to the mast and a rotor assembly disposed radially outward from the stator assembly and configured to rotate with respect to the stator assembly. A plurality of rotor blades project radially outward from the rotor assembly.

Electric propulsion system for a rotary wing aircraft

A hybrid power drive system for an aircraft that comprises a rotor and a first power drive sub-system. The first power drive sub-system includes at least one engine in connection with the rotor and provides a first power to the rotor. The hybrid power drive system also includes a second power drive sub-system connected in parallel to the first power drive sub-system, which supplements with a second power the first power delivered to the rotor during operation of the aircraft. In addition, an electric power source provides a third power to the second power drive sub-system.

Hybrid electric power drive system for a rotorcraft

An adaptive landing gear assembly for a rotary wing aircraft, the adaptive landing gear assembly including a controller; a first landing gear support having a first ground contact element; and a second landing gear support having a second ground contact element; the controller independently controlling the first landing gear support and the second landing gear support.

Adaptive landing gear assembly for rotary wing aircraft

An external cargo damping system includes lifting gear and a damping assembly. The lifting gear has a lifting body attachment end and an opposed external cargo end, and defines a load path that extends between the lifting body attachment and external cargo ends of the lifting gear. The damping assembly is connected in series with the lifting gear and is disposed along the load path to damp vibratory force transmitted between the lifting gear lifting body attachment and lifting gear ends.

Systems and methods for lifting body vibration control

A detachable power transfer device for a rotary-wing aircraft includes a docking station integrated into the rotary-wing aircraft. A power pod of the detachable power transfer device is constructed and arranged to detachably connect to the docking station for transferring power to the rotary-wing aircraft.

Detachable power transfer device for a rotary-wing aircraft

A touchdown control system for a vertical take-off and landing (VTOL) aircraft including a detection controller receptive to aircraft state signals including one or more of an altitude signal, an aircraft attitude signal, an external environment signal, an aircraft velocity signal, an attitude rate signal, and a proximity signal. An enable controller is operatively connected to the detection controller. The enable controller selectively provides a touchdown control signal based on one or more of the altitude signal, the aircraft attitude signal, the external environment signal, the aircraft velocity signal, the attitude rate signal, and the proximity signal. A regulation controller is operatively connected to the enable controller. The regulation controller selectively adjusts aircraft control surfaces based on the touchdown control signal to facilitate final touchdown of the VTOL aircraft.

Touchdown control system

A system for a vehicle includes a receiver configured to receive input data, and a processor configured to run an optimization algorithm to evaluate the input data. The optimization algorithm includes at least one cost model configured to determine vehicle operational parameters to meet the input data. An output module is configured to output to the vehicle operational parameters that optimize operation of the vehicle in view of the input data.

Optimal flight planner

An aircraft assembly is provided and includes a first member extending from an aircraft airframe, a propeller, which is drivable to rotate and a secondary member on which the propeller is supportable and which is aerodynamically pivotable with respect to the first member.

Rotary or fixed wing aircraft with thrust vectoring tail

The disclosure herein relates to power leveling mechanisms comprising a high frequency controller. The power leveling mechanism receives a power demand signal indicating a power requirement of a vehicle and determines a high frequency component of the power demand signal. The power leveling mechanism also provides a signal to a primary propulsion system and provides, via the high frequency controller, a high bandwidth signal based on the high frequency component to an auxiliary propulsion system.

Power leveling controller

A tail rotor recovery control system has a detection module configured to detect a loss of tail rotor drive from a tail rotor sensor of an aircraft; and a regulation module configured to augment or deactivate manual flight control signals and transmit automated signals to control modules of a primary flight control system. The automated signals facilitate the aircraft to attain or maintain a preset tip path plane level, attain or maintain a preset aircraft state, or to execute an automated recovery to forward flight.

Tail rotor failure recovery controller

An aircraft is provided and includes an airframe having an upper section and a tail section, a main rotor assembly operably disposed at the upper section and one or more tail rotor assemblies operably disposed at the tail section. The one or more tail rotor assemblies respectively include one or more articulated propellers with thrust vectoring capability that are each independently rotatable about a respective variable rotational axis.

Aircraft with thrust vectoring tail

A hybrid power drive system for an aircraft comprises a rotor that receives power and a first power drive sub-system including at least one engine in connection with the rotor is configured to provide a first power to the rotor. Further, the hybrid power drive system also includes a second power drive sub-system connected in parallel to the first power drive sub-system. The second power drive sub-system is configured to provide a second power to the rotor a second power drive sub-system connected in parallel to the first power drive sub-system and configured to provide a second power to the rotor when the first power provided by the first power drive sub-system is less than a power demand of the rotor.

Hybrid contingency power drive system

A method of rotorcraft state control includes receiving command input indicative of an intended state change in a rotorcraft. The method also includes issuing command output to a rotor actuation system to carry out the intended state change by varying drag and/or efficiency on one or more rotor blades of the rotorcraft. Issuing command output can include issuing a command output to the rotor actuation system to carry out the intended state change by increasing drag at a substantially constant thrust on one or more rotor blades of the rotorcraft.

Growing community of inventors

Royal Palm Beach, FL, United States of America

Peter James Waltner