Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system including a propeller is positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. A drive system is configured to operate both the main rotor system and the translational thrust system. The drive system includes a clutch configured to selectively couple or decouple the propeller from the drive system.

Abstract: An aircraft includes an airframe having an extending tail, a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail and providing translational thrust to the airframe; The aircraft is configured to operate at an altitude of over 20,000 feet and at an airspeed of greater than 200 knots.

Abstract: A method of controlling a rotary wing aircraft includes accelerating the aircraft in a fore direction independently of cyclic control of the main rotor and pitch of the aircraft.

Abstract: An aircraft load management system determines a cargo through a wireless communication system to rapidly position the cargo. RFID emitter tags on each piece of cargo are triangulated relative to an aircraft internal cargo bay. Real time cargo position information is displayed to facilitate direction of drivers, loadmasters and aircrew. Cargo data is also relayed to onboard systems for mission planning, and for communication to a global information network to prioritize cargo delivery and dynamic mission re-planning. Even prior to onloading, cargo data is wirelessly communicated to the load management system to automatically plan the cargo load sequence. The load management system also autonomously loads remote controlled ground vehicles and equipment through communication therewith.

Abstract: An aircraft load management system determines a cargo through a wireless communication system to rapidly position the cargo. RFID emitter tags on each piece of cargo are triangulated relative to an aircraft internal cargo bay. Real time cargo position information is displayed to facilitate direction of drivers, loadmasters and aircrew. Cargo data is also relayed to onboard systems for mission planning, and for communication to a global information network to prioritize cargo delivery and dynamic mission re-planning. Even prior to onloading, cargo data is wirelessly communicated to the load management system to automatically plan the cargo load sequence. The load management system also autonomously loads remote controlled ground vehicles and equipment through communication therewith.

Abstract: An aircraft load management system that determines the position of an aircraft cargo hook for display to an aircrew. The cargo hook positional information may alternatively or additionally be communicated directly to a flight control system and a winch control system to automate and coordinate flight control inputs with winch operation to actively position the cargo hook. Data transfer from the cargo through a data link system also provides the load management system with exact position of the cargo load connection points even prior to attachment of the cargo hook to the load. The load management system also includes anti-sway algorithms for active load stability inputs to the flight control system and to alter flight control laws and automatically compensate for C.G. excursions.

Abstract: A rotor system includes a hydraulic pressure system located within a rotor shaft along an axis or rotation. The hydraulic pressure system is within the rotating field such that fluid pressure is generated and supplied from within the rotational field without the need to cross a rotational interface. Differential rotation between the rotor shaft and a standpipe rotates a hydraulic pump body relative a hydraulic pump shaft. The hydraulic pressure system is contained within a support structure so as to be readily mounted and removed from the rotor hub for replacement or maintenance. A gear system is mounted to the support structure between the standpipe and the hydraulic pump shaft to step-up or step-down the relative rotation between the rotor shaft and the standpipe.