Abstract: A translational thrust system for a rotary wing aircraft is provided including a propeller system. The propeller system includes more than one pair of propeller blades extending radially outward from a rotatable propeller hub. Each pair of propeller blades includes a first propeller blade and a second propeller blade arranged diametrically opposite one another about a circumference of the propeller hub. Each pair of propeller blades is arranged at an angle to an adjacent pair of propeller blades such that the angle is less than is the pairs of propeller blades were uniformly distributed around the circumference of the propeller hub.

Abstract: A single engine rotary wing aircraft is provided including a fuselage having a longitudinal first axis. A main rotor assembly is mounted to the fuselage for rotation about a second axis, perpendicular to the first axis. A tailboom is connected to an empennage. The tailboom is mounted to an end of the fuselage such that the tailboom is laterally offset from the first axis in a first direction. The rotary wing aircraft also includes a propulsion system. The single engine of the propulsion system is laterally offset from the first axis in a second direction opposite the first direction.

Abstract: 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.

Abstract: A rotary-wing aircraft with an electric motor mounted along an axis of rotation to drive a rotor system about the axis of rotation.