An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a binary lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes a plurality of ducted fans in a tandem lateral orientation. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

A propulsion system for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The propulsion system includes an turboshaft engine, a lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes at least one ducted fan. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the at least one ducted fan generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

A pitch beam movable by a pitch change shaft to adjust a pitch of at least one rotor blade of a rotor system via a pitch linkage includes a first surface having a generally planar configuration, a smooth second surface disposed opposite the first surface, and a sidewall extending between the first surface and the second surface. A pitch linkage connection point is disposed at the sidewall to which the pitch linkage is attachable. An interior is defined between the first surface and the second surface and an opening extends through the first and second surface at a rotational axis of the rotor system to which the pitch change shaft is attached. Movement of the pitch change shaft moves the pitch beam and adjusts the pitch of the at least one rotor blade via the pitch linkage attached at the pitch linkage connection point.

A pitch beam movable by a pitch change shaft to adjust a pitch of at least one rotor blade of a rotor system via a pitch linkage includes a first surface having a generally planar configuration, a smooth second surface disposed opposite the first surface, and a sidewall extending between the first surface and the second surface. A pitch linkage connection point is disposed at the sidewall to which the pitch linkage is attachable. An interior is defined between the first surface and the second surface and an opening extends through the first and second surface at a rotational axis of the rotor system to which the pitch change shaft is attached. Movement of the pitch change shaft moves the pitch beam and adjusts the pitch of the at least one rotor blade via the pitch linkage attached at the pitch linkage connection point.

A contra-rotating electric helicopter utilizes an electric motor having a base and an output shaft and a power source. The helicopter couples the base to a first rotor, thus allowing both the base and the power source to rotate within the frame of reference of the first rotor, while a contra-rotating and coplanar second rotor is coupled to the output shaft of the electric motor.

A contra-rotating electric helicopter utilizes an electric motor having a base and an output shaft and a power source. The helicopter couples the base to a first rotor, thus allowing both the base and the power source to rotate within the frame of reference of the first rotor, while a contra-rotating and coplanar second rotor is coupled to the output shaft of the electric motor.

An active flow control system for generating pitch control moments for an aircraft during flight. The system includes a nozzle disposed proximate the aft end of the aircraft. The nozzle is configured to discharge a gas stream in the aftward direction. A pressurized air system includes a pressurized air source and one or more injectors configured to selectively inject pressurized air into the nozzle to influence the path of the gas stream. Based upon which injectors are injecting pressurized air into the nozzle, the gas stream exits the nozzle generating no pitch control moment, generating a pitch down control moment or generating a pitch up control moment.

An active flow control system for generating roll control moments for an aircraft during hover flight. The system includes right and left roll effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left roll effectors. Based upon which of the injectors is injecting pressurized air, the right and left roll effectors generate no roll control moment, generate a roll right control moment or generate a roll left control moment.

An active flow control system for generating yaw control moments for an aircraft during hover flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.

An active flow control system for generating yaw control moments for an aircraft during forward flight. The system includes right and left yaw effectors disposed proximate the right and left wingtips of the wing. A pressurized air system includes a pressurized air source and a plurality of injectors operably associated with the right and left yaw effectors that influence the path of airflow above and below the yaw effectors. Based upon which of the injectors is injecting pressurized air, the right and left yaw effectors generate no yaw control moment, generate a yaw right control moment or generate a yaw left control moment.