An aircraft is provide 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 positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.

An aircraft is provide 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 positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.

An aircraft includes a fuselage having a top surface opposite a bottom surface, a front section, a center section, and a rear section. A first mounting rod and a second mounting rod are coupled to the top surface. The first mounting rod and the second mounting rod are single rods. A first and a second wing are coupled to the center section. A plurality of power generator systems are coupled to the first mounting rod or the second mounting rod. Each power generator system includes a power source, a first propeller and a second propeller. The power source is configured to drive the first propeller and the second propeller. The first propeller and the second propeller have an axis of rotation, and are pivotable between a first position and a second position. A shroud encloses the power generator system.

An aircraft includes a fuselage having a top surface opposite a bottom surface, a front section, a center section, and a rear section. A first mounting rod and a second mounting rod are coupled to the top surface. The first mounting rod and the second mounting rod are single rods. A first and a second wing are coupled to the center section. A plurality of power generator systems are coupled to the first mounting rod or the second mounting rod. Each power generator system includes a power source, a first propeller and a second propeller. The power source is configured to drive the first propeller and the second propeller. The first propeller and the second propeller have an axis of rotation, and are pivotable between a first position and a second position. A shroud encloses the power generator system.

A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.

A vertical landing and take-off aircraft VTOL transitions from a vertical takeoff state to a cruise state where the vertical takeoff state uses propellers to generate lift and the cruise state uses wings to generate lift. The aircraft has an M-wing configuration with propellers located on the wingtip nacelles, wing booms, and tail boom. The wing boom and/or the tail boom can include boom control effectors. Hinged control surfaces on the wings, tail boom, and tail tilt during takeoff and landing to yaw the vehicle. The boom control effectors, cruise propellers, stacked propellers, and control surfaces can have different positions during different modes of operation in order to control aircraft movement and mitigate noise generated by the aircraft.

The disclosure generally relates to aircraft vehicles, specifically vertical takeoff and landing (VTOL) aircraft that include propellers. A propeller is coupled to a boom and the boom includes a boom control effector. The boom control effector is configured to direct the airflow behind or below the propeller. The boom control effector can be configured to control the yaw movement of the aircraft and mitigate noise from the propeller. A boom control effector can be a single effector or a split effector. The split effector may operate in conjunction with a boom that operates as a resonator to reduce noise produced by the propeller.

The disclosure generally relates to aircraft vehicles, specifically vertical takeoff and landing (VTOL) aircraft that include propellers. A propeller is coupled to a boom and the boom includes a boom control effector. The boom control effector is configured to direct the airflow behind or below the propeller. The boom control effector can be configured to control the yaw movement of the aircraft and mitigate noise from the propeller. A boom control effector can be a single effector or a split effector. The split effector may operate in conjunction with a boom that operates as a resonator to reduce noise produced by the propeller.

Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

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.