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.

A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.

The present disclosure relates to a rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a shrouded duct that is arranged in the aft region and that forms an inner air duct, wherein the shrouded duct is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft; and a propeller that is at least configured to propel the rotary wing aircraft in the forward flight condition; wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller is rotatably mounted to the shrouded duct such that the circular propeller disc is at least essentially arranged inside of the inner air duct.

The present disclosure relates to a rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a shrouded duct that is arranged in the aft region and that forms an inner air duct, wherein the shrouded duct is formed to generate sideward thrust for main rotor anti-torque in forward flight condition of the rotary wing aircraft; and a propeller that is at least configured to propel the rotary wing aircraft in the forward flight condition; wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and wherein the propeller is rotatably mounted to the shrouded duct such that the circular propeller disc is at least essentially arranged inside of the inner air duct.

In an embodiment, a system for air cooling in a wet environment includes a propeller coupled to a vehicle capable of at least one of: taking off from and landing on water. The system includes a battery configured to power the propeller, a float configured to hold the battery, and a flap in the float. The flap is configured to open in response to air pressure to permit airflow into the float to cool the battery.

In an embodiment, a system for air cooling in a wet environment includes a propeller coupled to a vehicle capable of at least one of: taking off from and landing on water. The system includes a battery configured to power the propeller, a float configured to hold the battery, and a flap in the float. The flap is configured to open in response to air pressure to permit airflow into the float to cool the battery.

Systems and methods for increasing lift of an aircraft lifting surface, may include: a leading-edge assembly; a plurality of high-lift propellers, coupled to the slat assembly and configured to be stowed within a compartment of the lifting surface; a high-lift motor to provide motive force to at least one of the plurality of the high-lift propellers; and a deployment linkage configured to move the slat assembly and plurality of high-lift propellers between a deployed configuration and a stowed configuration, wherein in the stowed configuration the high-lift propellers are stowed within the compartment of the lifting surface and at least a portion of the slat assembly covers the compartment of the lifting surface, and in the deployed configuration the high-lift propellers are positioned external to the aircraft lifting surface to direct airflow from the high-lift propellers past the leading-edge assembly.

Systems and methods for increasing lift of an aircraft lifting surface, may include: a leading-edge assembly; a plurality of high-lift propellers, coupled to the slat assembly and configured to be stowed within a compartment of the lifting surface; a high-lift motor to provide motive force to at least one of the plurality of the high-lift propellers; and a deployment linkage configured to move the slat assembly and plurality of high-lift propellers between a deployed configuration and a stowed configuration, wherein in the stowed configuration the high-lift propellers are stowed within the compartment of the lifting surface and at least a portion of the slat assembly covers the compartment of the lifting surface, and in the deployed configuration the high-lift propellers are positioned external to the aircraft lifting surface to direct airflow from the high-lift propellers past the leading-edge assembly.

A battery powered helicopter uses one or more torque arms as the power source directly driving the main rotor blades, causing them to rotate. The helicopter does not require a combustion engine, a clutch, a reducer, a tail driver, a tail boom, a tail rotor, or a fuel supply system. The output shaft of the high-energy motor is coaxial with the main rotor shaft. The centrifugal force of one or more motor(s) is negligible or minimized. The torque arm assembly includes a plurality of torque arms. Each of the torque arms of the plurality of torque arms includes a propeller and a driving system. The torque arm propellers are hinged so that they can move between a first closed position and a second open position to institute an autorotation safety system.

A battery powered helicopter uses one or more torque arms as the power source directly driving the main rotor blades, causing them to rotate. The helicopter does not require a combustion engine, a clutch, a reducer, a tail driver, a tail boom, a tail rotor, or a fuel supply system. The output shaft of the high-energy motor is coaxial with the main rotor shaft. The centrifugal force of one or more motor(s) is negligible or minimized. The torque arm assembly includes a plurality of torque arms. Each of the torque arms of the plurality of torque arms includes a propeller and a driving system. The torque arm propellers are hinged so that they can move between a first closed position and a second open position to institute an autorotation safety system.