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.

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 positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A cockpit in the airframe, the cockpit including two seats and a single collective control input positioned between the two seats.

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 positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A cockpit in the airframe, the cockpit including two seats and a single collective control input positioned between the two seats.

An aircraft is provided and includes an airframe, an extending tail, 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 sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.

An aircraft is provided and includes an airframe, an extending tail, 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 sensor and at least one inertial measurement unit (IMU) to sense current flight conditions of the aircraft, an interface to execute controls of a main rotor assembly in accordance with control commands and at least one flight control computer (FCC) to issue the control commands. The at least one FCC includes a central processing unit (CPU) and a memory having logic and executable instructions stored thereon, which, when executed, cause the CPU to issue the control commands based on the current flight conditions and a result of an execution of the logic for the current flight conditions.

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.

The ideal design for a redundant orbitally driven electric ducted fan that can replace a family of current propeller and motor combinations in electric ducted fan designs by meeting air flow and pressure requirements while drawing less electric current to rotate and thus produce the required flow not only would reduce cost of operation over the life of the fan but opens new possibilities for electric powered vertical takeoff and landing vehicles with redundant drives improving safety of operation. The entry of flying machines using propellers and lifting fans such as hover bikes and quadcopters, manned or unmanned is driving a need to re-examine the application of force applied to rotate these fans to achieve a reduction in aircraft weight and increase flying time for a given battery charge or load of fuel.

Provided is an aerial vehicle, including: a package carrier including a plurality of vertical members being changeable in relative positions in a horizontal direction and surrounding a package in the horizontal direction to prevent falling of the package. A plurality of rotary wings are changeable in relative positions in the horizontal direction. The relative positions of the plurality of vertical members and the relative positions of the plurality of rotary wings are changeable. The package carrier is changed in shape in the horizontal direction in accordance with the relative positions of the plurality of vertical members. The change in the relative positions of the plurality of rotary wings is in conjunction with the shape of the package carrier.