A dual use UAV or “drone” can include a battery and primary processor located at a fuselage, as well as two separate modular units removably coupled to the fuselage and in communication with the primary processor. The two separate modular units can interact with each other to provide an enhanced operation while the drone is in flight. One modular unit can be an ISR unit having a video camera, and the other modular unit can be a cargo unit. The enhanced operation can involve the ISR unit using its video camera to identify a delivery location for a cargo pod of the cargo unit. Alternative modular units can include a secondary ISR unit, a cargo fuel pod unit, or a robotic arm assembly. Standardized interfaces coupled to the fuselage can enable the ready removal of one modular unit and installation of another one.

Systems, devices, and methods for a vertical take-off and landing (VTOL) aerial vehicle having a first GPS antenna and a second GPS antenna, where the second GPS antenna is disposed distal from the first GPS antenna; and an aerial vehicle flight controller, where the flight controller is configured to: utilize a GPS antenna signal via the GPS antenna switch from the first GPS antenna or the second GPS antenna; receive a pitch level of the aerial vehicle from the one or more aerial vehicle sensors in vertical flight or horizontal flight; determine if the received pitch level is at a set rotation from vertical or horizontal; and utilize the GPS signal not being utilized via the GPS antenna switch if the determined pitch level is at or above the set rotation.

A configurable electrical architecture for an eVTOL aircraft having a takeoff and landing power mode and a cruise power mode. The configurable electrical architecture includes a power-optimized power source including a high-power battery array and an energy-optimized power source selected from a plurality of interchangeable energy-optimized power sources including a high-energy battery array, a hydrogen fuel cell system and a turbo-generator system. A distribution system is electrically coupled to the power-optimized power source and the energy-optimized power source. At least one electric motor is electrically coupled to the distribution system. In the takeoff and landing power mode, both the power-optimized power source and the energy-optimized power source provide electrical power to the at least one electric motor. In the cruise power mode, the energy-optimized power source provides electrical power to the at least one electric motor and to the power-optimized power source to recharge the high-power battery array.

A wingless compact aircraft, with a limited footprint and no exposed high-speed moving parts. The aircraft can takeoff and land vertically, can fly at high-speed and even cruise on land and water in one of the preferred embodiments.

The disclosure relates to an electric aircraft propulsion assembly for an electric vertical takeoff and landing, eVTOL, aircraft, the assembly comprising: an electric storage unit; a first electric motor connected to power a first propulsor; a first converter configured as a DC:AC converter for driving the first electric motor and a second electric motor connected to power a second propulsor, a second converter. A controller is connected to control operation of the first and second converters and is configured to operate in a first mode in which the first and second converters are operated as DC:AC converters to drive the first and second electric motors and a second mode in which the first converter is operated to drive the first electric motor to power the first propulsor and the second converter is operated to drive the second electric motor to provide a braking torque on the second propulsor.

A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

A foldable propeller for air mobility includes a link assembly including a plurality of links facilitating blades to be rotated around a hub as a moving portion vertically slides such that the blades are folded to each other or unfolded from each other.

A control system for a multi-rotor aircraft is described that results in lower operating noise. Allowing blades to flap during flight reduces aerodynamic interference as blades pass by other aircraft components, such as wings or the fuselage. Pitch links coupled to a rotational swashplate can be used to allow flapping during flight. The swashplates can allow the canting of the rotors to change a rotational or out-of-plane angle of the blades to decrease noise.

A fixed-wing VTOL hybrid UAV is disclosed comprising: a central frame 104; a pair of quick lockable fixed-wings 102 comprising right wing 102-2 and left wing 102-1 that lock with each other over the central frame; and four electrically operated rotors 108 in downward facing configuration attached to fixed-wings with help of rotor-blade arms 110. Arms 110 are pivotally fixed to wings 102 so that arms 110 are movable between a working position in which arms 110 are oriented parallel to central frame 104, and a storage position in which arms 110 are aligned with wings 102. Central frame 104 is a thin rod and works as fuselage. Drivers and control modules are fitted in wings 102. UAV includes rudders attached to arms at 45 degrees for maneuvering UAV for yaw and a secondary roll response. UAV includes two landing gears 106 attached to each end of central frame.

A tiltrotor has a range of motion between a forward flight position and a hovering position, where a pylon and the tiltrotor are coupled via a telescoping actuator, a rigid bottom bar, and a fixed hinge that is attached between the rigid bottom bar and the tiltrotor. The tiltrotor moves from the forward flight position to the hovering position includes extending the telescoping actuator so that the tilt rotor rotates about the fixed hinge.