The disclosure concerns an unmanned aircraft for carrying of cargo, comprising a fuselage (10) extending in a fore-aft direction and configured to receive cargo in an unpressurized interior space thereof; a wing (20) extending in a spanwise direction perpendicular to the fore-aft direction; and a single engine (30) located at or adjacent the rear of the fuselage, wherein the engine (30) is a jet engine. The aircraft is configured for roll-on/roll-off loading of intermodal cargo containers.

The disclosure concerns an unmanned aircraft for carrying of cargo, comprising a fuselage (10) extending in a fore-aft direction and configured to receive cargo in an unpressurized interior space thereof; a wing (20) extending in a spanwise direction perpendicular to the fore-aft direction; and a single engine (30) located at or adjacent the rear of the fuselage, wherein the engine (30) is a jet engine. The aircraft is configured for roll-on/roll-off loading of intermodal cargo containers.

An unmanned helicopter with a rotor disc area expanded to twice that of conventional multi-rotor drones to maximize lift generation under low Reynolds number conditions is described. Aerodynamic efficiency is further improved via airfoils known for their high lift performance in thin atmospheres. A four-blade rotor configuration with low solidity is used to minimize weight while optimizing performance. To facilitate deployment, the helicopter features a foldable transport design that remains compact during interplanetary travel and expands upon re-entry into the atmosphere. Post-landing operations are supported by a hybrid ground mobility system in which the landing gear functions as the drive train for a four-wheeled vehicle. Two coaxial air propellers, integrated into the front wheels, provide additional left-right directional control during both flight and ground movement. The design of the helicopter effectively doubles the payload capacity for a given power input compared to conventional rotorcraft.

An unmanned helicopter with a rotor disc area expanded to twice that of conventional multi-rotor drones to maximize lift generation under low Reynolds number conditions is described. Aerodynamic efficiency is further improved via airfoils known for their high lift performance in thin atmospheres. A four-blade rotor configuration with low solidity is used to minimize weight while optimizing performance. To facilitate deployment, the helicopter features a foldable transport design that remains compact during interplanetary travel and expands upon re-entry into the atmosphere. Post-landing operations are supported by a hybrid ground mobility system in which the landing gear functions as the drive train for a four-wheeled vehicle. Two coaxial air propellers, integrated into the front wheels, provide additional left-right directional control during both flight and ground movement. The design of the helicopter effectively doubles the payload capacity for a given power input compared to conventional rotorcraft.