A landing gear system for an aircraft includes an aft landing gear fitting coupled to the aircraft and a cross tube rotatably coupled to the aft landing gear fitting. The landing gear system also includes first and second wheel fittings coupled to the first and second ends of the cross tube, respectively, and first and second wheels rotatably coupled to the first and second wheel fittings, respectively.

A landing gear system for an aircraft includes an aft landing gear fitting coupled to the aircraft and a cross tube rotatably coupled to the aft landing gear fitting. The landing gear system also includes first and second wheel fittings coupled to the first and second ends of the cross tube, respectively, and first and second wheels rotatably coupled to the first and second wheel fittings, respectively.

Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.

Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.

A cargo transportation system includes a cargo platform having an upper surface and a perimeter. A propulsion system is disposed about the perimeter of the cargo platform. The propulsion system includes a plurality of propulsion assemblies, each including a propulsion unit disposed within a housing defining an airflow channel having an air inlet for incoming air and an air outlet for outgoing air such that the outgoing air is operable to generate at least vertical lift. A power system disposed within the cargo platform provides energy to drive the propulsion system. A flight control system operably associated with the propulsion system and the power system controls flight operations of the cargo transportation system.

An unmanned aircraft system (UAS) configured for both vertical take-off and landing (VTOL) and fixed-wing flight operations includes forward and aft wing assemblies mounted to the fuselage, each wing assembly including port and starboard nacelles terminating in motor-driven rotors powered by an onboard control system capable of adjusting rotor speeds. The UAS may transition between a powered-lift VTOL configuration to a winged-flight configuration by shifting its center of gravity forward, pivoting the wing assemblies from a powered-lift position perpendicular to the fuselage to a winged-flight position parallel to the fuselage. The forward rotor blades may be folded back so that the aft rotors may provide primary thrust for winged flight operations. Onboard attitude sensors may detect rotor or control failures, to which the control system responds by triggering a conversion to the winged-flight configuration for recovery operations.

An unmanned aircraft system (UAS) configured for both vertical take-off and landing (VTOL) and fixed-wing flight operations includes forward and aft wing assemblies mounted to the fuselage, each wing assembly including port and starboard nacelles terminating in motor-driven rotors powered by an onboard control system capable of adjusting rotor speeds. The UAS may transition between a powered-lift VTOL configuration to a winged-flight configuration by shifting its center of gravity forward, pivoting the wing assemblies from a powered-lift position perpendicular to the fuselage to a winged-flight position parallel to the fuselage. The forward rotor blades may be folded back so that the aft rotors may provide primary thrust for winged flight operations. Onboard attitude sensors may detect rotor or control failures, to which the control system responds by triggering a conversion to the winged-flight configuration for recovery operations.

The firefighting helicopter fans comprise a left pivoting cowled fan and a right pivoting cowled fan mounted onto the sides of a helicopter. The fans may be used to create an airstream, which counters the prevailing wind and/or blows flames and embers away from unburned materials. The fans are each protected by a cowl that surrounds the blades to protect the blades and direct the airstream. The left pivoting cowled fan and the right pivoting cowled fan are each coupled to the helicopter by a pivot axis and a pivot motor which allows the fanes to be aim directly forward, directly down, or any angle in between.

The firefighting helicopter fans comprise a left pivoting cowled fan and a right pivoting cowled fan mounted onto the sides of a helicopter. The fans may be used to create an airstream, which counters the prevailing wind and/or blows flames and embers away from unburned materials. The fans are each protected by a cowl that surrounds the blades to protect the blades and direct the airstream. The left pivoting cowled fan and the right pivoting cowled fan are each coupled to the helicopter by a pivot axis and a pivot motor which allows the fanes to be aim directly forward, directly down, or any angle in between.

The present disclosure provides a flying water-ski device which enables a person to float in the air and fly in addition to gliding on the water in waterskiing. The flying water-ski device may be equipped with an airfoil having an outer form of a simplified triangle whose top faces toward the front. A flap section which has right and left flap axes may be placed at the back-end of said airfoil and right and left flaps, each of which can rotate around said right and left flap axes. A suspension support section may be suspended from said airfoil, and a harness section fixed to the suspension support section. A first tow rope may be coupled to the airfoil, and a second tow rope coupled to the harness section.