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.

A cross flow fan to be incorporated into an aircraft comprises a cross flow fan rotor to be positioned in an aircraft, a drive arrangement for the cross flow fan rotor, and a plurality of vanes positioned downstream of the cross flow fan rotor. An aircraft is also disclosed.

Pipe Props Rotary Wing of the present invention is a propeller driven propulsion engine in a pipe profile with props or propellers rotating in part as rotary wings around their shafts; the props and shafts are oriented lengthwise along the pipe; and the props in rotations propel directional air transversely through and across the pipe to generate variable directional thrusts and lifts in directions also transverse to the pipe. Pipe Props Rotary Wing is a variable thrusts and lifts propeller driven propulsion engine to unify all propeller driven propulsion engines for all propeller driven aircrafts, including: propeller aircrafts, rotary wing aircrafts or helicopters, and tilt rotor aircrafts. Pipe Props Rotary Wing in a pipe profile, with props rotating in part as rotary wings, is suitable as fixed wings replacements for propeller aircrafts and tilt rotor aircrafts. Been adapted from Omni M-VAWT or Omni Multi Axes-Vertical Axis Wind Turbine with modifications, Pipe Props rotary Wing as propeller driven propulsion engines are unified also with some vertical axis wind turbines.

An authentication between a wireless charger and a device configured to receive wireless energy from the wireless charger includes establishing a wireless data channel between the wireless charger and the device. An authentication challenge signal is driven onto a transmit charging coil of the wireless charger and a receive charging coil of the device is configured to receive the authentication challenge signal. The device sends an authentication response signal to the wireless charger based at least in part on the authentication challenge signal.

In one aspect, there is provided an aircraft, including a fuselage having a longitudinal axis extending from a front portion through an aft portion; first and second tail members extending from the aft portion; a first cross-flow fan system rotatably mounted to the first tail member; and a second cross-flow fan system rotatably mounted to the second tail member. The first and second cross-flow fan systems are configured to provide a forward thrust vector and an anti-torque vector on the aircraft. The first and second cross-flow fan systems can have a rotational axis oriented generally vertically. In another aspect, there is an aircraft including a fuselage having a front portion and a tail portion; and a cross-flow fan system supported by the tail portion. Embodiments include a cross-flow fan system retrofittable onto an aircraft and methods for retrofitting an aircraft with a cross-flow fan system.

A cross flow fan to be incorporated into an aircraft fuselage comprises an ingestion fan rotor to be positioned in a tail section of an aircraft fuselage to reduce boundary layer air from a top surface of the fuselage and to drive the air away from the top surface, and a drive arrangement for the ingestion fan rotor. An aircraft is also disclosed.

A tail sitter aircraft includes a fuselage having a forward portion, an aft portion and a longitudinally extending fuselage axis. At least two wings are supported by the forward portion of the fuselage. A distributed propulsion system includes at least one propulsion assembly operably associated with each fixed wing and is operable to provide forward thrust during forward flight and vertical thrust during vertical takeoff, hover and vertical landing. A tailboom assembly extends from the aft portion of the fuselage and includes a plurality of rotatably mounted tail arms having control surfaces and landing members. In a forward flight configuration, the tail arms are radially retracted to reduce tail surface geometry and provide yaw and pitch control with the control surfaces. In a landing configuration, the tail arms are radially extended relative to the fuselage axis to form a stable ground contact base with the landing members.

An authentication between a wireless charger and a device configured to receive wireless energy from the wireless charger includes establishing a wireless data channel between the wireless charger and the device. An authentication challenge signal is driven onto a transmit charging coil of the wireless charger and a receive charging coil of the device is configured to receive the authentication challenge signal. The device sends an authentication response signal to the wireless charger based at least in part on the authentication challenge signal.

An authentication between a wireless charger and a device configured to receive wireless energy from the wireless charger includes establishing a wireless data channel between the wireless charger and the device. An authentication challenge signal is driven onto a transmit charging coil of the wireless charger and a receive charging coil of the device is configured to receive the authentication challenge signal. The device sends an authentication response signal to the wireless charger based at least in part on the authentication challenge signal.

A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.