A lift cell module is disclosed having a housing with an air inlet, an air outlet and an air duct connecting them, the housing having a generally circular inner wall having an axis and the inner wall being mounted for rotation about the axis. A plurality of radially disposed lift cells including winglets having opposed ends are connected to the inner wall, each of the winglets being vertically spaced and extending parallel to one another. The lift cell module further including a member connected to the housing for applying a motive force to rotate the inner wall.

A zero fuel time is determined and presented to an operator of an unmanned aerial vehicle (UAV). Zero fuel time may be determined based on a fuel burn rate and an amount of remaining fuel. A return to base time is determined and presented to an operator of a UAV. Return to base time may be determined based on a location of the UAV and a location of a base. Zero fuel time and return to base time are presented to an operator of a UAV proximate to one another using contrasting and/or varying visual characteristics to ease comparison and identification of this data.

For autonomous data evacuation, a compartment is motivated by a propulsion device. A navigation module guides the compartment to a disaster recovery target using the propulsion device in response to an evacuation signal. At least a portion of the navigation module comprises one or more of hardware and executable code, the executable code stored on one or more computer readable storage media.

According to an aspect, an unmanned aerial vehicle (UAV) is provided that is capable of flying between a pick up point and a delivery point with respect to a package transfer operation. The delivery point is identifiable by the UAV through global positioning system (GPS) coordinates of the delivery point and verification of a device identifier of a package docking device (PDD) associated with a package transfer request. A control processor coupled to the UAV receives a transaction packet for the operation that includes the GPS coordinates and the device identifier of the PDD associated with the request. Upon arrival of the UAV at the delivery point, the control processor verifies that a device identifier of a PDD located at the delivery point matches the device identifier in the transaction packet, implements the package transfer operation, and transmits confirmation of completion of the operation to an originator of the request.

V2 Pipe Prop Rotary Wing (PPRW) incorporates a general PPRW documented in patent application Ser. No. 16/128,537 filed on Sep. 12, 2018; and both V2 PPRW and the general PPRW are each a propeller driven propulsion engine in a pipe profile with props or propellers rotating in part as rotary wings. V2 PPRW enhances propulsion performances through the shaping of fluid flow field patterns around props and by the increased relative fluid flow velocities between props of interacting planet and sun airfoils. V2 PPRW props in rotations propel directional fluid for thrusts of lift and drag forces transversely through and across the pipe along the length of the pipe; and when vectored, the thrust forces are turned into variable thrust forces for vehicles in air, on ground, and above or below water.

A computer is programmed to deploy an aerial drone to fly within a specified distance of a first vehicle. The computer is programmed to detect a second vehicle and then activate an aerial drone light.

A flying machine includes: a flying machine body that includes a rotor blade; a protective member that forms a frame shape inside which the rotor blade is disposed, that is rotatably fixed to both end portions of the flying machine body, and that is pipe shaped; and a connecting wire that passes through an inner portion of the protective member to connect the flying machine body and an external device together.

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.

An unmanned aerial vehicle (UAV), comprising one or more motors, one or more non-destructive testing data collectors, and an electro-magnet, may be used to inspect a structure to which it can magnetically attach by having the UAV approach the structure and activating the electro-magnet when the UAV is a predetermined distance to the structure to be inspected. Once maneuvered close enough to the structure to allow the electro-magnet to magnetically attach to the structure to be inspected, the UAV may be secured against the structure using the electro-magnet proximate an area to be inspected such that the non-destructive testing data collector is disposed proximate the area to be inspected. Data may then be collected using the non-destructive testing data collector.

A flight propulsion system for Vertical Take-Off and Landing (VTOL) and Short Take-Off and Landing (STOL) aircraft, having a two cyclorotors, installed in the front and rear portions of a pair-wings mechanism involving top wing and bottom wing, three degree-of-freedom DOF adjusting mechanism for pair-wings, a dielectric barrier discharge (DBD) plasma actuators, a bar mechanism for pitching oscillation and rotation speed controls and rear cyclorotor, a yawing mechanism for rear cyclorotor, all on each side of the flight vehicle. This propulsion system is particularly useful for VTOL aircraft. The main features are: high controllability and manoeuvrability, low noise and environmental pollutions, VTOL, STOL, hover state flights, marine and ground take-off and landing, high safety, suitable for different aircraft scales and for different missions and purposes, instant altering the flight direction.