Described are aerial vehicle kits and aerial vehicles comprising two or more wing units that can be driven individually. Such control of the lift and propulsion generation of each wing individually enables greater vehicle control for increased maneuverability and weather tolerance.

The user assistance drone device is an unmanned aerial vehicle used as a communication device. The user assistance drone device tracks the client while the user assistance drone device is in the air. The user assistance drone device follows the client and forms an audio communication link between the client and an appropriate authority. The audio communication link allows the client to speak with an appropriate authority. The user assistance drone device comprises the unmanned aerial vehicle and a master circuit. The unmanned aerial vehicle is a device capable of travel through the atmosphere. The master circuit: a) tracks the location and the movement of the client; b) transmits flight instructions to the unmanned aerial vehicle that allows the unmanned aerial vehicle to follow the client; and, c) establishes the audio communication link between the client and the appropriate authority.

Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

An ejector system for propelling a vehicle. The system includes a diffusing structure and a duct coupled to the diffusing structure. The duct includes a wall having openings formed therethrough and configured to introduce to the diffusing structure a primary fluid produced by the vehicle. An airfoil is positioned within the flow of the primary fluid through the openings to the diffusing structure.

Aerial launch and/or recovery for unmanned aircraft, and associated systems and methods. A representative unmanned aerial vehicle (UAV) comprises an airframe, a plurality of rotors, and a capture line. The rotors are coupled to the airframe and configured to support the UAV in hover. The capture line is carried by the UAV and is operatively coupled to an immersible anchor. The immersible anchor is configured to be immersed within a body of water during a capture operation involving the capture line.

A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.