A base module may be used to receive and house one or more unmanned aerial vehicles (UAVs) via one or more cavities. The base module receives commands from a manager device and identifies a flight plan that allows a UAV to execute the received commands. The base module transfers the flight plan to the UAV and frees the UAV. Once the UAV returns, the base module once again receives it. The base module then receives sensor data from the UAV from one or more sensors onboard the UAV, and optionally receives additional information describing its flight and identifying success or failure of the flight plan. The base module transmits the sensor data and optionally the additional information to a storage medium locally or remotely accessible by the manager device.

Presently disclosed systems and methods are configured for in-flight retrieval of unmanned aerial vehicles (UAVs). Such systems generally include a retrieval ramp, a tether system including a tether, and a capture connector. The retrieval ramp is configured to be moved between a stowed configuration and an extended configuration, in which at least a portion of the retrieval ramp is positioned outside the aircraft for retrieval of the UAV. The tether system is moveable to a capture configuration, in which a terminal tether end of the tether is positioned beyond a terminal end of the retrieval ramp, typically outside of turbulence generated by the aircraft. The system is configured to position the retrieval ramp, the tether system, and the capture connector in order to engage the UAV with the capture connector. Once captured, the system may move the UAV into the aircraft as the tether is retracted towards a retracted configuration.

An aerodynamically shaped, active towed body includes a fuselage curved along its vertical and horizontal longitudinal plane. The fuselage has a unit chamber and a load chamber. A transverse plane of the fuselage is triangular, two upper corners being located on an upper face of the fuselage and a lower corner being located on a lower face of the fuselage. Each of two wings is subdivided into a small and a large segment. The small segment points downwards and is attached to the fuselage in a region of the lower corner and the large segment points upwards and is attached to the small segment. Each of the small segments comprise an additional load chamber. The towed body further includes a tail fin, rudders that are each adjustable by the control device and a coupling for the towing cable.

A system for delivering objects from a fixed-wing aircraft has a first tether having a connector on a deployed end, an anchor apparatus fixed to a point on the ground, a slide ring assembled over the first tether, a drag line connected to the slide ring by one end, and a drag-producing device connected to at a second end, and an object carrying apparatus connected by a support line. The aircraft is flown at an altitude in an orbit at a diameter and a speed such that the deployed first tether assumes a spiral pattern. An object is placed in the object-carrying apparatus and released from the aircraft, with the slide ring guiding along the first tether, and the drag-producing element slows descent of the object in the carrying apparatus in the spiral pattern until the object reaches the ground, where the object is removed from the object-carrying apparatus.

A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a radar antenna for bistatic reception of reflected radar pulses. The UAV operates with a flight profile in contested airspace. A tactical fighter aircraft having a radar transmitter for transmitting radar pulses operates with a flight profile in uncontested airspace. A communications data link operably interconnects the UAV and the tactical fighter aircraft, the communications data link transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the fighter aircraft.

A cone shaped docking and releasing mechanism provides rigid connection between a parent UAV and a sub UAV to form a spliced double unmanned aerial vehicle system with improved cruising duration ability by providing sub UAV battery with charging function. It comprises a parent UAV, a sub UAV and a docking mechanism with charging ports. The parent UAV and the sub UAV are connected with each other through the docking mechanism to form a double UAV system, the docking mechanism is a cone structure and comprises a charging output component connected with the parent UAV internal control system, a charging circuit connected with a sub UAV control system and a charging input component connected with the charging circuit.

A vehicle-based airborne wind turbine system having an aerial wing, a plurality of rotors each having a plurality of rotatable blades positioned on the aerial wing, an electrically conductive tether secured to the aerial wing and secured to a ground station positioned on a vehicle, wherein the aerial wing is adapted to receive electrical power from the vehicle that is delivered to the aerial wing through the electrically conductive tether; wherein the aerial wing is adapted to operate in a flying mode to harness wind energy to provide a first pulling force through the tether to pull the vehicle; and wherein the aerial wing is also adapted to operate in a powered flying mode wherein the rotors may be powered so that the turbine blades serve as thrust-generating propellers to provide a second pulling force through the tether to pull the vehicle.

A container is used to launch a small aircraft, such as an unmanned aerial vehicle (UAV), from a host aircraft. The container protects the UAV from stresses during the initial ejection from a launcher that is part of the host aircraft. The initial stresses may be due to turbulence in the vicinity of the host aircraft, high airspeed, and/or tumbling that may result from the ejection from the host aircraft moving at a high airspeed. The container may deploy a drag device, such as a drogue chute, to slow the container down and reorient the container, prior to deployment of the UAV from the container. During the time between ejection from the host aircraft and deployment from the container, the UAV may be powered up and acquire data, such as global positioning system (GPS) data, to allow the UAV a “hot start” enabling immediate mission commencement.

A disposable unmanned aerial glider (UAG) with pre-determined UAG flight capabilities. The UAG comprises a flight module comprising at least one aerodynamic arrangement; and a fuselage module comprising a container configured for storing therein a payload and having structural integrity. The container is pressurized so as to maintain structural integrity thereof at least during flight, so that the UAG flight capabilities are provided only when the container is pressurized.

In some embodiments, apparatuses and methods are provided herein useful to transport unmanned aircraft systems to delivery products. In some embodiments, gas-filled aerial transport and launch system, comprises: a transport aircraft comprising: a gas chamber; and a carrier compartment where the gas chamber induces a lifting force on the carrier compartment; at least one propulsion system; and a navigation control system that controls the direction of travel of the transport aircraft; wherein the carrier compartment comprises: an unmanned aircraft system (UAS) storage area configured to receive multiple UASs; and an UAS launching bay that enables the UAS to be launched while the transport aircraft is in flight and while the UAS is carrying a package to be delivered.