A technique for operating unmanned aerial vehicles (UAVs) in a terminal area from which the UAVs are staged includes charging a plurality of the UAVs on charging pads disposed in a staging array at the terminal area. Merchant facilities for preparing packages for delivery by the UAVs are disposed about a periphery of the staging array. The UAVs are relocated under their own propulsion from interior charging pads to peripheral loading pads of the staging array as the peripheral loading pads become available and the UAVs are deemed sufficiently charged and ready for delivery missions.

The disclosed embodiments are directed to a modular autonomous vehicle system comprising a blended wing body module, at least two high speed long range wing panel modules configured to interchangeably mount to the blended wing body module, at least two low speed high endurance wing panel modules configured to interchangeably mount to the blended wing body module, a vertical tails module configured to interchangeably mount to the blended wing body module, a vertical takeoff and landing fin module configured to interchangeably mount to the blended wing body module, a power train, and a wheels module with a plurality of wheels operably connected to the power train.

The disclosed embodiments are directed to a modular autonomous vehicle system comprising a blended wing body module, at least two high speed long range wing panel modules configured to interchangeably mount to the blended wing body module, at least two low speed high endurance wing panel modules configured to interchangeably mount to the blended wing body module, a vertical tails module configured to interchangeably mount to the blended wing body module, a vertical takeoff and landing fin module configured to interchangeably mount to the blended wing body module, a power train, and a wheels module with a plurality of wheels operably connected to the power train.

In some embodiments, unmanned aerial task systems are provided that include a plurality of unmanned aerial vehicles (UAV) each comprising: a UAV control circuit; a motor; propulsion system; and a universal coupler configured to interchangeably couple with and decouple from one of multiple different tool systems each having different functions to be put into use while carried by a UAV, wherein a coupling system of the universal coupler is configured to secure a tool system with the UAV and enable a communication connection between a communication bus and the tool system, and wherein the multiple different tool systems comprise at least a package securing tool system configured to retain and enable transport of a package while being delivered, and a sensor tool system configured to sense a condition and communicate sensor data of the sensed condition to the UAV control circuit over the communication bus.

An unmanned aerial vehicle (UAV) includes: a fuselage and a battery module. The fuselage has a bottom facing a ground level. The battery module includes a battery. The battery has a top portion facing the bottom of the fuselage. The top portion of the battery is disposed below the bottom of the fuselage.

In some embodiments, systems, apparatuses and methods are provided to enhance delivery of packages and/or cargo through the use of unmanned delivery aircraft. In some embodiments, a portable unmanned delivery aircraft launch system is provided that comprises: a first portable launch pad system comprising: a package deck; an unmanned delivery aircraft deck secured with the package deck and positioned above and separated by a distance from the package deck; and multiple modular coupling structures fixed with a frame enabling temporary rigid coupling and decoupling between the first launch pad system and multiple additional portable launch pad systems.

An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

A method of operating an aircraft includes, prior to an in-flight refueling operation, operating the aircraft using fuel from a first fuel tank connected to a fuel delivery system. Subsequently, the in-flight refueling operation is performed over a refueling area while operating the aircraft from another fuel tank, including (1) disconnecting the first fuel tank from the fuel delivery system, (2) jettisoning the first fuel tank, and (3) taking on a replacement fuel tank by (a) capturing the replacement fuel tank from the refueling area and (b) bringing the captured replacement fuel tank onboard the aircraft. The replacement fuel tank is then connected to the fuel delivery system and the aircraft is operated using fuel from the replacement fuel tank.

A modular payload airframe section for an aircraft airframe is disclosed. The modular payload airframe section comprises: a storage volume for receiving a payload; a releasable fixation means for releasably affixing the modular payload airframe section to an airframe of the aircraft; and wherein the modular payload airframe section forms at least part of a nose-cone of the aircraft airframe when affixed thereto.