A motor vehicle system includes a motor vehicle including an aircraft landing portion, and an actively propelled unmanned aircraft configured to be supported on the aircraft landing portion. The vehicle and aircraft are configured such that the vehicle can provide at least one of fuel and electrical energy to the aircraft while the aircraft is supported on the aircraft landing portion.

A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power.

Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical input and even extinguished by interrupting the electrical to control a secondary thrust profile (e.g., amplitude, transition rates) to fulfill the needs of a given takeoff, inflight or landing maneuver and provide a smooth transition in and out of the maneuver. Multiple pairs of fixed thrusters (opposite sides of the fuselage), a single pair of gimbaled thrusters or a hybrid of fixed and gimbaled thrusters may be configured to provide all such maneuvers. Flight control inputs are passed back and forth through an interface to enable the thrust assist.

Disclosed is a remotely controlled wireless drone which employs a solid fuel rocket engine to propel it quickly to a desired or location. More specifically, an unmanned vehicle including a fuselage and a propulsion unit engaged with the fuselage, the propulsion unit being operable to bring the unmanned vehicle to a desired altitude or location, generally during a launch stage. The fuselage also includes multiple rotors pivotally engaged with the fuselage and a rotor positioning system operable to pivot the multiple rotors between stowed and deployed positions. The stowed position of the propellers minimizes drag and instability during the launch stage, and the deployed position allows the multiple rotors to control the position and altitude of the unmanned vehicle after the fuel of the rocket engine is spent. Submersible/amphibious and other embodiments are also described.

A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power.

An unmanned aerial combat vehicle system is disclosed. The system provides for an unmanned aerial combat vehicle that is capable of performing reconnaissance, disrupting enemy communications, or delivering a weaponized payload. The unmanned aerial combat vehicle may also be equipped with a cloaking mechanism, where it can mask it's heat signature, or simulate an image on its outer surface.

Systems and methods for calculating launch sites for a satellite constellation are provided. A carrier aircraft may be configured to launch a first satellite into the first orbit and a second satellite into the second orbit. In some embodiments, information about an accessible range of the aircraft may be received. Based on the received information, a geographical area that the aircraft can access without landing may be calculated. Using received information and the orbit parameters of the first orbit and the second orbit, a first launch site for launching the first satellite and a second launch site for launching the second satellite may be calculated. The first launch site may comprise a first geographical position and a first launch time, and the second launch site may comprise a second geographical position and a second launch time. Both launch sites may be within the calculated geographical area.

Methods and associated systems for autonomous package delivery utilize a UAS/UAV, an infrared positioning senor, and a docking station integrated with a package delivery vehicle. The UAS/UAV accepts a package for delivery from the docking station on the delivery vehicle and uploads the delivery destination. The UAS/UAV autonomously launches from its docked position on the delivery vehicle. The UAS/UAV autonomously flies to the delivery destination by means of GPS navigation. The UAS/UAV is guided in final delivery by means of a human supervised live video feed from the UAS/UAV. The UAS/UAV is assisted in the descent and delivery of the parcel by precision sensors and if necessary by means of remote human control. The UAS/UAV autonomously returns to the delivery vehicle by means of GPS navigation and precision sensors. The UAS/UAV autonomously docks with the delivery vehicle for recharging and preparation for the next delivery sequence.

A motor vehicle system includes a motor vehicle including an aircraft landing portion, and an actively propelled unmanned aircraft configured to be supported on the aircraft landing portion. The vehicle and aircraft are configured such that the vehicle can provide at least one of fuel and electrical energy to the aircraft while the aircraft is supported on the aircraft landing portion.

A drone launch system includes a canister defining an internal cavity, and a drone positioned within the internal cavity in a stowed state. The drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister. A method for launching a drone, the method includes positioning the drone in a stowed state in an internal cavity of a canister, ejecting the drone from the canister, and transitioning the drone into a deployed state after the ejecting operation.