A vertical-takeoff-and-landing (“VTOL”) aircraft including a non-VTOL aircraft equipped for forward takeoff and flight and a modular boom system interoperably coupled to the non-VTOL aircraft. The modular boom system includes a first modular boom and a second modular boom. The first modular boom includes a first rocket-turbine engine. The first modular boom is mounted to a first wing of the non-VTOL aircraft. The second modular boom includes a second rocket-turbine engine. The second modular boom is mounted to a second wing of the non-VTOL aircraft.

An aerospace vehicle that permits horizontal launch and subsequent orbital deployment of a second stage. The vehicle can be returned to Earth for subsequent re-use. Both land-based and water-based launch is disclosed. A rocket propulsion engine is located at the center of gravity of the vehicle and rotates to provide vertical and horizontal thrust.

The present invention relates to a fire fighting system for transporting a nozzle of a fire hose coupled to a drone to a high place. The fire fighting system includes a fire hose (10) having a fire hose (10) having a nozzle (11) for injecting a fire extinguishing liquid; a fire-extinguishing-liquid supply source (2) which is coupled to the fire hose (10), and supplies the fire extinguishing liquid to the fire hose (10); a top drone (1) coupled to the nozzle (11); a wired cable (4) coupled to the top drone (1); and a power supply unit (3) which supplies power or fuel for flying the top drone (1) through the wired cable (4).

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.

An emergency landing apparatus for an aircraft and a method of operating the emergency landing apparatus is provided. The emergency landing apparatus comprises: one or more rocket motors arranged to eject efflux in order to provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and control circuitry configured to: cause the one or more rocket motors to eject efflux and provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and cause redirection of the efflux ejected by the one or more rocket motors, during the emergency landing of the aircraft, in order to reduce the upwards thrust provided by the one or more rocket motors.

Electric aircraft power plants and associated methods are provided. One power plant includes an emergency power unit (EPU) for providing electric power in the event of a malfunction of a battery pack of an electric aircraft to permit the electric aircraft to make an emergency maneuver. The EPU includes a rocket engine for generating a stream of exhaust fluid using a rocket propellant, a turbine operatively connected to extract energy from the stream of exhaust fluid generated by the rocket engine, and an electric generator operatively connected to be driven by the turbine and to supply electric power to an electric motor propelling the electric aircraft.

Disclosed is a system for a gas turbine engine, the gas turbine engine comprising a primary shaft, the system including a rotor shaft; a plurality of components connected to the rotor shaft, including a wound field synchronous main machine (MM) and a permanent magnet generator (PMG); and wherein the PMG, alone or with the MM provide torque to change rotational speed of the rotor shaft, thereby changing rotational speed of the primary shaft.

An optical heat exchanger and an associated system and method are provided to allow a vehicle, such as an unmanned air vehicle, a rocket or the like, to deliver more payload at a lower cost. The optical heat exchanger includes a support surface defining a plurality of tapered openings. Each tapered opening tapers from the first size proximate an outwardly facing end of the opening to a second smaller size proximate an inwardly facing end of the opening. The inwardly facing end of each tapered opening is in communication with the propellant. The optical heat exchanger also includes a plurality of lenses with each lens positioned proximate the outwardly facing end of a respective opening. Each lens is configured to receive an electromagnetic energy beam and concentrate the majority of the electromagnetic energy beam through the inwardly facing end of the respective tapered opening, thereby heating the propellant.

An aircraft includes a fuselage having an upper surface and a lower surface and a plurality of planetary modules housed in the fuselage, an individual planetary module having a first jet engine directed outward of the upper surface of the fuselage and a second jet engine directed outward of the lower surface of the fuselage, the individual planetary module rotatable within the fuselage about a vertical axis.

Disclosed is a system for a gas turbine engine, the gas turbine engine comprising a primary shaft, the system including a rotor shaft; a plurality of components connected to the rotor shaft, including a wound field synchronous main machine (MM) and a permanent magnet generator (PMG); and wherein the PMG, alone or with the MM provide torque to change rotational speed of the rotor shaft, thereby changing rotational speed of the primary shaft.