Abstract: A heating element for a vaporizer cartridge is provided. The vaporizer cartridge may include a reservoir containing vaporizable material and a wicking element in fluid communication with the reservoir. The heating element may include a heating portion, a cartridge contact, and a leg. The heating portion includes at least two tines spaced apart from one another. The cartridge contact may be in in electrical communication with a power source. The leg extends between the heating portion and the cartridge contact. The heating portion may be crimped around the wicking element such that the heating portion secures the wicking element to the heating element and contacts at least two surfaces of the wicking element.

Abstract: The combustion chamber and associated fuel injection and ignition equipment of a turbine engine is removed and replaced with a particle bed reactor. The reactor has central fuel elements removed to receive a shaft therein. The shaft is connected between a turbo compressor and drive turbine. Air compressed by the compressor turbine is heated by the reactor and the heated gas passes across rotor vanes of the drive turbine, the latter powering the interconnecting shaft. Exhaust gases from the drive turbine furnish resultant thrust.

Abstract: The inlet of a jet engine is equipped with a pivotally displaceable deflector which becomes deployed when the aircraft is in a stalled, horizontally stabilized condition. As the aircraft undergoes vertical descent, vertically impinging airflow is reflected off the interior surface of the deflector and flows coaxially through the inlet thereby forcing continued rotation of turbine blades. Hydraulic and electronic control devices deriving power from the turbine may be maintained operative even though the aircraft is in a stalled condition, thereby permitting limited horizontal maneuvering of the aircraft as the vertical descent continues.

Abstract: An autophage rocket has its casing constructed from KEVLAR-epoxy material which is itself combustible and stores liquid propellant. As the propellant is consumed during flight, the casing is combusted so that the pressure within the casing remains constant. A secondary nozzle is mounted to the outlet end of the rocket and cooperates with a ram-rocket construction to achieve additional impulse. A multiplicity of rocket motors are fed from a single stage tank to enable controlled motion of the rocket.