Abstract: An igniter for use in aircraft gas turbine and rocket engines that derives its energy from a directly connected magnetron. The igniter is intended to be mounted exterior of the engine, and to protrude into the engine's combustion chamber. The magnetron energy is conductively connected to one end of a coaxial transmission line. The other end of the transmission line is at a region of high potential, and there is a small gap between the inner and outer transmission line conductors in that region. A gas comprised of either an oxidizer or fuel is flowed past the gap, and into the combustion chamber of the engine. The high potential causes a plasma to be formed in the gas, which plumes into the combustion chamber and ignites the propellants flowing therein.

Abstract: A flame stabilizing system for an augmentor, or a ramjet engine, which utilizes continuously operating microwave powered plasma plume igniters to generate a stable source of ignition for the flowing combustible mixture within the augmentor combustion chamber.

Abstract: A microwave driven self-starting plasma plume igniter for aircraft gas turbine engines. In the preferred embodiment, microwave energy is generated by a magnetron and transmitted through a waveguide and coaxial transmission line. The coaxial transmission line terminates with a corner at the end of the inner conductor being opposed to a corner on the outer conductor, creating a region where the electromagnetic stress will be concentrated, and a self-starting plasma will be created. Air flow through the coaxial transmission line blows the plasma plume out of the end of the coaxial transmission line. In the preferred embodiment, The outer conductor of the coaxial transmission line terminates in a cap with a central hole and the inner conductor terminates even with or slightly behind the inner wall of the outer conductor cap. The corner on the end of the inner conductor is thus opposed to the interior corner on the outer conductor formed by the hole through the cap.

Abstract: A system for re-igniting an aircraft gas turbine jet engine which has flamed out, using a plurality of electromagnetic wave powered plasma plume igniters in an intermittent mode to avoid compressor stall, and bootstrap the engine back up to normal operating conditions. The system uses electromagnetic wave powered plasma plume igniters to provide a source of thermal energy to ignite fuel, and the Fully Automatic Digital Engine Control (FADEC) which is a standard component on aircraft using aircraft gas turbine jet engines, to control the igniter operation preventing compressor stall during the re-ignition process.

Abstract: A water vehicle particularly suited for recreational use and designed to simulate the control and excitement of motorcycles, dune buggies and the like. These water vehicles are characterized as having a forward planing surface and rear hydrofoil members disposed so as to support the majority of the weight of the vehicle and passengers when operating at high speed. Sufficient lateral buoyancy is provided for flotation and low speed operation by a pair of spaced apart float assemblies toward the rear of the vehicle. The winglike members between the float assemblies and the vehicle body and the other hydrodynamic surfaces are designed to allow transition from low speed to high speed operation with a minimum of propulsive power required. Power may be provided by conventional outboard motors of a reasonable range of sizes, with stable but responsive control during high speed operation being provided by a combination of the steering apparatus and the spacing and support capability of the hydrofoils.