Abstract: A linear aerospike rocket engine has a tapered body, a slanted or curved reaction plane, a leading end, and a trailing end. A first fuel injector is located at the leading end and directs a first fuel towards the reaction plane. A second fuel injector is located in between the leading end and trailing end and directs a second fuel towards the reaction plane. The second fuel injector helps to increase propulsive pressure across the reaction plane and inhibit boundary layer separation. A vortex may be induced parallel to the reaction plane to help increase propulsive pressure across the reaction plane. The vortex is induced using a flap or spoiler, a rotatable turbine, or at least two fuel injectors that direct fuel in counter current directions across the reaction plane. The reaction plane may be corrugated, dimpled, grooved, or coated with a special material to inhibit boundary layer separation from the reaction plane.

Abstract: A manifold alternator generator including a turbine located proximal to a flow of exhaust gases in an internal combustion engine where the exhaust gases energize the turbine and produce rotation of an output shaft. The output shaft is connected to a rotor that is engaged with a generator such that the rotation of the turbine and output shaft generates electrical power. The manifold alternator generator may be used in combination with electromagnetic valve actuators and a flywheel alternator/starter. A processor may be used to optimize the performance of the manifold alternator generator and other system components.

Abstract: A linear aerospike rocket engine has a tapered body, a slanted or curved reaction plane, a leading end, and a trailing end. A first fuel injector is located at the leading end and directs a first fuel towards the reaction plane. A second fuel injector is located in between the leading end and trailing end and directs a second fuel towards the reaction plane. The second fuel injector helps to increase propulsive pressure across the reaction plane and inhibit boundary layer separation. A vortex may be induced parallel to the reaction plane to help increase propulsive pressure across the reaction plane. The vortex is induced using a flap or spoiler, a rotatable turbine, or at least two fuel injectors that direct fuel in counter current directions across the reaction plane. The reaction plane may be corrugated, dimpled, grooved, or coated with a special material to inhibit boundary layer separation from the reaction plane.

Abstract: A linear aerospike rocket engine has a tapered body, a slanted or curved reaction plane, a leading end, and a trailing end. A first fuel injector is located at the leading end and directs a first fuel towards the reaction plane. A second fuel injector is located in between the leading end and trailing end and directs a second fuel towards the reaction plane. The second fuel injector helps to increase propulsive pressure across the reaction plane and inhibit boundary layer separation. A vortex may be induced parallel to the reaction plane to help increase propulsive pressure across the reaction plane. The vortex is induced using a flap or spoiler, a rotatable turbine, or at least two fuel injectors that direct fuel in counter current directions across the reaction plane. The reaction plane may be corrugated, dimpled, grooved, or coated with a special material to inhibit boundary layer separation from the reaction plane.

Abstract: An engine for an aerospace plane has an inlet in association with which a core member is provided to render the inlet annular. The inlet leads into a combustion chamber and an outlet. The core member houses a rocket engine which, in use, induces ambient air to flow into the inlet at low and even zero speed, thus allowing the combustion chamber and outlet to be operated as a ram jet engine at low and even zero speed. By way of development, the core member houses oxygen liquification means adapted to capture ambient air and to liquify and separate oxygen therefrom. The oxygen is used in the rocket engine and allows the mass of on-board oxygen at take-off to be reduced. This increases the potential payload.

Abstract: An engine suitable for use in an aerospace plane is a composite engine comprising, in combination, a turbo jet engine, a ram jet engine, and a rocket engine, all arranged co-axially. An aerospace plane comprises such an engine mounted in a body defining, toward a rear thereof, in association with said engine, a nozzle surface which extends rearwardly in curved, concave manner, and which is part-round in cross-section, said or each nozzle surface being arranged in relation to a nozzle of said engine to be an extension of the nozzle.

Abstract: Conditioned air (i.e. cooled or heated air) is supplied to spaces in a building structure via guides and air mains. The conditioned air is guided into the spaces directly from the guides, or via plenum chambers and transfer openings, or via both routes simultaneously. Circulation of conditioned air through the plenum chambers cools/heats the building structure. During a subsequent period when cooled/heated air is demanded for the spaces, air from the spaces is circulated through the plenum chambers via air return openings. Such circulated air is cooled/heated by contact with the building structure and is re-introduced as conditioned air. The building structure thus acts as a reservoir of heat to augment the conditioning effort of the air conditioning means during periods of peak demand.