Abstract: In a hybrid flight vehicle, having four rotors configured to produce thrust to propel a frame, a gas turbine engine incorporating a compressor and a first turbine adapted to rotate integrally with the compressor, a generator configured to generate electric power, a battery configured to store power generated by the generator, four motor-generators connected to the battery and the multiple rotors to drive the rotors when power is supplied from the battery, while generating power when driven by the rotors. In the vehicle, there is provided a second turbine provided independently of the gas turbine engine and configured to drive the rotors when supplied high pressure gas outputted from the gas turbine engine.

Abstract: An engine, a power generation system, and methods of manufacturing and using the same are disclosed. The engine includes a detonation/combustion chamber configured to detonate a fuel and rotate around a central rotary shaft extending from the chamber, a fuel supply inlet configured to provide the fuel to the chamber, an air supply channel configured to supply air to the chamber, at least two rotating arms extending radially from the chamber and configured to exhaust gases from detonating the fuel in the chamber and provide a rotational thrust and/or force, and a mechanical work unit configured to receive at least part of the rotational thrust and/or force. Each of the rotating arms has an exhaust nozzle at a distal end thereof, the exhaust nozzle being at or having an angle configured to provide the rotational thrust and/or force.

Abstract: Circular propulsion jet compressor-engine, through a circular combustion chambers propellants spheroidal geometry set, generates a tangential push the turning radius and therefore resulting angular momentum about the shaft of the circle in rotation. This impulse is the consequence of the principle of action-reaction, the violent expansion that occurs inside the combustion chamber, when burning mixtures of fuel and oxidizer at high pressure, or by merging a small mass of H2, encapsulated and simultaneously subjected to very high pressure, constant electromagnetic fields and high-frequency electric fields and high peak intensity. The high pressure on the oxidant or H2, is achieved using the force resulting from the centripetal acceleration shaft rotating about a significant mass of a piston, solid or liquid and alternatively or cyclically. The gases and vapors produced are cooled inside the engine.

Abstract: A rotor blade assembly is disclosed including a blade spar having a duct extending therethrough and having upper and lower surfaces. A mounting structure is secured to the blade spar and defines a fluid path in fluid communication with the duct. The mounting structure likewise has upper and lower surfaces. A tip jet is secured to the mounting structure in fluid communication with the fluid path. The blade spar and mounting structure abut one another at a joint and the upper surfaces of the blade spar and mounting structure lie on a common airfoil contour extending across the joint. The lower surfaces of the blade spar and mounting structure also lie on the common airfoil contour. One or both of the blade and mounting structure include a composite material. The mounting structure may include two portions secured to one another having a distal portion of the blade spar captured therebetween.

Abstract: The present invention comprises, in one embodiment, an inexpensive, lightweight flying vehicle using fixed pitch helicopter blades powered by ramjet engines mounted to a power-ring which transfers torque to the lifting rotors. The use of fixed pitch blades eliminates the need for a tail boom and tail rotor, as well as for variable incidence control of blade pitch and/or cyclic and collective rotor-pitch controls. An optional ballistic parachute may be deployed for emergency landings. A radial shroud encloses the ramjet engines to act as a sound shield. Since the rotor has a fixed pitch, lift may be controlled by rotor speed, where increased speed results in ascent, and decreased speed, descent.

Abstract: A gas compressor based on the use of a driven rotor having an axially oriented compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which forms a supersonic shockwave axially, between adjacent strakes. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the gas compression ramp on a strake, the shock capture lip on the adjacent strake, and captures the resultant pressure within the stationary external housing while providing a diffuser downstream of the compression ramp.

Abstract: A method of simulating aerial images of large mask areas obtained during the exposure step of a photo-lithographic process when fabricating a semiconductor integrated circuit silicon wafer is described. The method includes the steps of defining mask patterns to be projected by the exposure system to create images of the mask patterns; determining an appropriate sampling range and sampling interval; generating a characteristic matrix describing the exposure system; inverting the matrix to obtain eigenvalues as well as the eigenvectors (or kernels) representing the decomposition of the exposure system; convolving the mask patterns with these eigenvectors; and weighing the resulting convolution by the eigenvalues to form the aerial images. The method is characterized in that the characteristic matrix is precisely defined by the sampling range and the sampling interval, such that the sampling range is the shortest possible and the sampling interval, the largest possible, without sacrificing accuracy.

Abstract: A helicopter aircraft with an upper hollow center circular plenum in gaseous communication with a plurality of hollow hinged attached rotor blades. Below the plenum and in gaseous communication with it are two fan jet engines whose gaseous output can be inputted to the plenum and their attached hollow rotor blades through a operator controlled valve system. This same valve system can be adjusted to completely or partially by-pass the plenum and discharge the jet engines' gas to a common rear rudder located on the aircraft's to provide directional control to the aircraft when in flight. The plenum is shaped lenticular in cross section similar to an airplane wing to provide a lifting body when the helicopter is in forward flight.

Abstract: An improved saddle stitching apparatus has dual scoring disks which cooperate with a scoring drum to create a flat spine on a cover. In one embodiment, a split ring is provided with two clamp arms, so that the ring can be releasably secured to the scoring drum. The ring includes a pair of annular grooves, with the distance between the grooves being of the desired spine width. The scoring disks are positioned adjacent the grooves so as to form the scoring lines. A folding assembly is also disclosed, which utilizes a flat carrying belt and a V-belt for purposes of folding the cover and moving the cover toward a stitching station. A gathering chain is also utilized to deliver the cover and signatures to the stitching station. The station includes a guide to assist in directing the preassembled covers and signatures toward a stitching head. Also provided is a block guide and an anvil for assistance in centering the spine beneath the stitching head.

Abstract: A jet-propelled rotary engine comprises a housing, a rotor journalled to the housing for rotation of the rotor about an axis, and at least one jet assembly secured to the rotor and adapted for combustion of a pressurized oxygen-fuel mixture. The jet assembly includes a hollow body having a closed leading end and an open trailing end downstream of the leading end. The hollow body defines a chamber having a combustion region where the pressurized oxygen-fuel mixture reacts during combustion to form combustion reaction products, a throat region downstream of the combustion region, a converging region extending from the combustion region to the throat region, and a diverging region extending from the throat region to the trailing end. The combustion reaction products form at least a part of thrust matter passing through the hollow body and discharged therefrom. The converging and diverging regions are configured for increasing the kinetic energy of and expanding the thrust matter.

Abstract: A flywheel engine includes a flywheel body made up of laminated disks, pressed one into another on a central drive shaft. Individual ones of the disks are stamped with recesses which accommodate jet or rocket propulsion housings, electrical wiring, and fuel delivery passages. The propulsion housings are removably mounted in the flywheel body to permit interchange with other propulsion devices according to thrust requirements. The propulsion housings are oriented to produce thrust on thrust axes that are substantially tangential to the rotational path of the flywheel body edge surface. Fuel and combustion supporting oxygen are delivered to the individual propulsion housings through the central shaft.

Abstract: A rotary internal combustion engine is shown having a combination of reaction nozzle means and turbine elements to extract energy from a stream of hot gases. A centrifugal air compressor feeds a rotary diffusion combustion chamber to operate the reaction nozzles. The products of combustion issuing from the nozzles are redirected by stationary vanes to drive a turbine to extract further energy from the gas flow as it passes to the exhaust.