Abstract: A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member. A control method is further included.

Abstract: A system for providing marine propulsion is provided including an input shaft driven by a prime mover, a pinion gear coupled to the input shaft, a plurality of planet gears coupled to the pinion gear, a planet carrier having the plurality of planet gears rotationally mounted thereto, and a ring gear surrounding the planet gears and coupled thereto. The planet carrier and ring gear are coupled to internal and external output shafts that are coaxially aligned, which are coupled to aft and forward propulsor elements. The ring gear and planet carrier rotate in opposite directions to provide contra-rotating forward and aft propulsor elements. The ring gear and planet gear are each coupled to rotation altering devices that, when at least one is activated, the rotation of both the planet carrier and ring gear will be altered, thereby altering the rotation of the propulsor elements.

Abstract: The present invention is an aero engine that is provided with compression combustion and weighs less than 725 lbs. The present invention is further a method of forming the aero engine.

Abstract: The present invention is an aero engine that is provided with compression combustion and weighs less than 725 lbs. The present invention is further a method of forming the aero engine.

Abstract: A system for providing marine propulsion is provided including an input shaft driven by a prime mover, a pinion gear coupled to the input shaft, a plurality of planet gears coupled to the pinion gear, a planet carrier having the plurality of planet gears rotationally mounted thereto, and a ring gear surrounding the planet gears and coupled thereto. The planet carrier and ring gear are coupled to internal and external output shafts that are coaxially aligned, which are coupled to aft and forward propulsor elements. The ring gear and planet carrier rotate in opposite directions to provide contra-rotating forward and aft propulsor elements. The ring gear and planet gear are each coupled to rotation altering devices that, when at least one is activated, the rotation of both the planet carrier and ring gear will be altered, thereby altering the rotation of the propulsor elements.

Abstract: A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member. A control method is further included.

Abstract: An enhanced pulse detonation engine (PDE) system for application in an aircraft capable of vertical takeoff and vertical landing (VTOVL) is described. The PDE system described herein may be installed onto a round vehicle platform whereby many PDE chamber and ejector tube assemblies are mounted with the ejector tubes facing towards a rotating bladed fan which, in certain embodiments, provides VTOVL flight and gyro stabilization. The angle and design of the fan blades are such that when the fan is rotated by exhaust force, the fan pulls fresh air through the aircraft's interior ducting, cooling the assemblies and adding more air mass for lift. Ignition rotation is adjustable (with or opposite fan rotation) to maximize the fan's thrust output. The design of the fan blade angle is optimized to provide low acoustical detection, low exhaust thrust temperature signature, and maximum air pull-through for lift.

Abstract: An engine with a hybrid crankcase includes the crankcase being a composite construction having an exoskeleton formed of a non-ferrite material having no defined endurance limit as a material, the non-ferrite exoskeleton encapsulating a load bearing skeleton formed of a ferrite material, the ferrite material having a well defined endurance limit, whereby the skeleton acts to carry the highest engine loadings. A method of forming such an engine is further included.

Abstract: A filtration installation for a swimming pool (2) comprising a filter vessel (4) containing a filter bed (5), an inlet pipe (6) extending between the pool and the filter vessel, a return pipe (8) extending between the filter vessel and the pool, a reversible pump (9) enabling to generate, in a backwashing state, an upward flow of water through the filter bed, and a drain pipe (11) arranged for removing the water pumped by the pump in its backwashing state through the filter bed. In order to reduce the required controls of the installation and to make it easier for unskilled persons to maintain it, the upper portion (12) of the filter vessel is in liquid communication through the inlet pipe (6) with the water in the pool and the inlet pipe is provided with a one-way valve (10).

Abstract: An orbiting multi-rotor homopolar machine employs axially parallel, cylindrical, electrically conductive magnets arranged circumferentially around vertical axis of central stator ring, intimately contacting and engaging non-slip rolling between rotor magnets and stator. A bearing rotatably secures each end of each magnet to a corresponding electrically conductive circular endplate, each slightly wider than the stator. An electrically conductive axle located in the center of the stator rigidly attaches to one of the top circular endplate, and an electrically insulating bearing means attaches the center of bottom circular endplate to a coaxial inner cylinder, located between the axle and the stator.

Abstract: A redundant ignition system for an internal combustion engine is provided. When the internal combustion system is a waste spark system, opposite ends of first and second secondary windings of first and second coils, are coupled, respectively, to first and second sparkplugs, for igniting first and second cylinders. In one embodiment, a diode or similar structure prevents feedback from one coil to another coil.

Abstract: An engine for rotating a main drive shaft (14) from a plurality of power modules (18) arranged in a concentric circumferentially spaced relation about a main drive gear (12) secured to the main drive shaft (14). Each power module (18) has a pair of parallel cylinders (50) with associated pistons (52) therein connected to rocker arms (62) and Z-crank convertors (68) for rotating a power input gear (20) engaging the main gear (12) for rotating the main drive shaft (14).

Abstract: Two centrifugal pump and paddle type boat propulsion devices are mounted in astern outboard positions on two swingable vanes, respectively, projecting aft of a boat hull, spaced athwartships of the hull and swingable from positions inclined rearwardly and downwardly from the hull transom into upwardly and rearwardly inclined positions in which the rotors of the propulsion devices and rudders behind them are retracted above the level of the boat bottom.

Abstract: The conventional slotted valve plate of an axial piston pump-motor is replaced by an integral or separate barrel extension having a charge-discharge passageway leading to each cylinder. The passageways lead axially from the cylinders and then turn generally radially inward to open at ports in a circular-cylindrical bore in the extension which is coaxial with the barrel and main shaft axis. The end of a fixed pintle shaft extends into the bore. The pintle shaft has fluid supply and return passages that open to charge and discharge areas within the bore which, in turn, communicate through ports in the shaft with the ports in the barrel. The charge and discharge areas are divided by a diametrical wall, and bridges at the edges of the wall and between the pintle shaft ports serve as valves which sequentially close each barrel port and thereby separate the charge and discharge stages of operation of each cylinder.

Abstract: The pintle shaft of a radial piston hydraulic pump-motor is cantilevered from one end frame member by guideways which permit it to be moved laterally for adjustment of the speed, torque output and direction of rotation. A reaction assembly is journaled in a second frame member by means of the input-output shaft. The reaction assembly includes two reaction rings, one on either side of the cylinder block, which rotate on bearing blocks on the pintle shaft, the bearing blocks and shaft having interengaging parallel, flat slide surfaces which permit the shaft to be translated while still being in mutually supported and stabilized relation with the reaction rings. The side loads on the pintle shaft are counteracted by friction forces developed between the slide surfaces on the bearing blocks and pintle shaft so that the pintle shaft remains stable relative to the reaction assembly without direct mechanical support of its blind end against side loads.

Abstract: The efficiency of a radial piston hydraulic pump or motor is improved by making the ports in the block through which the hydraulic fluid flows from and back to the charge and discharge areas, respectively, of the pintle shaft asymmetrical about their centerlines in the axial direction, the area of the part of each port which lies on the side of the axial centerline remote from the supply and return passages in the pintle shaft being substantially greater than the area of the remaining part of the port. Similarly, the ports in the pintle shaft which communicate the charge and discharge areas to the ports in the block have greater areas in the portions thereof on the side of the axial centerline remote from the supply and return passages than in the portions on the side of the axial centerline nearer the supply and return passages.

Abstract: Marine propellers are constructed with a split-hub design, permitting adjustment of the pitch of the blades, and axial removability of the blade. By virtue of the axial removability of the blades, blades can be removed easily for repair or replacement without increasing the diametral clearance between the blade tips and a tunnel or nozzle of the type in which propellers are frequently disposed. Also, individual blades can be removed without the necessity of dropping the rudder, which is necessary in many vessels utilizing solid propellers. The blades have their spindles or roots clamped in the hub, such that axial adjustment of pitch can be achieved by reducing the clamping force. The hub preferably is formed in two sections, one section being mounted to or forming part of the propeller shaft, and including recesses which partially house the blade spindles or roots.