Abstract: Some embodiments are directed to an apparatus, such as a panel that might be appropriate for aircraft or space vehicle fuel tanks. According to some embodiments, a plurality of stiffening elements may be attached to a matrix stiffened laminate skin and arranged in an isogrid pattern. Each stiffening element may include, for example, a hollow hat-shaped and substantially rectangular cross-sectional profile and a layer of unidirectional fibers proximate to a top portion of the stiffening element. In some embodiments, the stiffening elements may be created on top of a core element that is later removed (e.g., by dissolving, melting, or vaporizing the core element after the stiffening elements and fiber skin are cured with heat).

Abstract: Some embodiments are directed to an apparatus, such as a panel that might be appropriate for aircraft or space vehicle fuel tanks. According to some embodiments, a plurality of stiffening elements may be attached to a matrix stiffened laminate skin and arranged in an isogrid pattern. Each stiffening element may include, for example, a hollow hat-shaped and substantially rectangular cross-sectional profile and a layer of unidirectional fibers proximate to a top portion of the stiffening element. In some embodiments, the stiffening elements may be created on top of a core element that is later removed (e.g., by dissolving, melting, or vaporizing the core element after the stiffening elements and fiber skin are cured with heat).

Abstract: An adjustable fastening mechanism generally including an adjustable clasp and a cord. The adjustable clasp has an inlet end, a fastener end, and a center core therebetween. In the preferred embodiment the adjustable clasp has an inlet and a radial port which are connected by a conduit. The inlet end of the adjustable clasp is narrower than the fastener end of the adjustable clasp. A helical groove is provided on the exterior of the adjustable clasp and extends from the radial port to an exterior bore near the fastener end of the adjustable clasp. The exterior bore extends through the solid center core of the adjustable clasp and is substantially perpendicular to the center axis of the adjustable clasp and helical groove.

Abstract: A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for deflecting thrust during vertical flight of the aircraft. By manipulating the cascade and control box, the roll, yaw and pitch of the aircraft during vertical flight may be controlled. In addition, ailerons, a rudder and elevators may be provided for controlling roll, yaw and pitch during forward flight. A pilot control input apparatus is also provided, which receives pilot input regarding desired roll, yaw and pitch of the aircraft. The pilot control input is operatively associated with a control mixer, which controls the control box, ailerons, rudder and elevators in accordance with the desired roll, yaw and pitch of the aircraft. As a result, the pilot uses the same control input apparatus for vertical and forward flight.

Abstract: A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for deflecting thrust during vertical flight of the aircraft. By manipulating the cascade and control box, the roll, yaw and pitch of the aircraft during vertical flight may be controlled. In addition, ailerons, a rudder and elevators may be provided for controlling roll, yaw and pitch during forward flight. A pilot control input apparatus is also provided, which receives pilot input regarding desired roll, yaw and pitch of the aircraft. The pilot control input is operatively associated with a control mixer, which controls the control box, ailerons, rudder and elevators in accordance with the desired roll, yaw and pitch of the aircraft. As a result, the pilot uses the same control input apparatus for vertical and forward flight.

Abstract: A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for deflecting thrust during vertical flight of the aircraft. By manipulating the cascade and control box, the roll, yaw and pitch of the aircraft during vertical flight may be controlled. In addition, ailerons, a rudder and elevators may be provided for controlling roll, yaw and pitch during forward flight. A pilot control input apparatus is also provided, which receives pilot input regarding desired roll, yaw and pitch of the aircraft. The pilot control input is operatively associated with a control mixer, which controls the control box, ailerons, rudder and elevators in accordance with the desired roll, yaw and pitch of the aircraft. As a result, the pilot uses the same control input apparatus for vertical and forward flight.

Abstract: A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for deflecting thrust during vertical flight of the aircraft. By manipulating the cascade and control box, the roll, yaw and pitch of the aircraft during vertical flight may be controlled. In addition, ailerons, a rudder and elevators may be provided for controlling roll, yaw and pitch during forward flight. A pilot control input apparatus is also provided, which receives pilot input regarding desired roll, yaw and pitch of the aircraft. The pilot control input is operatively associated with a control mixer, which controls the control box, ailerons, rudder and elevators in accordance with the desired roll, yaw and pitch of the aircraft. As a result, the pilot uses the same control input apparatus for vertical and forward flight.

Abstract: A variable-geometry duct having at least one moveable side wall, and a bellows interposed between the side wall and a back-up structure. The bellows creates a sealed cavity between the moveable side wall of the duct and the back-up structure. Pressurized fluid in the cavity is controlled so as to maintain a desired pressure differential between it and the pressure of the fluid carried by the conduit for all positions of the moveable side wall.

Abstract: A jet aircraft is provided of the vertical or short take off and land (VSTOL) type which is a stable and controllable in all flight attitudes. The aircraft exhibits a high engine thrust/weight ratio which enables it to achieve shorter take-off, shorter landing distances and faster climbs as compared with prior art aircraft of the same general type. The aircraft includes two jet engines mounted side-by-side in its nose which assist in achieving smooth variation in cross-sectional area so that the area rule is not violated, and this enables efficient flight speeds in the sonic vicinity to be achieved. The exhaust of each engine of the aircraft is controlled by a thrust deflector and associated air foil array, the thrust deflector being deflected downwardly at an angle of substantially 75.degree.

Abstract: Apparatus and system for producing high pressure gas, such as high pressure coal gas from coal, air and water. Pulverized coal is introduced into a rising stream of steam in a central reaction column of a retort to constitute a fluidized or entrained bed. The coal reacts with the steam to form a gas consisting of hydrogen, carbon monoxide, carbon dioxide, nitrogen, methane and higher hydrocarbons. The retort is constructed so that product gas and air may be burned in an annular chamber surrounding the central reaction column to produce hot flue gas. The hot flue gas is used to drive a turbine which in turn, drives a compressor which introduces compressed air into the annular chamber. Steam tubes may be disposed in the annular space so that the steam introduced to the central reaction chamber may be super-heated by the hot flue gas.

Abstract: A two-position pilot-operated control unit is provided for reducing the fuel-to-air ratio and for simultaneously advancing the ignition of a piston-type aircraft engine so as to achieve a significant saving in fuel consumption during flight operations.

Abstract: Hydrogen is produced from water by the addition of heat to a series of chemical reactions which comprise the reaction of cadmium with water, and the subsequent recovery of the cadmium for re-use. The equipment used to produce the hydrogen requires only the input of water and heat to produce an output of hydrogen and oxygen gas.

Abstract: Hydrogen is produced from water by the addition of heat to a series of chemical reactions which comprise the reaction of cadmium with water, and the subsequent recovery of the cadmium for re-use. The equipment used to produce the hydrogen requires only the input of water and heat to produce an output of hydrogen and oxygen gas.