Abstract: A composite material blank comprising an elongate blank body extending between a first end face and a second end face; said blank body extending in a longitudinal direction, parallel to a longitudinal axis thereof, and having four peripheral sides; each said first and second end face having edges which define a trapezoid shape; wherein the peripheral sides of said blank body connect the edges of said first end face with the edges of said second end face; and wherein said first trapezoid end face is inverted in relation to said second trapezoid end face. A method of manufacturing a composite blank, and a wind turbine blade root insert which may be formed from a blank.

Abstract: An insert (105) for a wind turbine blade root. The insert (105) has a bushing (40) and an outer surface with circumferential annular grooves (68). A transition layer (102) is built up around the bushing (40). The transition layer (102) has fibrous material sheet layers and filamentary material windings (80) in the grooves which alternate with fibrous plies (98) covering the grooves (68). Each fibrous ply (98) is anchored into the grooves (68) by the windings (80). Fibrous battens (148) are fitted around the transition layer (102) to form an insert body (108). Each batten (148) has a deltoid cross-section so that the battens give the insert a quadrilateral or trapezoidal cross-section.

Abstract: An insert (105) for a wind turbine blade root. The insert (105) has a bushing (40) and an outer surface with circumferential annular grooves (68). A transition layer 5 (102) is built up around the bushing (40). The transition layer (102) has fibrous material sheet layers and filamentary material windings (80) in the grooves which alternate with fibrous plies (98) covering the grooves (68). Each fibrous ply (98) is anchored into the grooves (68) by the windings (80). Fibrous battens (148) are fitted around the transition layer (102) to form an insert body (108). Each batten (148) 10 has a deltoid cross-section so that the battens give the insert a quadrilateral or trapezoidal cross-section.

Abstract: A composite material blank comprising an elongate blank body extending between a first end face and a second end face; said blank body extending in a longitudinal direction, parallel to a longitudinal axis thereof, and having four peripheral sides; each said first and second end face having edges which define a trapezoid shape; wherein the peripheral sides of said blank body connect the edges of said first end face with the edges of said second end face; and wherein said first trapezoid end face is inverted in relation to said second trapezoid end face. A method of manufacturing a composite blank, and a wind turbine blade root insert which may be formed from a blank.

Abstract: A composite material blank (190) comprising an elongate blank body (300) extending between a first end face (312a) and a second end face (312b); said blank body (300) extending in a longitudinal direction, parallel to a longitudinal axis thereof, and having four peripheral sides (341, 342, 343, 344); each said first and second end face (312a, 312b) having edges (361a-364a; 361b-364b) which define a trapezoid shape; wherein the peripheral sides (341, 342, 343, 344) of said blank body (190) connect the edges (361a-364a) of said first end face (312a) with the edges (361b-364b) of said second end face (312b); and wherein said first trapezoid end face (312a) is inverted in relation to said second trapezoid end face (312b). A method of manufacturing a composite blank (190), and a wind turbine blade root insert (105) which may be formed from a blank (190).

Abstract: A composite material blank (190) comprising an elongate blank body (300) extending between a first end face (312a) and a second end face (312b); said blank body (300) extending in a longitudinal direction, parallel to a longitudinal axis thereof, and having four peripheral sides (341, 342, 343, 344); each said first and second end face (312a, 312b) having edges (361a-364a; 361b-364b) which define a trapezoid shape; wherein the peripheral sides (341, 342, 343, 344) of said blank body (190) connect the edges (361a-364a) of said first end face (312a) with the edges (361b-364b) of said second end face (312b); and wherein said first trapezoid end face (312a) is inverted in relation to said second trapezoid end face (312b). A method of manufacturing a composite blank (190), and a wind turbine blade root insert (105) which may be formed from a blank (190).

Abstract: An insert (105) for a wind turbine blade root. The insert (105) has a bushing (40) and an outer surface with circumferential annular grooves (68). A transition layer 5 (102) is built up around the bushing (40). The transition layer (102) has fibrous material sheet layers and filamentary material windings (80) in the grooves which alternate with fibrous plies (98) covering the grooves (68). Each fibrous ply (98) is anchored into the grooves (68) by the windings (80). Fibrous battens (148) are fitted around the transition layer (102) to form an insert body (108). Each batten (148) 10 has a deltoid cross-section so that the battens give the insert a quadrilateral or trapezoidal cross-section.

Abstract: A wind turbine for use in a wide range of wind conditions is disclosed. The wind turbine uses blade pitch change and/or blade folding to accommodate wind conditions and maintain a substantially constant speed. The blades are configured to fold in unison for balanced wind turbine operation.

Abstract: The present invention provides a fast, low-cost, small diverter capable of generating a relatively high impulse (1-5 N-sec) over a short time period. The diverter is adapted for installation in a projectile for steering the projectile in flight by ejecting an end cap or hot burning gases in response to control signals from a guidance system. In one embodiment, multiple diverters are arranged in one or more bands about a flying projectile such as a rocket.

Abstract: The present invention provides a fast, low-cost, small diverter capable of generating a relatively high impulse (1-5 N-sec) over a short time period. The diverter is adapted for installation in a projectile for steering the projectile in flight by ejecting an end cap or hot burning gases in response to control signals from a guidance system. In one embodiment, multiple diverters are arranged in one or more bands about a flying projectile such as a rocket.

Abstract: The present invention provides a fast, low-cost, small diverter capable of generating a relatively high impulse (1-5 N-sec) over a short time period. The diverter is adapted for installation in a projectile for steering the projectile in flight by ejecting an end cap in response to control signals from a guidance system. In one embodiment, multiple diverters are arranged in one or more bands about a flying projectile such as a rocket. Each diverter includes a header assembly providing a mounting surface and support for a plurality of electrical leads, a reactive semiconductor bridge mounted on the mounting surface of the header assembly and providing an electrical path for the electrical leads at a certain voltage across the bridge, a diverter body supporting the header assembly and containing a prime, wherein the reactive semiconductor bridge and the prime define a gap, and an end cap attached to the diverter body and containing a propellant.

Abstract: Methods and systems for laser diode ignition of field cannons and weaponry. A series of one or more laser diodes or laser diode array, bars or stripes that are configured to optically pump a collimator which may be formed of materials to provide a lasing medium. The energy output of these devices can be combined when configured as an array or a series of redundant laser diodes assemblies to provide safe and reliable ignition systems. The collimator may direct the output from these laser diode assemblies as multiple collimated ignition beams. The laser diode assemblies may optically end pump and/or side pump the collimator or collimating rod to deliver a more directed energy output to artillery propellant. Additionally, the duration of the pulses may be controlled and extended as necessary to help ensure proper ignition of the propellant.

Abstract: The present invention provides a fast, low-cost, small diverter capable of generating a relatively high impulse (1-5 N-sec) over a short time period. The diverter is adapted for installation in a projectile for steering the projectile in flight by ejecting an end cap in response to control signals from a guidance system. In one embodiment, multiple diverters are arranged in one or more bands about a flying projectile such as a rocket. Each diverter includes a header assembly providing a mounting surface and support for a plurality of electrical leads, a reactive semiconductor bridge mounted on the mounting surface of the header assembly and providing an electrical path for the electrical leads at a certain voltage across the bridge, a diverter body supporting the header assembly and containing a prime, wherein the reactive semiconductor bridge and the prime define a gap, and an end cap attached to the diverter body and containing a propellant.

Abstract: The optical window is useful in laser-initiated explosive devices. It includes a solid transparent block of high temperature-resistant material such as glass, quartz, corundum, cubic zirconia or the like having two opposed light input and light output surfaces, one or both of which bear ablative mirror coatings of metal or the like, preferably aluminum, silver or gold, which can be vaporized by a laser beam. Preferably, the coatings are covered by a protective ablative film which resists scratching or the like. Such may be, for example, silicon monoxide. The coatings reflect incident light so as to prevent inadvertent initiation of explosive situated behind or downstream of the window in an explosive device. Preferably, the block is cylindrical with a curved light-focusing input surface which reduces the intensity which the laser beam trained through the window has to have in order to vaporize the mirror coatings and set off the explosive.

Abstract: The explosive initiator features an angled fiber optic adapter connected thereto. The initiator includes an elongated tubular cartridge with a longitudinal passageway having input and output ends and an explosive disposed therein downstream of a transparent sealing window and upstream of an output closure. The adapter has an elongated passageway therethrough with input and output ends and divided into a first portion at an angle of preferably 90 degrees from the longitudinal axis of the cartridge and a second portion in line with the cartridge. A mirror lens is positioned in the adapter passageway at the intersection of the two portions for reflecting a light beam from an optical fiber in the inlet end of the adapter to the cartridge passageway and focusing the light beam on the window. Preferably the second portion of the adapter is rotatably mounted to the cartridge.

Abstract: The improved focusing mirror lens reduces the ellipticity of the output beam of a laser diode or the like light source and corrects astigmatism of the beam so that beam light can be focused to a fine point. The lens has a monolithic, transparent, preferably cylindrical lens body of glass or the like, upon the opposite entrance and exit ends of which are coated focusing mirrors. At least one of the mirrors, and preferably both, has the configuration of a segment of a circular cylinder. The other mirror may have the configuration of a segment of a circular cylinder or of a sphere. The axes of the mirrors, when both are segments of a cylinder, are perpendicular to each other. Each of the mirrors has a light-transmitting unmirrored pupil aligned along the longitudinal axis of the lens body.

Abstract: The novel optical explosive initiator employs a window of a new type. The window hermetically seals the initiator explosive and is a transparent preferably monolithic block or cylinder of glass or the like solid material having a mirrored convex entrance end in the configuration of a segment of a spheroid, paraboloid, ellipsoid or hyperboloid and having an unmirrored opening therethrough along the longitudinal axis of the cylinder. The opposite exit end of the cylinder is mirrored and is perpendicular to the cylinder longitudinal axis and is at least nearly flat, preferably entirely flat. It includes an unmirrored opening along the longitudinal axis of the cylinder. An optical fiber transmitting light, such a laser light, can be positioned adjacent to the entrance opening.

Abstract: The method seals optical windows in explosive initiators so that the resulting seal remains undamaged by exposure to about - 320.degree.-840.degree. F. and pressures up to 26000 psi. The method includes disposing a solid body optical window of quartz or silica glass or the like in a passageway in a wall of an explosive initiator body of metal, ceramic or the like. The optical window is dimensioned relative to the passageway so that an annular space is provided between the outer periphery of the optical window and the passageway wall. This annular space is filled with solder glass, in powdered or solid body or slurry form. Preferably, the solder glass is a ring which closely fits around the optical window. The resulting sub-assembly preferably abuts a shelf in the passageway formed between two contiguous portions of the passageway with different diameters, the sub-assembly being in the larger portion.