To provide a method of manufacturing a shaft-shape composite member in which a bent section is suitably treated. A plurality of thermosetting fiber-reinforced resin materials made of a UD material is supplied to a bending section of a mold in a state of being aligned in parallel to an axial direction of a cavity to form a UD material layer. Subsequently, after forming a tubular member having the UD material layer by the metal mold, by thermally curing the tubular member, the shaft-shape composite member having the bent section can be obtained. When manufacturing the shaft-shape composite member, a cross-section orthogonal to the axial direction of each of the fiber-reinforced resin materials has a circular shape.

Various implementations include a method of curing of thermoset resin. The method includes disposing one or more thermoset resin layers in a layup; disposing one or more heaters in the layup, wherein each of the one or more heaters includes two electrodes, wherein the two electrodes of each of the one or more heaters are couplable to an external electricity source when the one or more heaters are disposed in the layup; and providing enough electricity to the electrodes of each of the one or more heaters to cause the one or more heaters to heat the layup to fully cure the one or more thermoset resin layers to form a cured laminate.

There is provided a method of manufacturing a composite structure of an aircraft. The composite structure includes a skin and a reinforcing material. The method includes, by stacking unhardened composite sheets on a region of a jig adjacent to a holding portion to hold the reinforcing material, forming a skin inner layer including a retainer to retain two end portions of a flange of the reinforcing material in a width direction of the flange. The method includes installing the reinforcing material at the holding portion of the jig so that the two end portions abut upon the retainer. The method includes, by stacking unhardened composite sheets on an outer surface of the flange and on an outer surface of the skin inner layer, forming a skin outer layer. The method includes hardening the skin inner layer and the skin outer layer.

An ultrasonic transducer and generator (TAG) assembly of a surgical instrument includes generator components and transducer components. The generator components are disposed within a first cavity cooperatively defined by a body portion and a cover. The generator components are covered in a thermally insulative material. The transducer components are disposed within a second cavity cooperatively defined by a proximal housing and a spinner housing.

An ultrasonic transducer and generator (TAG) assembly of a surgical instrument includes generator components and transducer components. The generator components are disposed within a first cavity cooperatively defined by a body portion and a cover. The generator components are covered in a thermally insulative material. The transducer components are disposed within a second cavity cooperatively defined by a proximal housing and a spinner housing.

A fibrous preform (1) is produced, provided with a sandwich structure comprising an intermediate flexible core (4) and two outer fibrous frames (2, 3), respectively arranged on opposing outer faces of said flexible core (4) and assembled by sections of wire (8, 9) passing through said fibrous frames (2, 3), said preform (1) being impregnated with resin. Said preform is then hardened and the core (4) is removed, preferably by pre-densification with chemical vapour infiltration, and the structure produced is then densified with liquid-phase infiltration.

A non-metallic flange isolation gasket kit sealing flanged pipeline connections and flanged vessel connections while providing electrical isolation protection between flanges suited for high-pressure and high-temperature cathodic protection applications is presented. The invention protects flange faces from media induced corrosion and mitigates flange rotation induced fatigue and failures. The invention comprises of a retainer, a seal, and a seal pre-load structural ring. The seal pre-load structural ring is inserted into the seal, and seal outer diameter surface is joined to the retainer inner diameter surface. A second embodiment comprises of a composite gasket blank, comprising of a retainer and a seal, and a seal pre-load structural ring. The seal outer diameter surface and the retainer inner diameter surface are joined by thermal fusion bonding. The invention may further comprise one or more gasket seating stress stabilizers and/or a centering ring. Tapered retainer upper and lower surfaces decrease flange rotation.

The present invention pertains to a method for producing a long-fiber composite in which a fiber bundle is impregnated with a non-Newtonian resin. More specifically, the present invention pertains to a method for producing a thermoplastic long-fiber composite, wherein the efficiency of a non-Newtonian resin impregnation process is improved using Equation 1 representing the correlation between the penetration pressure, effective viscosity, transverse permeability, and average penetration velocity of the non-Newtonian resin, and the thickness of the fiber bundle.

An orthopedic component having multiple layers that are selected to provide an overall modulus that is substantially lower than the modulus of known orthopedic components to more closely approximate the modulus of the bone into which the orthopedic component is implanted. In one exemplary embodiment, the orthopedic component is an acetabular shell. For example, the acetabular shell may include an outer layer configured for securement to the natural acetabulum of a patient and an inner layer configured to receive an acetabular liner. The head of a femoral prosthesis articulates against the acetabular liner to replicate the function of a natural hip joint. Alternatively, the inner layer of the acetabular shell may act as an integral acetabular liner against which the head of the femoral prosthesis articulates.

A device for consolidating a fiber preform to obtain a panel made of composite material of large dimension, comprising an induction heating system configured to generate at least one electromagnetic field in a heating zone, at least one susceptor incorporated in a first die tool supporting the fiber preform and/or a cladding covering the fiber preform, each susceptor producing a uniform heating of the fiber preform when it is positioned in the electromagnetic field of the induction heating system, and a mechanism configured to induce a relative movement between the induction heating system and the first die tool so that all the fiber preform crosses the heating zone.