Abstract: A composite material fabrication method includes stacking a plurality of fiber layers and a first binder and curing the first binder to form a three-dimensional structure with a plurality of mesh openings, and filling the plurality of mesh openings with a plurality of fiber filaments of a fiber array and a second binder and curing the second binder. A plurality of first mesh openings of the plurality of mesh openings are connected in a first direction.

Abstract: A composite material fabrication method includes stacking a plurality of fiber layers and a first binder and curing the first binder to form a three-dimensional structure with a plurality of mesh openings, and filling the plurality of mesh openings with a plurality of fiber filaments of a fiber array and a second binder and curing the second binder. A plurality of first mesh openings of the plurality of mesh openings are connected in a first direction.

Abstract: An integrated heat shield which encloses a frame structure comprises a leading edge component, a left side component, a right side component, an optionally top component, an optional bottom component and an optional trailing edge subassembly, wherein the leading edge component and the left and right side components are directly, integrally co-cured on the frame structure while in a B-stage. The leading edge component and the left and right side components are shingle laminated to form ply angles to air flow. The leading edge component and the side components are scarf-jointed or step-jointed. The side components and trailing edge subassembly are also scarf jointed or step-jointed. The co-curing as well as the scarf or step joints makes the heat shield an integrated assembly. A method of manufacturing the integrated heat shield is further introduced.

Abstract: An integrated heat shield which encloses a frame structure comprises a leading edge component, a left side component, a right side component, an optionally top component, an optional bottom component and an optional trailing edge subassembly, wherein the leading edge component and the left and right side components are directly, integrally co-cured on the frame structure while in a B-stage. The leading edge component and the left and right side components are shingle laminated to form ply angles to air flow. The leading edge component and the side components are scarf-jointed or step-jointed. The side components and trailing edge subassembly are also scarf jointed or step-jointed. The co-curing as well as the scarf or step joints makes the heat shield an integrated assembly. A method of manufacturing the integrated heat shield is further introduced.

Abstract: A measurement and operation auxiliary device, for supporting a length measurement tool disposed on an object under test, especially when measuring dimensions of a large object under test with a large length measurement tool, includes a fastening element, a connection shaft, and a support unit. The fastening element is unfastenably coupled to the object under test. The connection shaft is disposed on the fastening element. The support unit has a receiving chamber and a through hole. The connection shaft is penetratingly disposed in the through hole to allow the support unit to be rotatably coupled to the fastening element. The receiving chamber receives the length measurement tool. With the measurement and operation auxiliary device, the bulky length measurement tool can be fixed to a location suitable for measuring the dimensions of the large object under test without another co-worker and in a convenient, labor-saving manner.

Abstract: A manufacture method of a three dimensional (3D) braided composite tube with a throat section includes: providing an assembled mandrel comprising an upper mandrel and a lower mandrel, and braiding an 3D braided inner layer on the upper mandrel; winding fiber yarns to form a fiber yarn layer over the 3D braided inner layer; tightening the 3D braided inner layer to the assembled mandrel by an appropriate tension force when winding; and infiltrating resin and increasing temperature to cure the resin for obtaining a composite tube with a narrower throat section. The present invention takes advantage of winding fiber yarn outer layer to keep the radius of the throat of the 3D braided inner layer to meet design requirement. Additionally, the hoop strength of the throat section is increased so that the metal shell can be made thinner to reduce the weight of the rocket nozzle.

Abstract: A manufacture method of a three dimensional (3D) braided composite tube with a throat section includes: providing an assembled mandrel comprising an upper mandrel and a lower mandrel, and braiding an 3D braided inner layer on the upper mandrel; winding fiber yarns to form a fiber yarn layer over the 3D braided inner layer; tightening the 3D braided inner layer to the assembled mandrel by an appropriate tension force when winding; and infiltrating resin and increasing temperature to cure the resin for obtaining a composite tube with a narrower throat section. The present invention takes advantage of winding fiber yarn outer layer to keep the radius of the throat of the 3D braided inner layer to meet design requirement. Additionally, the hoop strength of the throat section is increased so that the metal shell can be made thinner to reduce the weight of the rocket nozzle.

Abstract: The invention provides a semi-continuity fiber prepreg material, a manufacturing method thereof, and a composite material made of the semi-continuity fiber prepreg material. The semi-continuity fiber prepreg material includes a plurality of intermittency notches and/or continuity notches formed on a fiber prepreg material along at least one direction to make the fiber prepreg material soft and suitable for molding.

Abstract: The invention provides a semi-continuity fiber prepreg material, a manufacturing method thereof, and a composite material made of the semi-continuity fiber prepreg material. The semi-continuity fiber prepreg material includes a plurality of intermittency notches and/or continuity notches formed on a fiber prepreg material along at least one direction to make the fiber prepreg material soft and suitable for molding.

Abstract: The invention provides a semi-continuity fiber prepreg material, a manufacturing method thereof, and a composite material made of the semi-continuity fiber prepreg material. The semi-continuity fiber prepreg material includes a plurality of intermittency notches and/or continuity notches formed on a fiber prepreg material along at least one direction to make the fiber prepreg material soft and suitable for molding.

Abstract: An angle-laminated composite tube with double layer of materials uses an inner layer material and an outer layer material with different functional properties. The two materials are cut into a plurality of slices in a specific shape. They are laminated alternately with a mismatching angle inside a mold with a specific angle to form a laminated assembly. Finally, a hot press is used to cure the laminated assembly into a structure with an inner layer, an outer layer, and an interlacing layer. The slice shape of the inner layer material and the outer layer material is specifically designed so that the inner layer, the outer layer, and the interlacing layer receive an even pressure during the curing process, rendering desired densities in the layers. The angle-laminated composite tube can achieve a high structural strength, with the inner and outer parts satisfying different functional needs.

Abstract: An angle-laminated composite tube with double layer of materials uses an inner layer material and an outer layer material with different functional properties. The two materials are cut into a plurality of slices in a specific shape. They are laminated alternately with a mismatching angle inside a mold with a specific angle to form a laminated assembly. Finally, a hot press is used to cure the laminated assembly into a structure with an inner layer, an outer layer, and an interlacing layer. The slice shape of the inner layer material and the outer layer material is specifically designed so that the inner layer, the outer layer, and the interlacing layer receive an even pressure during the curing process, rendering desired densities in the layers. The angle-laminated composite tube can achieve a high structural strength, with the inner and outer parts satisfying different functional needs.

Abstract: A dual-layered thermal insulation composite panel includes an out layer of high-temperature resistant carbon fiber reinforced phenolic resin composite and an inner layer of low thermal conductivity and high-purity silica fiber reinforced phenolic resin composite. A hot press or autoclave may be used to pressurize said materials into shaping. The dual-layered thermal insulation composite panel achieves excellent performance in thermal resistance, thermal insulation and mechanical strength.

Abstract: A manufacture method of a laminated hollow composite cylinder with an arranged ply angle is disclosed. The fiber in the hollow composite cylinder can be arranged in an angle ? between 30° and 60° according the applications. Prepregs were cut into fan-shaped pieces and laminated in a metal mold to form an annular lamina assembly. The metal mold comprises a concave female mold and a convex male mold that both have a tapered angle complying with the ply angle ?. Hot press molding with pressure over 140.6 kg/cm2 was then used for solidifying the lamina assembly to produce the composite hollow cylinders with the ply angle ?. The laminated hollow composite cylinder can achieve excellent thermal and mechanical properties to meet design requirements.