Abstract: The invention relates to the field of composite materials and can be used for the manufacture of parts and structures made of composite materials, such as brackets, fittings, basic parts, wearable products, mesh and honeycomb structures for use in aviation, rocket and space technology, medicine, automotive industry, etc. The reinforcing composite filament which contains a roving of reinforcing fibers impregnated with a thermosetting binder and has a cross section in the shape of a circle 0.1-0.7 mm in diameter or an ellipse with ellipticity from 1 to 2 and the largest diameter of 0.1-0.7 mm; and the impregnated roving is subjected to heat or other treatment right up to a complete curing of the thermosetting binder. With the help of the claimed composite filament, a prepreg can be made by adding a thermoplastic binder. And also the tape can be produced by connecting the claimed filament or prepreg with the use of cross-links made of thermoplastic material.

Abstract: The invention relates as a whole to composite structures and may be used, in particular, in the manufacture of bodies or compartments of flying vehicles used in rocketry and aeronautics.A composite shell shaped as a body of revolution comprises a load-bearing framework of a multilayer structure consisting of intersecting spiral and annular strips arranged at intervals and forming cross nodes and stiffening ribs therebetween, an outer load-bearing shell, fine-cellular layers consisting of spiral and annular strips therebetween, surrounding the stiffening ribs of the framework in the directions thereof, and having the width exceeding the width of the strips in the ribs and forming their bearing flanges. The spiral and annular strips of the framework and of the fine-cellular layers, and the outer load-bearing shell are made of unidirectional fibers and a polymer binder.

Abstract: The invention relates as a whole to composite structures and methods of forming thereof and can be used in particular, in the manufacture of bodies and compartments of flying vehicles used in rocketry and aeronautics.A composite shell shaped as a body of revolution comprises a plurality of multilayer elements forming its structure consisting of a set of crisscrossing strips. Said strips are made of a plurality of fibers formed as a "skin-core" structure and impregnated with a thermoplastic or resilient-elastic binder. The fibers formed as a "skin-core" structure are produced by impregnating the fiber filaments with a thermosetting binder and curing it. Multilayer air-tight shells and multilayer shells of a rib-cellular structure can be produced from said strips (FIG. 1, FIG. 10).

Abstract: A composite shell which can be used, in particular, in the manufacture of bodies or compartments of flying vehicles used in rocketry or aeronautics, comprises a load-bearing framework formed of intersecting stiffening ribs, and an outer load-bearing shell. Box-shaped cover plates are secured with glue an the cross nodes of the stiffening ribs from the internal surface of the framework, and thin-walled plates are secured at the outer surface of the shell by threaded rod elements that pass through the shell and framework and are connected to the box-shaped cover plates. In one embodiment, the composite shell is formed of a plurality of panels connected together at their abutting edges.

Abstract: A composite transverse wing rib shaped as a multi-layered flat panel comprises a cellular-ribbed structure of intersecting rectlinear ribs whose lengthwise directions are angled in opposite directions at oblique angles to a longitudinal dimension of the wing rib. The ribs have widthwise directions that extend between opposite side surfaces of the cellular-ribbed structure. The cellular-ribbed structure includes projections having flat faces arranged on an outer frame of the structure. The wing rib also includes other layers overlying opposite side surfaces of the cellular-ribbed structure and the projections. The outer layers comprise a net of intersecting small composite belts oriented along the oppositely angled directions of the rectilinear ribs and intersecting at the cross intersections of the rectlinear ribs. The cellular-ribbed structure and outer layers are formed of high-module yarns bound by a polymer binder.

Abstract: The inventions relate to the field of machine manufacturing and more specifically, to shell-type construction of base members used in aviation engineering and rocketry, which operate under conditions of combined stressed state, to the methods of and mandrels for their manufacture.A load-carrying tube-shell comprises a cellular framework 1 made of spiral and annular strips 4, 5 crossing each other to define layers 3 of systems repeated over the thickness of the wall thereof so that stiffening ribs 6, 7 with criss-crosses 8, 9, 10 are thus formed, and outer coating layers 2 respectively made of unidirectional filaments 11 bound by a cured polymeric binder 12. Damping-absorbing layers 14 of resilient-elastic material such as rubber or polyurethane are disposed between the layers 3.A method of the manufacture of the tube-shell comprises a step of introducing intermediate continuous forming strips 20 placed beneath the layers 4, 5 laid down under tension.