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: A load-bearing tubular structural shell for use particularly in aerospace applications includes a structural frame of lattice-like structure formed by intersecting helical, girth, and longitudinal stiffening ribs, ad an outer covering surrounding the structural frame. The ribs are formed by helical, girth, and longitudinal strips of unbidirectional fibers wrapped in intersecting and overlapping fashion to form a plurality of layers of the strips. The longitudinal and girth ribs intersect at nodes, and at least some of these nodes are attached to helical ribs so as to form closed structural triangular nodes. Two sides of each triangular node are formed by first faces of the longitudinal and girth ribs, and the opposite second faces of the longitudinal and girth ribs intersect at a corner that lies within the closed triangular node. The helical rib at the triangular node has one face that lies within the closed triangular node and an opposite face that forms a third side of the triangular node.