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.

Abstract: The invention relates to machine-building. More specifically, it pertains to shell fabrication of airframe parts, which are used in aerospace equipment operating under compound stress. The invention also covers methods and apparatus for the fabrication of the shell structures.The invention aims to improve wall rigidity and strength.A tubular pressure vessel in the form of a composite cylindrical body incorporates a lattice-type frame 1 and external protective cover 2; the grid frame is made by winding a layered system 3 of helical 4, longitudinal 5, girth 6, and oblique transition strips 14 linking the girth strips 6; the pattern forms interleaved stiffening ribs 8, 9, 10, 15. The winding is applied to the mandrel, the core 17 is covered with thermostabilized flexible plates 19 with a web of grooves 23, 24, 25, 26 for imbedding a matching pattern of strips 6,4,5, and 14.