The article discusses the problems of designing and calculating the bodies of solid fuel rocket engines with a high degree of weight perfection and made of composite materials by automatic continuous winding. The history of the creation of such structures is briefly described and the problems of optimal reinforcement and optimization of structural forms of composite torqueless shells of revolution are considered. The results obtained in this direction by the science school of the academic V.V. Vasiliev.
The composite corps of a solid fuel rocket engine is an integral structure consisting of a cylindrical unit and bottoms formed by winding longitudinally reinforced composite tapes onto a rotating mandrel, which is removed after winding and curing of the polymer binder connecting the fibers of the composite material. This process was proposed in the 50s of the last century in the American laboratory R.E. Young Development and was implemented by the mid-60s for the manufacture of engine bodies of the strategic missile Polaris-A3.
In the USSR, at this time, the process of longitudinal-transverse winding was used, providing equal strength reinforcement of the cylindrical part of the body in axial and annular directions. Such bodies used in the Temp and Pioneer missiles did not receive further distribution due to problems encountered when connecting the composite cylindrical unit of the body to the bottoms. Continuous winding of cylindrical unit of bodies with bottoms was implemented in the mid-70s in relation to the Topol strategic missile and is now widely used in russian rocket science.