Annotation: The exploratory and experimental investigations were conducted into design of propellant tank made of composite polymer materials for work in cryogenic environment at operating pressure of 7.5 kgf/cm2 . When determining the configuration of a liner-free composite propellant tank, the main requirement was ensuring its leak-tightness at internal excess pressure and cryogenic temperature effect. The world experience of creating similar designs was analyzed and the requirements were defined imposed on configuration of propellant tank load-bearing shells. Before defining the final configuration, the types of materials, reinforcing patterns, and possible ways to ensure leak-tightness were analyzed, and preliminary tests were conducted of physical and mechanical characteristics of thin-wall samples of composite materials and tubular structures with different reinforcing patterns. The tests of carbon plastic samples were conducted at different curing modes to determine the most effective one from the viewpoint of strength characteristics and the tests for permeability by method of mouthpiece were conducted. The tests of pilot propellant tank showed that the calculated values of deformations and displacements differ from the experimental values by no more than 10 %. Using the parameters measurement results from the tests on liquid nitrogen, the empirical formulas were obtained to calculate linear thermal expansion coefficient of the package of materials of load -bearing shell. The empirical dependences were constructed of relative ring deformations at load-bearing shell middle section on pressure and temperature. The tests confirmed correctness of adopted solutions to ensure strength and leak-tightness of propellant tank load-bearing shell at combined effect on internal excess pressure and cryogenic temperature, particularly at cyclic loading. The materials used and propellant tank manufacturing technologies ensure leak-tightness of load-bearing shell at liquid nitrogen operating pressure of 7.5 kgf/cm2 and strength at excess pressure of 15 kgf/cm2 and allow conducting approbation of prospective stage of the integrated launch vehicle.

Annotation: The tubes of rectangular section made of composite material find ever- growing use. Winding of tubes without using dowels for small winding angles has a number of disadvantages. The technology of winding through dowels does not have these disadvantages. The paper presents the authors-developed calculation technique for programs of winding the tubes of rectangular section made of composite materials using dowels. To ensure winding continuity, the dowels at base must have equal distances between them. The external diameter of comb is selected with margin taking into account band stranding on the dowels. The scheme of winding on entire layer is determined that represents a table which indicates band position between the dowels of front and rear comb during winding a layer for each coil. Then the coordinates of machine tool are determined. For this purpose, we determine the angles of coil winding, corresponding angles of mandrel turn in determined coordinates X, the coordinates of band escape point, angle of inclination of free section of band, then from geometrical considerations we obtain the components of unit vector of tangent to reinforcing trajectory and directly the coordinated of machine tool actuators. As a result, we obtain the table of coordinates of machine toll actuators during winding of the first coil (at forward and back travel). Using the presented logics, similarly it is easy to obtain for all coils the coordinates of machine tool actuators. According to this technique, the Vitok auto-programming system was developed in MathCad environment. The Vitok system was used during development of winding program for tube 28x28x2 mm under Sich-2M program. The programs operated successfully. The test samples of tubes were wound. The authors performed winding of the tubes of rectangular section made of composite material to obtain a structure with zero linear thermal expansion coefficient.