This study addresses the need for thermomechanically robust materials for high-temperature environments by investigating fabric-reinforced composites produced through polymer infiltration and thermal pressing using phenol-formaldehyde (PF) and epoxy (ER) resins. Experimental validation was required due to the lack of comparative data across different textile reinforcements under identical conditions. Seven technical fabrics—carbon, aramid, basalt, silica, fiberglass, asbestos, and a carbon/aramid hybrid—were used as reinforcements. Mechanical testing revealed that carbon- and hybrid fiber composites exhibited the highest tensile (up to 465 MPa) and compressive strengths (up to 301 MPa), particularly when combined with ER. Conversely, the use of PF generally resulted in a 30–50% reduction in mechanical strength. However, PF-based composites demonstrated superior thermal resistance, with the silica/PF combination showing the lowest back-face temperature (401 °C), up to 37% lower than other pairings. Thermal conductivity ranged from 0.041 to 0.51 W/m·K, with PF-based systems offering 6–12% lower values on average compared to ER-based analogs. Morphological analysis confirmed better interfacial bonding in ER composites, while PF systems showed higher structural integrity under thermal loading. Overall, the results emphasize the trade-offs between mechanical strength and thermal protection depending on the fabric–resin combination. Among all variants, the silica fabric with PF demonstrated the most balanced performance, making it a promising candidate for thermomechanical applications.

In this paper, a study of carbon fiber reinforced plastic tubes, which are widely used in overwhelming of technical industries, including aerospace industry, with single and combined winding angles (30°, 45°, 60° and 80°) fabricated by wet winding method on X-Winder machine has been carried out. The core problem addressed in this research is identifying optimal winding angles of carbon fiber reinforced plastic tubes at which the strength parameters remain in a relative equilibrium. Compressive strength, tensile strength and impact strength tests were carried out. The results of specimens with single winding angle showed that a maximum tensile strength of 630 MPa was achieved at a winding angle of ±30° and a maximum compressive strength of 380 MPa was achieved at an angle of ±80°. The maximum value of impact strength was achieved at a winding angle of ±60°. In order to obtain a balance in the strength characteristics of the tubular rods, combined reinforced winding with ±30°/45°, ±30°/60°, ±30°/80°, ±80°/45° and ±80°/60° angles were investigated. High values of compressive strength of 434 MPa, tensile strength of 675 MPa and impact strength of 165 kJ/m2 were achieved with ±30°/80° combined winding angle. The fibers of the material, which were oriented closer to the compression direction, resulted in reduced efficiency of transferring compressive forces between the fibers and decreased compressive strength. This uniform stress distribution permitted the load to be equally divided between the fibers, which effectively utilized their strength properties. Thus, results confirmed the importance of selecting the optimal winding angles to create carbon fiber reinforced plastic tubes with the required strength properties

This paper investigates a polymer composite and carbon fiber impregnated with epoxy resin for the fabrication of a lightweight and high-strength composite casing for rocket propulsion systems. It describes the winding technology which uses a removable mandrel and angular winding at ±55° and ±20° to expand the stress distribution, as well as alternating angles of ±45° and 80° to improve resistance to tensile and torsional loads. A fixture has been developed that ensures ease of disassembly and good strength of the final products. Hydrostatic tests showed the operational stability of the casings under internal pressure up to 10 MPa for a 1.5 mm-thick casing and 18 MPa for a 3 mm-thick casing, which confirms the effectiveness of the proposed technology. The research results demonstrate the high reliability and potential exploitation of composite materials.

This study presents a numerical investigation of the thermophysical and mechanical characteristics of a liquid rocket engine nozzle assembly with regenerative cooling. The simulations were performed using Ansys Discovery, Ansys Steady-State Thermal, and Ansys Mechanical software packages. Various combinations of structural materials (copper, aluminum, and steel) were analyzed, along with the influence of the convective heat transfer coefficient on the thermal state of the structure. It was found that increasing the coolant heat transfer coefficient up to 1.2 W/mm²·K significantly reduces the temperature of the inner layer, thereby ensuring acceptable operating conditions. Based on the results obtained, a nozzle design was developed featuring an inner layer made of a CuCrZr alloy and an outer shell made of 30KhGSA steel with a regenerative cooling system. The proposed design ensures stable operation at temperatures up to 3000 K and internal pressures up to 6 MPa with a safety factor of at least 1.5. The proposed approach provides a practical framework for the design and material selection of high-performance rocket engine nozzle assemblies.