We present a concept of optimization of structural and technological parameters of rocket and space technology units from polymer composite materials under heterogeneous loading and a project complex for their rational selection, taking into account the current level of production. The concept includes five interconnected components: design, production technologies, operation, ecology, and safety of industrial life. The analysis of possible criteria-based optimization estimates is carried out on the example of the technological component of the problem. Decompositions of the general task of parameters’ optimization were carried out into a number of types that correspond to the main types of structures of the considered class of technology: load-bearing compartments of launch vehicles and precision structures of spacecraft. An integrated approach to the optimal design of the bearing compartments of the head block of launch vehicles of various structural and power schemes is proposed. A distinctive feature of the approach is the possibility of multifactor optimization of the parameters for units of the class under consideration while providing regulated load-bearing capacity with simultaneous power and heat loading, taking into account technological, operational, economic, and environmental restrictions that correspond to the existing level of their production. A conceptual approach to the synthesis of rational parameters of composite frames of solar panels of various structural and power circuits is proposed, based on the integrated realization of well-known principles implemented by relevant units that are integrated by computer technology into a single optimization complex. An integrated approach has been synthesized to create precision space structures from polymer composite materials, which makes it possible to obtain rational thermo-dimensionally stable composite structures. An algorithm for determining the rational structure of a composite package has been developed and implemented, which provides a compromise combination for the absolute values of the coefficient of linear thermal expansion keeping maximum precision of the product in accordance with the proposed criteria. The results obtained made it possible to provide an increase by more than 20% in the mass efficiency of the composite aggregates of rocket and space technology produced at the leading enterprises of the industry.
Optimization of Technological Parameters of Impregnation of Load-Bearing Rod Elements of Reflector made of Polymer Composite Materials by Transfer Molding Method
