## 1 Introduction  
Man-caused pollution of near-Earth space poses a threat to spacecraft, including the real risk of damage and destruction. The term \"space debris\" (SD) appeared in the late 1980s and, according to [PERSON]'s definition [1], describes all artificial objects and their parts in near-Earth space that do not serve any useful purpose or function. Since the launch of the first artificial Earth satellite, the number of launches has increased, resulting in the accumulation of both large fragments and small SD particles [2]. The collision of spacecraft construction elements with SD may lead to catastrophic consequences or local damage resulting in a loss of efficiency or function. In addition, natural meteoric particles from distant space pose a threat. The longer the spacecraft is in flight, the greater the probability of a collision with SD particles. To ensure effective protection against various external influences, the spacecraft's body must be technologically advanced in production and have the smallest possible mass. For low-orbit spacecraft, designing hulls and protective screens is particularly relevant due to the concentration of a large number of SD on low orbits. Several types of screens have been developed to protect against SD particles. [PERSON]'s protection [3] is an innovative approach that prevents impacts by incorporating a large space debris number of thin shells that destroy incoming kinetic energy particles. This creates a cloud of fragments that dissipate the kinetic energy of impact and distribute it over a larger area [4]. Multilayer heterogeneous screens are another type of protective construction that weakens the impact impulse through multiple reflections on multiple boundaries [5]. Other protective constructions, such as porous structures [6] and woven composites [7], have gaps in material properties that contribute to the dissipation of impact energy and prevent its spread. However, these protection technologies are often bulky, which presents a challenge in the design of aerospace systems where size and weight are severely limited. To sum up, the challenge of reducing the mass of spacecraft protective screens while maintaining their effectiveness remains a significant concern. Since the dawn of the space era, composites based on organic matrices and metal matrices (MMC) have been developed for use in space. These materials possess high specific stiffness and a virtually zero coefficient of thermal expansion (CTE). Organic matrix composites, such as graphite/epoxy resin, have been used in the space for truss elements, paneling, antennas, waveguides, and parabolic reflectors. On the other hand, MMCs are able to withstand high temperatures and possess high thermal conductivity, low CTE, high specific stiffness, and strength. These potential advantages generated optimism regarding the use of MMCs in critical space systems in the late 1980s [8]. The successful development of many modern branches of technology is primarily associated with the utilization of cutting-edge materials in construction, certain parts of which are subjected to extreme loads due to various reasons. Making an appropriate choice of a material capable of enduring the applied stress over a specific period of time can be quite laborious without conducting a theoretical prediction. The stress-strain and thermodynamic calculations of the loaded material, in the hands of an experienced researcher, serve as the key to enhancing reliability and prolonging the lifespan of the entire structure. The advancement and refinement of material creation technologies with predetermined properties, such as additive technologies, electron beam welding, and so on, have broadened the scope of heterogeneous materials' applications. Experimental work focused on practically developing manufacturing technologies for such heterogeneous mediums with specific properties far surpasses the methods used for predicting the properties themselves.