Abstract. With the rapid expansion of CubeSat small satellite constellations, the problem of anthropogenic contamination of near-Earth space is becoming increasingly relevant. Current international standards and space agency initiatives are tightening the requirements for the post-mission disposal timelines of end-of-life spacecraft. This necessitates developing structures that combine high operational performance with controlled disposal capabilities after the end of operational life. A computational and analytical justification for applying an aramid fiber-reinforced polymer composite in the load-bearing structure of a 12U CubeSat is presented. A three-layer wall configuration with a total thickness of 2.0–3.0 mm is proposed, comprising an outer layer modified with silica or alumina nanoparticles, a primary load-bearing layer with an epoxy matrix, and an inner trigger layer designed to initiate structural fragmentation upon mission completion. To assess structural durability, a mathematical model of atomic oxygen linear erosion has been developed, based on data from the SPENVIS orbital environment database, the MET-V 2.0 and IRI2001 atmospheric models, and post-flight data from the LDEF and MISSE missions. Structural analysis was performed using the Tsai-Wu failure criterion, which accounts for composite anisotropy and the combined effects of space environment factors, including thermal cycling, radiation exposure, moisture absorption, and manufacturing defects. A system of structural knockdown factors was introduced, with the total knockdown factor K_Σ taken as 0.62. Erosion calculations indicate that thickness recession over a five-year period amounts to 0.160 mm at an altitude of 500 km and 0.559 mm at 400 km. It was established that structural integrity is maintained with an initial wall thickness of at least 2.5 mm, while the factor of safety according to the Tsai-Wu criterion ranges from 1.24 to 1.48. The aramid-epoxy composite enables a 25–32 % reduction in structural mass, accounting for design constraints, compared to the V95 aluminum alloy. Economic assessment indicates that, despite the increased production cost of the composite bus, the cumulative economic benefit resulting from increased allowable payload mass and the reduced volume of active deorbiting systems amounts to 928,000–1,036,000 rubles. The results confirm the potential technical and economic feasibility of applying polymer matrix composites in CubeSat structures, provided that reliability requirements and international standards are met.

Keywords: small satellites, CubeSat, polymer matrix composites, aramid-epoxy composite, atomic oxygen, erosion, post-mission disposal, space debris

For citation: Rychkova A. D. Computational and analytical assessment of polymer composite material performance in CubeSat structures. Aerospace Engineering and Technology. 2026. Vol. 4, no. 2, pp. 279–295. (In Russ.) https://doi.org/10.52467/2949-401X-2026-4-2-279-295; https://elibrary.ru/kkpflp

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