Space exploration is significant for scientific innovation, resource utilization, and planetary security. Space exploration involves several systems including satellites, space suits, communication systems, and robotics, which have to function under harsh space conditions such as extreme temperatures (- 270 to 1650 °C), microgravity (10⁻⁶ g), unhealthy humidity (< 20% RH or > 60% RH), high atmospheric pressure (~ 1450 psi), and radiation (4000-5000 mSv). Conventional energy-harvesting technologies (solar cells, fuel cells, and nuclear energy), that are normally used to power these space systems have certain limitations (e.g., sunlight dependence, weight, degradation, big size, high cost, low capacity, radioactivity, complexity, and low efficiency). The constraints in conventional energy resources have made it imperative to look for non-conventional yet efficient alternatives. A great potential for enhancing efficiency, sustainability, and mission duration in space exploration can be offered by integrating triboelectric nanogenerators (TENGs) with existing energy sources. Recently, the potential of TENG including energy harvesting (from vibrations/movements in satellites and spacecraft), self-powered sensing, and microgravity, for multiple applications in different space missions has been discussed. This review comprehensively covers the use of TENGs for various space applications, such as planetary exploration missions (Mars environment monitoring), manned space equipment, In-orbit robotic operations /collision monitoring, spacecraft's design and structural health monitoring, Aeronautical systems, and conventional energy harvesting (solar and nuclear). This review also discusses the use of self-powered TENG sensors for deep space object perception. At the same time, this review compares TENGs with conventional energy harvesting technologies for space systems. Lastly, this review talks about energy harvesting in satellites, TENG-based satellite communication systems, and future practical implementation challenges (with possible solutions).

Optical Solar Reflectors (OSRs) constitute the physical interface between radiator panels and outer space and allow for radiative cooling of the spacecraft. The performance of an OSR is defined mainly by two Thermo-Optical (T.O.) parameters: solar absorptance ? (the lower the better) and IR emittance ? (the higher the better). The market of OSRs is dominated by OSR quartz tiles, and by flexible Second Surface Mirrors (SSMs). Quartz OSRs exhibit excellent T.O. properties and durability, but are expensive and tend to break during assembly, integration and testing. Conversely, SSMs are easy to handle and apply, but age rapidly in space, due to the effects of UV radiation, charged particles and atomic oxygen on the polymeric support of SSM tape. First-Flex is a brand-new OSR technology that aims at combining the performance and durability of quartz OSRs with the flexibility and easy handling of SSMs, at fair costs. First-Flex consists of a fully inorganic coating sputter-deposited onto the first surface of polyimide film. The coating provides the required T.O. properties, while the film remains protected from the environment and serves only as mechanical support for the coating. First-Flex stems from a study for the Bepi Colombo mission, that led to the development and qualification of an extremely durable white coating named "Interferential CERMET" (IC), now flying around Mercury on the High Gain Antenna feed of the MPO. Subsequently, in the frame of the ESA ARTES AT and C&G pro

A stable and independent power supply is essential in extreme environments, where access to power infrastructure or opportunities for resupply are limited. Conventional batteries and fuel-powered generators are often heavy and require specialized maintenance. In contrast, solar cells can generate electricity directly from sunlight without reliance on external fuel sources. Among next-generation photovoltaic technologies, perovskite solar cells (PSCs) offer notable advantages, including tunable bandgaps and a high absorption coefficient, which enable spectral matching and stable operation even under low-irradiance conditions. Furthermore, PSCs are thin, lightweight, and mechanically flexible, allowing integration into mobile electronics and aerial systems such as drones and satellites. Despite these advantages, PSCs were previously considered unsuitable for deployment in harsh environments due to the intrinsic instability of perovskite absorbers, which are prone to degradation under external stressors such as heat, humidity, and continuous radiation. Recent progress in interface passivation, encapsulation, and the development of self-healing perovskite materials has significantly enhanced the long-term stability of PSCs, thereby enabling their potential application in extreme environmental conditions. In this review, we categorize the environmental threats relevant to space, underwater, desert, and polar regions, and analyze the specific stressors associated with each setting. We then examine recent technological advances that address these stressors and evaluate the practical feasibility of PSC operation under such conditions. The review concludes by identifying remaining challenges and offering perspectives on the future implementation of PSCs in extreme environments.

Perovskite solar cells (PSCs) have quickly achieved certified energy conversion efficiency reaching a certified record of 27.3% for single-junction cells, while having a low mass, thin-film form factor and high specific power, which are attractive for space energy systems. However, their long-term reliability in extraterrestrial environments is not adequately ensured by terrestrial qualification routes, and standardized space-related test protocols remain insufficiently developed. This review critically summarizes the current understanding of the degradation of PSCs under the influence of key environmental factors in space-ionizing and non-ionizing radiation, thermal vacuum exposure and thermal cycling, and ultraviolet radiation AM0, as well as atmospheric oxygen in low orbits. The central task of the work is to develop and justify the need to create specialized PSCs test protocols for space applications, since existing ground standards do not reflect the multifactorial nature and extreme orbital loads. It has been shown that thermal vacuum accelerates ion migration, interphase reactions, and degassing, while AM0 UV and atomic oxygen introduce additional photochemical and oxidative mechanisms of destruction; at the same time, stressors often act synergistically and are not detected by single-factor tests. Next, the limitations of the current IEC and ISOS are discussed and an approach to their expansion is formulated through the ISOS-T-Space and ISOS-LC-Space protocols, which integrate high vacuum, AM0 lighting, extended temperature ranges and controlled particle irradiation. It is concluded that the development and interlaboratory validation of such space-oriented protocols is a key condition for the correct qualification of PSCs and targeted optimization of materials and interfaces to meet the requirements of space energy.

Oxidation Study of an Ultra High Temperature Ceramic Coatings Based on HfSiCN High temperature fiber-reinforced ceramic matrix composites (CMCs) are important for aerospace applications because of their low density, high strength, and significantly higher-temperature capabilities compared to conventional metallic systems. The use of the SiCf/SiC and Cf/SiC CMCs allows the design of lighter-weight, more fuel efficient aircraft engines and also more advanced spacecraft airframe thermal protection systems. However, CMCs have to be protected with advanced environmental barrier coatings when they are incorporated into components for the harsh environments such as in aircraft engine or spacecraft applications. In this study, high temperature oxidation kinetics of an advanced HfSiCN coating on Cf/SiC CMC substrates were investigated at 1300 C, 1400 C, and 1500 C by using thermogravimetric analysis (TGA). The coating oxidation reaction parabolic rate constant and activation energy were estimated from the experimental results. The oxidation reaction studies showed that the coatings formed the most stable, predominant HfSiO4-HfO2 scales at 1400 C.

Oxidation Study of an Ultra High Temperature Ceramic Coatings Based on HfSiCN High temperature fiber-reinforced ceramic matrix composites (CMCs) are important for aerospace applications because of their low density, high strength, and significantly higher-temperature capabilities compared to conventional metallic systems. The use of the SiCf/SiC and Cf/SiC CMCs allows the design of lighter-weight, more fuel efficient aircraft engines and also more advanced spacecraft airframe thermal protection systems. However, CMCs have to be protected with advanced environmental barrier coatings when they are incorporated into components for the harsh environments such as in aircraft engine or spacecraft applications. In this study, high temperature oxidation kinetics of an advanced HfSiCN coating on Cf/SiC CMC substrates were investigated at 1300 C, 1400 C, and 1500 C by using thermogravimetric analysis (TGA). The coating oxidation reaction parabolic rate constant and activation energy were estimated from the experimental results. The oxidation reaction studies showed that the coatings formed the most stable, predominant HfSiO4-HfO2 scales at 1400 C.

Solar cells in superstrate arrangement need a protective cover glass as one of its main components. The effectiveness of these cells is determined by the cover glass's low weight, radiation resistance, optical clarity, and structural integrity. Damage to the cell covers brought on by exposure to UV irradiation and energetic radiation is thought to be the root cause of the ongoing issue of a reduction in the amount of electricity that can be generated by solar panels installed on spacecraft. Lead-free glasses made of xBi2O3-(40 - x)CaO-60P2O5 (x = 5, 10, 15, 20, 25, and 30 mol%) were created using the usual approach of melting at a high temperature. The amorphous nature of the glass samples was confirmed using X-ray diffraction. At energies of 81, 238, 356, 662, 911, 1173, 1332, and 2614 keV, the impact of various chemical compositions on gamma shielding in a phospho-bismuth glass structure was measured. The evaluation of gamma shielding revealed that the results of the mass attenuation coefficient of glasses increase as the Bi2O3 content increases but decrease as the photon energy increases. As a result of the study conducted on the radiation-deflecting properties of ternary glass, a lead-free low-melting phosphate glass that exhibited outstanding overall performance was developed, and the optimal composition of a glass sample was identified. The 60P2O5-30Bi2O3-10CaO glass combination is a viable option for use in radiation shielding that does not include lead.