Property changes in materials due to atomic oxygen in the low Earth orbit

Abstract

We expect satellites at altitude below 300 km, very low Earth orbit (VLEO), making observations of the Earth at optical wavelength with increasingly higher resolution. The density of atomic oxygen (AO) at VLEO is significantly higher than that at LEO; severe degradation of spacecraft materials (polymers) due to the high-flux AO is a serious concern. To clarify VLEO environmental effects on spacecraft materials, we designed the Material Degradation Monitor (MDM) and MDM2 missions. The MDM is a material exposure experiment onboard the Super Low-Altitude Test Satellite (SLATS). It aims to understand reactions and degradation of polymeric materials depending on AO fluence in VLEO. In the MDM, samples of spacecraft material were exposed at altitude of 160–560 km; their degradation behaviors were observed optically by a CCD camera for 1.8 years. The MDM2 is a material exposure experiment onboard the International Space Station (ISS) and aims to correctly understand surface reactions and degradation of the same samples used in the MDM at a given AO fluence. In the MDM2, the samples were exposed at altitude of 400 km for 1 year and then returned to Earth for analysis. Based on the results from both missions, we will help in the molecular design of more-durable materials, and establish design standards for future VLEO satellites. This study aims to quantitatively understand the surface reactions and degradation of the 11 types of thermal control materials exposed on the ISS in the MDM2. Five types of multilayer insulation (MLI) films (three types of Si-containing AO protective materials (a silsesquioxane-(SQ-) containing coated polyimide film, two types of polysiloxane-block polyimide (BSF-30) films), an ITO-coated polyimide film, and a Beta Cloth), and flexible optical solar reflectors (flexible OSRs) were found to have a high durability against erosion by AO. This was determined by measuring their loss of mass and thermo-optical properties. The Ag/Inconel layer’s discoloration and peeling were observed for three types of FEP/Ag films as determined by the Ag layer’s oxidation by AO. Also, X-ray photoelectron spectroscopy (XPS) showed that reactions of the Si-containing materials, the SQ-coated polyimide film and the BSF-30 film, form a layer of silica that protects against AO. Even though the concentration of Si in the SQ-coating is the same or greater than in the BSF-30 film, the amount of the SQ-coating that reacted was larger than that of the BSF-30 film under the same AO fluence. Moreover, the effective ability of the UV-shielding coating, composed of ITO and CeO2 coated onto one of the BSF-30 films, was demonstrated by UV–Vis spectrometry. Its sufficient AO protection was confirmed by mass measurements, XPS analyses, and FE-SEM observations.

Physical Characterization of Moon Impactor WE0913A

“…The composition of the thermal control material (TCM) used and its resistance to space aging may vary drastically between the Falcon 9 R/B and the Long March 3C R/B. Some white TCMs tend to yellow as they space age, while others are resistant to the changes and maintain a white appearance (Dever 1991;Bengtson et al 2018;Goto et al 2021). Although the exact paint is not known, it is plausible that the paint used on the Long March 3C R/B tends to yellow with exposure to the space environment, whereas the paint used on the Falcon 9 does not.…”

Atomic Oxygen in Low Earth Orbits, a Retrospective Review Study

“…Table 4 summarizes the development efforts of FAO testing facilities and Table 5 presents the main types of FAO sources in LEO space environment simulation facilities worldwide [30].…”

Carbon Nanocomposites in Aerospace Technology: A Way to Protect Low-Orbit Satellites

“…Research and development of space grade materials have a long history dating back to the beginning of space age. Presently available space materials were optimised to withstand the harsh conditions of the space environment, such as the effects of ultra-high vacuum, ionizing radiation, charge accumulation, UV radiation, thermal cycling and many other factors [15,16]. General application requirements also need to be fulfilled, such as weight reduction, mechanical stability, chemical reactivity, and cost reduction.…”