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Analysis Results of Micro-Particles Captu ANALYSIS RESULTS OF THE MICRO-PARTICLES CAPTURER AND SPACE ENVIRONMENT EXPOSURE DEVICE (MPAC&SEED) EXPERIMENT ON THE INTERNATIONAL SPACE STATION SERVICE MODULE Yugo KIMOTO (1) *1, Junichiro ISHIZAWA(1), Eiji MIYAZAKI(1) , Hiroyuki SHIMAMURA(1) , Riyo YAMANAKA(1), (1) Space Materials Section, Electronic Devices and Materials Group, Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency (JAXA), 2-1-1 Sengen, Tsukuba, Ibaraki 305-8505, Japan. *1Phone: +81-29-868-2317, E-mail: [email protected] ABSTRACT Three identical SM/MPAC&SEED units MPAC&SEED is a JAXA-owned experiment for (SM/MPAC&SEED #1, #2, and #3) were attached to the particle capture and material exposure mounted on the SM and flown. The SM/MPAC&SEED was launched Russian Service Module (SM) and KIBO Exposed aboard a Progress M-45 on 21 August, 2001. Facility (EF) of the International Space Station (ISS). SM/MPAC&SEED was unpacked and assembled by This report particularly describes analysis results of the inner vehicle activity (IVA). At 09:17 UT on 15 October MPAC&SEED on the SM (hereinafter 2001, all three units were mounted on the handrail SM/MPAC&SEED). This was a first experiment that outside the SM by extra-vehicular activity (EVA). On 26 prepared three sets of the same samples and evaluated August 2002, the first unit of the SM/MPAC&SEED, the relation between the material deterioration and the SM/MPAC&SEED #1, was retrieved by EVA after 315 exposure period. The MPAC is a passive experiment days (ten months (0.9 years)) of on-orbit exposure. designed to sample micrometeoroids and space debris. Subsequently, SM/MPAC&SEED #2 was retrieved on 26 The SEED is a passive experiment designed to expose February 2004 (after 865 days (28 months (2.4 years))). materials. The MPAC experiment succeeded in capturing Later, SM/MPAC&SEED #3 was repositioned to the dust and the componential analysis was done. The impact location that had been occupied by MPAC&SEED #2. flux from captured dust and debris models were Finally, SM/MPAC&SEED #3 was retrieved on 18 compared. From the SEED experiment, space August 2005 (after 1403 days (46 months (3.8 years))) demonstration data were acquired and the materials [1]. proposed by JAXA, universities, and companies in Japan proved to have high space environment durability. This 2. EXPERIMENTS paper summarizes the results from the 2.1 MPAC[1] SM/MPAC&SEED experiment. The MPAC is a passive experiment designed to sample micrometeoroids and space debris. Three types of 1. INTRODUCTION samples were prepared to capture and measure The SM/MPAC&SEED experiment is the space micro-particles for the MPAC. Silica-aerogel (hereafter, exposure experiment on the exterior of the Russian aerogel) is a transparent and porous solid with nanosized Service Module of the ISS. The most unique aspect of holes. It is used to capture dust particles intact and to the SM/MPAC&SEED experiment is that three identical estimate impact parameters (incident direction, particle components were manufactured. All three were exposed diameter, and impact velocity) based on the impact track at the same time and each was individually retrieved morphology. Polyimide foam was prepared to capture after varying periods of time. It was the world's first such large debris. The densities of aerogel and polyimide trial and this method can compare material aging foam used are 0.03 g cm-3 and 0.011 g cm-3, respectively. deterioration at virtually the same position. Another An aluminum plate was used to measure the number of unique feature is that samples capture micrometeoroids impacts from space debris or micrometeoroids. and space debris. This MPAC is a passive experiment designed to sample the micrometeoroid and space 2.2 SEED[2] debris environment and to capture particle residue for The SEED is a space material exposure experiment. later chemical analysis using aerogel, polyimide foam, The SEED consists of 28 samples, outlined in Table 1. and 6061-T6 aluminum. Another point is that the same Samples were proposed by JAXA, universities, and samples were arranged on both ram and wake sides. This companies in Japan and were selected by JAXA based on method should demonstrate the effect of AO, which their frequency of use and prospective future use. The collides with and erodes materials on the front and back SEED experiment also includes space environment of the spacecraft [1]. monitoring samples which monitor the total dose of AO, UV, space radiation, and maximum temperature. possible impact residues, one just beyond the point after the track narrows, and one at the end. EDX analysis was Table 1. SEED samples conducted on both. The first one revealed Ag, Al and S, Sample name Organization Main Use and could be orbital debris. The second revealed only CF/Polycyanate, CF/Polyimide Fuji Heavy Industries Structural materials Ltd. background elements, and is thought to be altered PEEK (loaded & unloaded) Hokkaido University Inflatable structures aerogel. AlN Structural and Tokyo Institute of SiC (reaction sintering / Hot pressed) functional materials Technology TiN-coated Al / Al2O3 Ball-bearing (3 types) Tohoku University Mechanism application TiN/MoS2/CuBN/Cu/-coated National Institute for Lubrication SUS304 Materials Science MoS2 bonded film on Ti alloy IHI Aerospace Lubrication Loaded & unloaded polyimide film Inflatable structures (UPILEX-S) Modified polyimide film Thermal control Japan Aerospace Flexible OSR Exploration Agency White paint Silicone potting compound Potting Silicone adhesive Adhesion 3. RESULTS AND DISCUSSION 3.1 MPAC SM/MPAC results have been analyzed by some authors. Neish et al. described the inspection and analysis of the MPACs retrieved first and second (hereafter MPAC#1, #2) [2]. They showed the number of expected hits and the impacts on the aerogels, polyimide Figure 2. A typical carrot-shaped MPAC#2 impact. film, and aluminum plate on the MPAC#1 and #2. For The first fragment revealed Ag, Al and S, the second example, the largest feature found in MPAC#1 aerogel is background elements only [2]. shown in Fig. 1 together with the result of the EDX analysis performed on the inner wall of the impact track, Kitazawa et al. reported a detailed post-flight as highlighted by the white oval. Aluminum was analysis (PFA). They showed the numbers of identified, which Raman spectroscopy subsequently impact-induced features of the first quality level (Class I), indicated was in the pure form (as opposed to an oxide). which is a category that meets all of three criteria (<1> This suggests a debris impact. the feature has a crater-like rim and/or central peak, <2> the feature has radial cracks and/or ejecta, <3> the feature has a shape similar to those induced by hypervelocity impact experiments). Class II (the second quality level) has probable hypervelocity impact-induced features which meet one or two of the criteria. Class III has no hypervelocity impact-induced features. The number of impact-induced features was almost directly related to the exposure period (Fig. 3). The impact rate was almost constant with the sum of Class I and Class Ⅱ events running at about 15 impacts per year [3]. They also compared the calculated impact fluxes of the three environment models with the impact fluxes on aerogels estimated from inspection. They concluded that it is difficult to inspect small tracks and it was not possible to estimate the fluxes of diameter >10 μm of the aerogels retrieved second and third. Impact fluxes of aerogel appear inversely proportional to the exposure period and the fluxes are greater than the model results Figure 1. MPAC #1 impact (the largest found in [4]. MPAC#1 aerogel; entry hole diameter: ~2 mm, track length: ~5 mm). The inner wall was subjected to EDX analysis, revealing Al. Si and O are constituents of aerogel, and C was used as a coating [2]. An MPAC #2 impact is shown in Fig. 2. This large, typical carrot-shaped track (Fig. 7), over 1 mm long and almost perpendicular to the surface, revealed two cause of the crack formation on the silica aerogel surface; moreover, ultraviolet rays cause browning of the silica aerogel surface [7]. Fig. 3 Number of impact features of the first quality level (Class I) on SM/MPAC&SEED versus exposure [3]. Particle Diameter > 10μm Particle Diameter > 20μm 2.E+03 7.E+02 MPAC MPAC 2.E+03 ORDEM2000 6.E+02 ORDEM2000 /year] MASTER2001 2 MASTER2001 /year] 2 1.E+03 MASTER2005 MASTER2005 5.E+02 1.E+03 4.E+02 1.E+03 MPAC 8.E+02 MPAC (NO DATA ) (NO DATA ) 3.E+02 6.E+02 Cumulative Impact Flux [number/m Flux Impact Cumulative 2.E+02 Cumulative Impact Flux [number/m Flux Impact Cumulative 4.E+02 1.E+02 2.E+02 0.E+00 0.E+00 SM1 SM2 SM3 SM1 SM2 SM3 （315 days’ exposure） （865 days’ exposure）（1403 days’ exposure） （315 days’ exposure） （865 days’ exposure）（1403 days’ exposure） Fig. 4 Comparison of impact flux of MPAC aerogels and Fig. 5 Photomicrographs of tracks investigated in the calculated results of three models (Left: Particle diameter study. Terminal particles are indicated by black arrows. >10 µm, Right: Particle diameter >20 µm ) [4]. (A) SM1_3RA1, (B) SM2_4WD1, (C) SM3_3WD1, (D) an enlarged image of the terminal particle in the track Noguchi et al. discovered that the number density of shown in (C) [5]. craters on the surfaces of the WAKE facing tiles is smaller than those of the RAM facing aerogels. However, their depth/crater diameter ratios are larger than those facing towards the RAM side. We investigated three terminal particles found at the ends of tracks in silica aerogels. Combined SEM, transmission electron microscope (TEM), micro Raman spectroscopy, and synchrotron radiation X-ray diffraction analyses revealed that they are space debris, secondary debris and a micrometeoroid, respectively.
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