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Artigos de revistas sobre o tema "Orbit, 1757"

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Autor: Grafiati

Publicado: 26 de julho de 2024

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1

Majeed, R. N., e S. A. El-Sheikh. "Fuzzy orbit topological spaces". IOP Conference Series: Materials Science and Engineering 571 (8 de agosto de 2019): 012026. http://dx.doi.org/10.1088/1757-899x/571/1/012026.

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2

Koryanov, Vsevolod V., e Budang Zhang. "Research on Coplanar Orbit Maneuvering in the Context of on-Orbit Service". IOP Conference Series: Materials Science and Engineering 630 (24 de outubro de 2019): 012001. http://dx.doi.org/10.1088/1757-899x/630/1/012001.

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3

Samoylov, A. G., S. A. Samoylov, S. A. Nasir e I. A. Al Tahar. "Radio links from low-orbit satellites". IOP Conference Series: Materials Science and Engineering 862 (28 de maio de 2020): 022030. http://dx.doi.org/10.1088/1757-899x/862/2/022030.

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4

Alshamy, Hossam M. I., Ah El-S. Makled, Y. Elhalwagy e Hossam Hendy. "Flight dynamic model for low earth orbit satellites". IOP Conference Series: Materials Science and Engineering 610 (11 de outubro de 2019): 012100. http://dx.doi.org/10.1088/1757-899x/610/1/012100.

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5

Relangi, Naresh, Lakshmi Narayana Phaneendra Peri, Caio Henrique Franco Levi Domingos, Amalia Fossella, Julia Meria Leite Henriques e Antonella Ingenito. "Design of Supersonic and Hybrid engine based Advanced Rocket (SHAR)". IOP Conference Series: Materials Science and Engineering 1226, n.º 1 (1 de fevereiro de 2022): 012031. http://dx.doi.org/10.1088/1757-899x/1226/1/012031.

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Abstract The paper deals with the design of a two-stage to orbit rocket launcher loaded with a solid rocket booster, scramjet, and hybrid rocket for delivering a 100kg payload in 200 km circular orbit. The possibility of implementing a cavity-based axisymmetric circular combustor in a scramjet is proposed. Computational analysis on various injector locations in a circular combustor and their validation with the test bench results were performed. The utilisation of a hybrid rocket in the final stage of the launcher to deliver the payload is discussed and the performance characteristics of the circular scramjet combustor and the hybrid rocket are shown. The overall mission proposed based on the sustainable and reusable characteristics.

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6

Jena, Soumyasree, e Sanjoy Datta. "Role of spin-orbit coupling in semimetallic bulk Bismuth". IOP Conference Series: Materials Science and Engineering 577 (7 de dezembro de 2019): 012072. http://dx.doi.org/10.1088/1757-899x/577/1/012072.

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7

Li, H., M. Y. Zhou, S. Y. Wu e X. R. Liang. "Research of spin-orbit interaction in organic conjugated polymers". IOP Conference Series: Materials Science and Engineering 213 (junho de 2017): 012005. http://dx.doi.org/10.1088/1757-899x/213/1/012005.

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8

Cha, J., B. Carroll, J. Rodriguez, K. Maynard e M. Romero. "Thermal design and on-orbit performance of the ECOSTRESS instrument". IOP Conference Series: Materials Science and Engineering 755 (30 de junho de 2020): 012005. http://dx.doi.org/10.1088/1757-899x/755/1/012005.

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9

Zhu, Lingchao, e Shuquan Wang. "Orbit-Attitude Coupled Tracking and Landing Control for an Asteroid". IOP Conference Series: Materials Science and Engineering 685 (22 de novembro de 2019): 012003. http://dx.doi.org/10.1088/1757-899x/685/1/012003.

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10

Zhang, Bin, Dongmei Wang, Yufeng Fan, Li Liu e Peirong Zhao. "In-orbit Failure Analysis and Verification for Thermistors outside Satellites". IOP Conference Series: Materials Science and Engineering 608 (27 de agosto de 2019): 012036. http://dx.doi.org/10.1088/1757-899x/608/1/012036.

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11

Yu, Shao-ting, e Cai-zhi Fan. "Aerodynamic Analysis and Drag-reduction Design for Ultra-low-orbit Satellite". IOP Conference Series: Materials Science and Engineering 887 (10 de julho de 2020): 012013. http://dx.doi.org/10.1088/1757-899x/887/1/012013.

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12

Reznik, S. V., D. V. Reut e M. S. Shustilova. "Comparison of geostationary and low-orbit “round dance” satellite communication systems". IOP Conference Series: Materials Science and Engineering 971 (1 de dezembro de 2020): 052045. http://dx.doi.org/10.1088/1757-899x/971/5/052045.

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13

Moore, B., D. Bolton, K. Penanen e S. Susca. "SPHEREx payload thermal architecture and analysis". IOP Conference Series: Materials Science and Engineering 1301, n.º 1 (1 de maio de 2024): 012014. http://dx.doi.org/10.1088/1757-899x/1301/1/012014.

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Abstract The SPHEREx (Spectro-Photometer for the History of the Universe, Epoch of Reionization, and Ices Explorer) is an all-sky spectral survey in a Sun-synchronous low earth orbit. It measures spectrum in the near infrared band from 0.75 µm to 5 µm. To achieve this wavelength coverage, the instrument has two focal plane arrays, both passively cooled at <55 K (mid-wave infrared) and <80 K (short-wave infrared). Additionally, the instrument requires no moving parts for spectral resolution, relying instead on spacecraft-controlled pointing. A thermally isolating structure and a set of V-groove radiators reduce the heat flow conducted and radiated from the spacecraft bus. The thermal system also blocks the incident solar flux and earth radiation from reaching the sensitive cryogenic instrument while still allowing substantial pointing flexibility. The combination of passive cryogenic cooling and survey requirements in a sun exposed low earth orbit environment presents a challenge for the thermal design. This paper will discuss the SPHEREx payload overall thermal architecture, bounding thermal environments, the component thermal design, and analysis of on-flight performance.

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14

Lv, Xinqi, Jingyan Wang e Nan Du. "Extraction and utilization of satellite products life and reliability data on orbit". IOP Conference Series: Materials Science and Engineering 1043, n.º 4 (1 de janeiro de 2021): 042030. http://dx.doi.org/10.1088/1757-899x/1043/4/042030.

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15

Gnanavel, C., R. Saravanan, M. Chandrasekaran e J. J. Jayakanth. "Improvement of Productivity in TIG Welding Plant by Equipment Design in Orbit". IOP Conference Series: Materials Science and Engineering 183 (março de 2017): 012020. http://dx.doi.org/10.1088/1757-899x/183/1/012020.

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16

Koryanov, V. V., A. G. Toporkov, V. P. Kazakovtsev, A. A. Nedogarok e E. K. Gnezdova. "The use of inflatable structures for the removal of spacecraft from orbit". IOP Conference Series: Materials Science and Engineering 683 (13 de dezembro de 2019): 012069. http://dx.doi.org/10.1088/1757-899x/683/1/012069.

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17

Wang, Chao, Jianwei Wang, Dong Fang, Donglin Li, Ying Zhang e Dalin Kong. "On Orbit Capture and Control of Space Manipulator Based on Magneto Rheological". IOP Conference Series: Materials Science and Engineering 685 (22 de novembro de 2019): 012001. http://dx.doi.org/10.1088/1757-899x/685/1/012001.

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18

Pascu, Sergiu, Nicolae Balc e Adrian Augustin Pop. "Reconstruction of Orbital Wall by Using Hybrid Manufacturing Operations". IOP Conference Series: Materials Science and Engineering 1268, n.º 1 (1 de novembro de 2022): 012014. http://dx.doi.org/10.1088/1757-899x/1268/1/012014.

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This paper will discuss the solutions and the main parameters used to print a mold that will be used in a manufacturing process for a personalized implant in orbital fracture situations. The main purpose of this article is to rebuild the damaged orbit. The new orbit should have dimensions and accuracy similar to one of the original elements. Based on the computed tomography (CT) of the patient, the images are extracted and processed. With that information, a customized implant is manufactured. In this article, a case study of a patient suffering from an orbital fracture is presented. Based on the CT images, a mold was printed on additive manufacturing equipment (AM). The manufacturing parameters being highly correlated with the requirements that are needed for this case such as hardness, accuracy, surface roughness and support removal were chosen based on a series of tests and results from other studies. Another aspect that was analysed was related to the material from which was manufactured the mold. The forming and cutting of the mesh are simplified, by introducing the formed metallic mesh making it ready to be applied to real patients and therefore decreasing the effective time required for this kind of operation.

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19

Zinecker, A., B. Spivey, G. Jayne e M. Hasegawa. "Solar Absorptivity Degradation of Spacecraft Materials Due to UV and Charged Particles in the Gateway Environment". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012009. http://dx.doi.org/10.1088/1757-899x/1287/1/012009.

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Abstract Gateway will be an outpost in cislunar space designed to survive a 15-year mission to support human Moon landings and future deep space exploration. The Gateway Passive Thermal Control System (PTCS) Group has identified charged particle and UV degradation of potential Gateway materials as a knowledge gap for the Near Rectilinear Halo Orbit (NRHO) and transit environment, especially the slow spiral transit planned for the first two modules. Solar absorptivity degradation is important to quantify because the end-of-life absorptivity impacts thermal performance of the system. To address this, ground testing has been completed at NASA Goddard Space Flight Center in which potential Gateway materials, including radiators, multi-layer insulation (MLI), and structural materials are subjected to the expected transit plus 15-year on-orbit charged particle fluence (9.86x1015 protons/cm2 at 2.5 keV and 3.1x1016 electrons/cm2 at 10 keV) and 5093 Equivalent Solar Hours (ESH). Reflectivity of a single sample of each material was measured in atmosphere and in vacuum inside the chamber after exposure to incremental levels of ESH and charged particle fluence. Increase in absorptivity of most samples were seen throughout the test including large differences in absorptivity of materials of the same category. Future planned testing will validate these results and include additional materials of interest.

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20

Yin, Wenjuan, Tao Song e Zhen Lin. "On-orbit Engine Thrust Prediction Algorithm for Geosynchronous Satellites based on Neural Network". IOP Conference Series: Materials Science and Engineering 887 (10 de julho de 2020): 012040. http://dx.doi.org/10.1088/1757-899x/887/1/012040.

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21

Li, Wen, Lei Guo, Jintao Liu, Yong Li e Lei Chen. "The Numerical Analysis to Gas-Liquid Separator used in On-orbit Refuelling Mission". IOP Conference Series: Materials Science and Engineering 793 (10 de abril de 2020): 012037. http://dx.doi.org/10.1088/1757-899x/793/1/012037.

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22

Liu, M. H., H. Cao e H. Y. Gao. "Simulation design method of free boundary simulator for high precision spacecraft on orbit". IOP Conference Series: Materials Science and Engineering 657 (25 de outubro de 2019): 012068. http://dx.doi.org/10.1088/1757-899x/657/1/012068.

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23

Wah, Leo Kwee, Ken Takayama, Toshikazu Adachi, Tadamichi Kawakubo e Tanuja Dixit. "Study the closed orbit correction of a compact hadron driver for cancer therapy". IOP Conference Series: Materials Science and Engineering 1285, n.º 1 (1 de julho de 2023): 012004. http://dx.doi.org/10.1088/1757-899x/1285/1/012004.

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Abstract A design of a compact hadron driver for future cancer therapies based on the induction synchrotron concept is given. In order to realize a slow extraction technique in a fast cycling synchrotron, which allows the energy sweep beam scanning, the zero momentum-dispersion D(s) region and high flat D(s) region are necessary. The present design meets both requirements. The lattice has the two-fold symmetry with a circumference of 52.8 m, 2 m-long dispersion-free straight section, and 3 m-long large flat dispersion straight section. Assuming a 1.5 T bending magnet, the ring can deliver heavy ions of 200 MeV/au at 10 Hz. Details of the lattice parameters and orbit correction approach and method are discussed.

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24

Matsuura, Yoshiki, Kumi Nitta, Hirohide Ikeda, Masahiro Kinoshita e Kyohichi Ui. "Evaluation of the Material Properties of Solid Rocket Motor Slag". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012005. http://dx.doi.org/10.1088/1757-899x/1287/1/012005.

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Abstract A considerable amount of aluminum oxide particles are generally produced during the Solid Rocket Motor (SRM) combustion. A project determining the damage caused by slag impact on spacecrafts in orbit is drafted to acquire physical property data of SRM slag by JAXA. After the grand firing test of small SRMs, all slag was collected and analyzed. This study describes the investigation results regarding the characteristics of SRM slag and the current possible scenario of the slag particle formation process.

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25

Mooney, C., N. Dias, Y. Butenko, O. Schmeitzky e G. van Papendrecht. "Materials inspection of the ISS Columbus Trunnion scuff plate MLI". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012031. http://dx.doi.org/10.1088/1757-899x/1287/1/012031.

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Abstract As part of the preparation for the Bartolomeo platform, various locations of the trunnion scuff plate were required. Scuff plate MLI blankets were removed and recovered from Columbus ISS in August 2019 as part of these EVA activities. These blankets having seen more than 11 years in orbit are extremely valuable from a materials-science perspective where direct analysis of the impact of the space environment can be seen and evaluated to see its effect on materials, contamination and functionality of the blankets.

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26

McKinley, I. M., J. I. Rodriguez, G. D. Allen, J. Keller, M. A. Mok e L. Chan. "Thermal Design of the High-Resolution Volatiles and Minerals Moon Mapper (HVM³) Instrument on the Lunar Trailblazer Mission (LTB)". IOP Conference Series: Materials Science and Engineering 1301, n.º 1 (1 de maio de 2024): 012012. http://dx.doi.org/10.1088/1757-899x/1301/1/012012.

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Abstract The Lunar Trailblazer (LTB) Mission consists of a spacecraft that hosts two science instruments, the High-resolution Volatiles and Minerals Moon Mapper (HVM3) and the Lunar Thermal Mapper. Flight system delivery is scheduled for the Fall of 2022. The purpose of the mission is to understand the form, abundance and distribution of water on the Moon as well as the lunar water cycle. HVM3 is a pushbroom shortwave infrared (SWIR) Offner imaging spectrometer that is optimized for the detection of volatiles to map OH, bound H2O and water ice. It has a spatial resolution of 70 m/pixel over a 20 km swath width and a spectral resolution of 10 nm over a spectral range of 0.6 µm to 3.6 µm. The spacecraft will deploy from an ESPA Grande and enter a 100±30 km lunar polar orbit where it may operate over all beta angles. The HVM3 thermal control architecture consists of active and passive elements. It leverages the passive cryogenic cooler design developed for the Moon Minerology Mapper (M3) that underwent a similar orbit. The first stage of the passive cooler is used to reject the heat of a Lockheed Martin Micro1-2 cryocooler that is used to actively cool the focal plane array (FPA). The second stage of the passive cooler is used to passively cool the optics. An overview of the overall thermal control design approach is presented.

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27

Lv, Zhen, Hua Zhang, Zhi-Ming Zhao e Kai-Xiang Gong. "Application on the impact domain analysis of on-orbit maintenance in China Space Station". IOP Conference Series: Materials Science and Engineering 1043, n.º 3 (1 de janeiro de 2021): 032067. http://dx.doi.org/10.1088/1757-899x/1043/3/032067.

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28

D'yachkov, P., e D. Kutlubaev. "Spin-Orbit Gaps in Armchair Nanotubes Calculated Using the Linear Augmented Cylindrical Wave Method". IOP Conference Series: Materials Science and Engineering 38 (20 de agosto de 2012): 012003. http://dx.doi.org/10.1088/1757-899x/38/1/012003.

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29

Gorev, V. N., V. Yu Prokopiev, Yu M. Prokopiev, L. D. Sinitsina e A. A. Sidorchuk. "Calculating electric power generated by 3U CubeSat’s photoconverters depending the orbit and orientation parameters". IOP Conference Series: Materials Science and Engineering 537 (17 de junho de 2019): 022079. http://dx.doi.org/10.1088/1757-899x/537/2/022079.

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30

Ji, Jialong, Yong Gao, Ali Zhang e Qian Lin. "A Method for Calibrating Thrust of Satellite Based on the Attitude Variety On-orbit". IOP Conference Series: Materials Science and Engineering 727 (7 de janeiro de 2020): 012015. http://dx.doi.org/10.1088/1757-899x/727/1/012015.

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31

Krasil’nikov, P. S. "On the exoplanet obliquity variations in planetary four – body problem with evolving satellite’s orbit". IOP Conference Series: Materials Science and Engineering 927 (26 de setembro de 2020): 012031. http://dx.doi.org/10.1088/1757-899x/927/1/012031.

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32

Sapietová, A., V. Dekýš, M. Sapieta, A. Jastraban e M. Pástor. "Modelling and Analysis of a Virtual Prototype of a Rotary Machine in MSC.ADAMS". IOP Conference Series: Materials Science and Engineering 1199, n.º 1 (1 de novembro de 2021): 012014. http://dx.doi.org/10.1088/1757-899x/1199/1/012014.

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Abstract The article presents an analysis of the virtual model of Laval (Jeffcott) rotor in the software environment MSC.ADAMS. The parameters describing the stability of the rotor operation were monitored and evaluated, i. j. critical angular velocity and trajectory of the rotor center of gravity (orbit). The results were compared with the values measured on the experimental equipment, as well as with the values obtained by analytical calculation. The paper further presents a simulation in which the second critical velocity was reached. The paper further presents a simulation in which the second critical velocity was reached.

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33

Kumar, S., S. H. Upadhyay e V. V. Koryanov. "A wrinkling analysis and control of rectangular membrane structures with upscale modelling under on-orbit conditions". IOP Conference Series: Materials Science and Engineering 812 (14 de maio de 2020): 012014. http://dx.doi.org/10.1088/1757-899x/812/1/012014.

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34

Zhang, Y., P. Sun, Z. W. Liang e W. P. Dong. "The estimation method of time of on-orbit spacecraft cabin decompression based on effective circulation area". IOP Conference Series: Materials Science and Engineering 657 (25 de outubro de 2019): 012042. http://dx.doi.org/10.1088/1757-899x/657/1/012042.

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35

Sun, W., R. X. Yan, L. C. Sun e R. P. Shao. "Development of the Noise-Resistant and Sound Focusing Accessory of Ultrasonic Leak Detector for Spacecraft on Orbit". IOP Conference Series: Materials Science and Engineering 281 (dezembro de 2017): 012063. http://dx.doi.org/10.1088/1757-899x/281/1/012063.

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36

Buntrock, L. J., M. Grabe e H. Fischer. "Contamination assessment of a freely expanding green propellant thruster plume". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012004. http://dx.doi.org/10.1088/1757-899x/1287/1/012004.

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Abstract A number of propellant/thruster combinations are under development in recent years that aim to replace the prevailing hydrazine-driven reaction control thrusters with less hazardous substances (“green propellants”). With some of these systems already in orbit, characterizing their contamination potential in a space environment becomes relevant. In this paper we discuss experiments on plume induced contamination from a novel propene/nitrous oxide bipropellant thruster, including high-speed imaging, SEM-EDS analysis, QCM measurements and in-situ mass spectrometry. Additional measurements of combustion chamber pressure complement the overall characterization of the thruster performance in a high vacuum environment. The main findings of this exploratory study are strong indications of solid and liquid phase particles being ejected from the nozzle, which will be investigated in a subsequent phase of the activity.

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Portaluppi, Mauricio, Sandra Fontorbes, Antonio Saverino e Riccardo Rampini. "Euclid cleanliness and contamination control". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012018. http://dx.doi.org/10.1088/1757-899x/1287/1/012018.

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Abstract Euclid is a space-based optical/near-infrared survey mission of the European Space Agency (ESA) to investigate the nature of dark energy, dark matter and gravity by observing the geometry of the Universe and the formation of structures over cosmological timescales. It will operate at L2 and it will survey about 36% of the sky on a 6 year mission, all with high image quality and stability. To allow such scientific achievements, an integrated cleanliness and contamination control (CCC) have been put in place covering all phases of Euclid development until end of operations. This document describes the design challenges, the engineering and AIT solutions used to control and to monitor the entire mission life time contamination from organic and particulate sources as well as the in-orbit water ice contamination.

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Bardin, B. S., e A. A. Antipov. "On resonant periodic motions close to conical precession of a dynamically symmetric satellite in a weakly elliptic orbit". IOP Conference Series: Materials Science and Engineering 927 (26 de setembro de 2020): 012016. http://dx.doi.org/10.1088/1757-899x/927/1/012016.

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Stepanova, E. A., O. I. Lebedev, G. M. Kozachenko, M. V. Povchinets, A. A. Atamanenko e A. P. Kobzeva. "Difficulties of diagnosing parasitic diseases of the orbit in patients living in non-endemic areas". Practical medicine 16, n.º 4 (2018): 182–84. http://dx.doi.org/10.32000/2072-1757-2018-16-4-182-184.

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Kumar, S., S. H. Upadhyay e V. V. Koryanov. "Research and modeling of wrinkles and control of rectangular membrane structures with high-class modeling in on-orbit conditions". IOP Conference Series: Materials Science and Engineering 812 (14 de maio de 2020): 012011. http://dx.doi.org/10.1088/1757-899x/812/1/012011.

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41

Popov, N. V., E. A. Radzhabov e A. S. Mysovsky. "First-principles study of electronic structure of Ce3+centres in alkaline-earth fluorides including spin-orbit and scalar relativistic effects". IOP Conference Series: Materials Science and Engineering 80 (20 de abril de 2015): 012025. http://dx.doi.org/10.1088/1757-899x/80/1/012025.

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42

Li, H., S. Y. Wu, X. R. Liang e M. Y. Zhou. "The effect of spin-orbit interaction on the electron spin transport in inorganic semiconductors and the comparison of organic semiconductors". IOP Conference Series: Materials Science and Engineering 137 (julho de 2016): 012005. http://dx.doi.org/10.1088/1757-899x/137/1/012005.

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43

Krylov, S. S., V. V. Perepelkin e A. S. Filippova. "Estimation of the contribution of geophysical perturbations to the Earth pole oscillatory process at the precession frequency of the lunar orbit". IOP Conference Series: Materials Science and Engineering 927 (26 de setembro de 2020): 012036. http://dx.doi.org/10.1088/1757-899x/927/1/012036.

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Cordill, MJ, P. Kreiml, A. Lassnig, DD Gebhart, S. Zak, C. Mitterer, T. Griesser e G. Milassin. "Annealing effects on Al/polyimide adhesion in flexible optical solar reflectors". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012006. http://dx.doi.org/10.1088/1757-899x/1287/1/012006.

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Abstract Flexible optical solar reflectors are made of single and multi-layered metal thin films on polymer substrates and will encounter around 6000 thermal cycles exceeding +/-100°C during one year of operation in low earth orbit. The candidate thin film system of Inconel/silver (Ag)/Teflon (FEP) recently demonstrated early damage formation (cracks and voids) after only a few thermal cycles, most likely due to the poor interfacial properties between Ag and FEP. An alternative material system that could be used is colourless polyimide, Tormed, instead of FEP. Additionally, aluminium (Al) has demonstrated very good interfacial properties with polyimide even after thermal cycling and has suitable optical properties. The adhesion of the Al/Tormed and Ag/Tormed interfaces were evaluated with tensile induced delamination. Generally, Al/Tormed has a much higher interface adhesion energy compared to Ag/Tormed, and there is no significant degradation after bake-out in vacuum (200°C, 10-6 mbar) for 10 and 24 hrs. Thus, the Al/Tormed system could be a more robust coating system for future flexible solar reflectors.

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Henry, T., e M. Holynska. "Investigation of long-term storage of space materials for future constellation missions: study of Braycote^® 601 EF lubricant". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012011. http://dx.doi.org/10.1088/1757-899x/1287/1/012011.

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Abstract The long-term storage (LTS) of space materials is becoming more and more critical for the next missions. For instance, for MTG (Meteosat Third Generation) mission, 5-year assemble, integration and testing (AIT) time on ground, up to 17.5-year storage for recurring models plus at least 8.5 years in orbit operation are planned. Hence, a good understanding of materials’ aging properties is desirable to ensure that materials’ specifications are still suitable after LTS, and, eventually, to anticipate the potential non-conformities. For this purpose, the European Space Research and Technology Centre (ESTEC) is investigating these problematics thanks to its wide capabilities from aging with environmental, climatic and vacuum chambers up to physico-chemical characterizations by numerous instruments such as microscopes, spectroscopes, thermal, mechanical or electrical analyzers. An overview is presented herein through the study of a fluorinated based grease lubricant named Braycote® 601EF widely used in mechanisms in space sector such as the US space shuttles actuator or the basic end effectors of The European Robotic Arm.

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Baranova, V. S., S. V. Liashkevich e V. A. Saetchnikov. "Development of minimalistic propulsion system for university nanosatellite". IOP Conference Series: Materials Science and Engineering 1290, n.º 1 (1 de setembro de 2023): 012004. http://dx.doi.org/10.1088/1757-899x/1290/1/012004.

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Abstract The paper presents the results of development of a neutralizer-free high-frequency ion thruster for university nanosatellite propulsion systems which allow it to perform orbit correction tasks. The application of high-frequency ion thruster technologies allows the self-neutralization mode and is relevant for the development of engines for CubeSat format small satellites where the size and weight of the propulsion system must be as minimal as possible. A pair of shapes of neutralizer-free high-frequency ion thrusters with different accelerating region geometries are proposed. The analysis of plasma flow and the charged particles acceleration was carried out. The trajectory and acceleration of a quasi-neutral plasma flow was calculated for crossed electric and magnetic fields. The cyclotron resonance model was applied for the quasi-neutral plasma flow acceleration in an ambipolar field. The coaxial structure of the ion thruster model is discussed. Preliminary estimate of the performance of the propulsion system prototype was carried out for a pulsed operation mode. Additionally, the energy budget of a high-frequency ion thruster prototype was calculated.

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47

Canavan, Edgar R., e Brian Comber. "Critical current stability of 2G REBCO tape for space-flight HTS leads". IOP Conference Series: Materials Science and Engineering 1302, n.º 1 (1 de maio de 2024): 012016. http://dx.doi.org/10.1088/1757-899x/1302/1/012016.

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Abstract High reliability is an essential requirement for all spaceflight hardware. Like the Hitomi x-ray observatory, its follow-on mission XRISM uses 2G REBCO tapes as current leads for the superconducting magnets that are a key component of the Adiabatic Demagnetization Refrigerator (ADR) that cools the detector array. While the Hitomi Soft X-ray Spectrometer (SXS) worked flawlessly in orbit, during its development there were indications that the critical current of its specialized REBCO tapes could degrade over time when exposed to normal-humidity air. To demonstrate that the updates to the XRISM HTS lead assemblies had mitigated this risk, a series of tests were carried out to measure the stability of Ic of dozens of samples over a period greater than the flight assemblies were exposed to air during integration and test. The test rig allowed not only the measurement of the sample Ic , but also the localization of the voltage rise as the current approached Ic . We will discuss the trends in the critical current of the samples, as well as localization of lower Ic regions.

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48

Suliga, Agnieszka, Abel Brieva, Gabor Milassin, Adrian Tighe e Thomas Voirin. "High temperature atomic oxygen testing for ESA’s Envision mission to Venus". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012027. http://dx.doi.org/10.1088/1757-899x/1287/1/012027.

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Abstract EnVision will be ESA’s next Venus orbiter, providing a holistic view of the planet from its inner core to upper atmosphere to determine how and why Venus and Earth evolved so differently. The spacecraft will be equipped with a suite of instruments including a sounder to reveal underground layering, and spectrometers to study the atmosphere and surface. The thermal fluxes in orbit around Venus are high, the solar flux at Venus distance is twice its value on Earth (around 2600 W/m2), and the reflected sunlight flux has a similar order of magnitude due to the albedo. Besides, there will also be an aerobraking phase, when a third thermal flux, the aerothermal flux, needs to be considered, with a similar order of magnitude as the two others. These high total thermal fluxes, together with the cold instruments’ requirements and high-power dissipation make the thermal environment a design driver for the mission. The chemistry of the atmospheric environment during aerobraking needs also to be taken into account. Atomic oxygen exists in Venus atmosphere at the altitude range foreseen for aerobraking, with densities of up to 1017 oxygen atoms per cubic metres at aerobraking altitudes. Though the concentrations are small, their accumulation over up to 2000 atmospheric passes lead to total atomic oxygen fluences on the exposed spacecraft surfaces which are comparable to those encountered on typical Low Earth orbiting satellites (upwards of 1021 atomscm-2). This drives the selection of spacecraft materials on the most exposed surfaces. Whilst significant data exists about atomic oxygen erosion effects on materials for Low Earth Orbit, there is little knowledge about high temperature atomic oxygen effects on materials under environmental conditions representative of the Venus atmosphere. To analyse the potential risks for the Envision mission, and to assist the designers in selecting the best materials, an atomic oxygen test campaign is being performed in the ESA ESTEC atomic oxygen ground-based simulator (LEOX facility). The facility has been adapted so that material samples can be simultaneously exposed to atomic oxygen and high temperatures up to at least 200°C. For the test campaign, the Envision instrument teams and designers of the prospective satellite systems are providing candidate materials to be exposed. This includes a variety of materials to be utilised on the outside of the satellite such as thermal control coatings, optical materials, coatings for appendages and antennas and multi-layer insulation. The paper describes the modifications to the facility and the first results of the testing which has been performed.

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Gouisset, E., G. Rioland, F. Bourcier, D. Faye, P. Walter e F. Infante. "Detection and characterization of contamination with fluorescence spectroscopy". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012025. http://dx.doi.org/10.1088/1757-899x/1287/1/012025.

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Abstract In the field of failure analysis and in particular molecular and particulate contamination, being able to detect any trace of contaminants during the integration of an orbital spacecraft is crucial. In this context, fluorescence allows not only to detect but also to discriminate contaminants. We studied the fluorescence response of two epoxy adhesives, typical sources of spacecraft contamination in orbit with a portable broadband hyperspectral instrument (UV-Vis-NIR) developed in collaboration with the CNES and Intraspec Technologies, but also with a commercial spectrofluorometer. These measurements had two objectives, evaluate the performance of our hyperspectral instrument in order to identify prospect of improvement, but as well study the pertinence of fluorescence signature study in the contamination field. The first goal brings out that the hyperspectral instrument is capable of imaging the scene and allows us to extract fluorescence spectra from the image, but it still needs development, especially in term of sensitivity in UV range. The second goal shows promising results. Fluorescence studies with the spectrofluorometer emphasize that fluorescence spectra are specific to the chemical nature of the contaminant, which allows us to clearly discriminate them.

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Leveque, D., S. Duzellier, M. Vilaranda Fernandes, G. Chanteperdrix, D. Nguyen Van Sang, V. Perrin-Bailly, P. Jouanne e E. Laurent. "Interaction mechanisms between Atomic Oxygen and materials: investigation on reflected beam". IOP Conference Series: Materials Science and Engineering 1287, n.º 1 (1 de agosto de 2023): 012010. http://dx.doi.org/10.1088/1757-899x/1287/1/012010.

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Abstract Atomic Oxygen (AO) is the main component of the residual atmosphere present at low earth orbit. Multiple reflections can locally enhance or lower erosion rate in case of complex geometry. The need for precise estimate of hyperthermal AO flux is thus crucial at critical target embedded into realistic assembly. Industrial modeling tools (example Atomox module in ESABASE2 and SYSTEMA toolboxes) may account for multiple reflections with simplistic approach (ray-tracing) and a set of semi-empirical parameters. In this context, an original geometrical setup was designed in order to expose target surfaces with normal and tilted incidences and after one reflection on a set of materials of interest (black conductive thermal coatings, coverglass, surface treatment…). Candidate materials have been selected in view to compare numerical results and experimental ones. Results of two test campaigns highlight the effect of incidence angle on erosion rate (higher erosion with tilted beam) and provide an estimate of residual fluence after one reflection (in the 4-10 % range depending on material type). First computations with engineering codes have been successfully conducted, the erosion patterns being rather well described with some basic hypotheses on material parameters (absorption, specular/diffuse reflection) and taken into account the reflection on adjacent metallic surfaces.

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