Frontiers in Space Technologies最新文献

{"title":"Matrix-assisted laser desorption/ionization analysis of the brain proteome of microgravity-exposed mice from the International Space Station","authors":"Correy Vigil, A. Daubenspeck, Heidi G Coia, Jerremy Smith, C. Mauzy","doi":"10.3389/frspt.2022.971229","DOIUrl":"https://doi.org/10.3389/frspt.2022.971229","url":null,"abstract":"Manned spaceflight exposes humans to extreme environmental conditions, including microgravity exposures. The effects of microgravity during spaceflight could lead to changes in brain structure, gene expression, and vascular physiology. Given the known physiological effects, it is highly likely that there are microgravity-initiated proteomic differentials in the brain, possibly domain specific. MALDI-TOF (matrix-assisted laser desorption/ionization time of flight) Imaging Mass Spectrometry allows the visualization of the spatial distribution of highly abundant intact proteins in tissue specimens. This study utilized this technique to visualize global proteomic changes induced by microgravity exposure in brain tissue received from the Rodent Research-1 Center for the Advancement of Science in Space (CASIS)/National Aeronautics and Space Administration (NASA). Proteome profiles were obtained from isolated whole brain tissue from microgravity exposed, Habitat control, and baseline. While a total of 135 mass peaks equating to individual proteins were identified, statistical analysis determined that there were no significant differences in the spectra profiles from the three test groups utilizing this methodology, possibly due to sample collection logistics rather than lack of cellular response.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"19 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125776382","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Design and environmental testing of imaging payload for a 6 U CubeSat at low Earth orbit: KITSUNE mission","authors":"M. H. Azami, Necmi Cihan Orger, V. H. Schulz, Takashi Oshiro, J. R. Alarcón, A. Maskey, Kazuhiro Nakayama, Yoshiya Fukuda, Kaname Kojima, T. Yamauchi, H. Masui, M. Cho","doi":"10.3389/frspt.2022.1000219","DOIUrl":"https://doi.org/10.3389/frspt.2022.1000219","url":null,"abstract":"Earth observation (EO) missions remain a challenging task for small satellite platforms due to their demanding requirements and space environment effects. In this study, the camera payload development and mission requirements are presented together with the ground-based testing results for a 6U CubeSat called KITSUNE, operating at low Earth orbit. The major challenge of the payload development is maintaining the focus of the optical system despite the thermal vacuum environment in orbit since the low thermal capacity and rapid temperature variation of CubeSats hinder the camera focus. First, the payload is developed with an objective of a 5-m-class imaging mission, which has a 31.4 MP CMOS sensor and a lens with a 300-mm focal length. Second, polyimide heaters and multilayer insulators are utilized in order to maintain focus during imaging operations. Third, a collimator lens is used to aid in image capture during thermal vacuum tests. These images are analyzed thoroughly using various focus measure operators. The Diagonal Laplacian was found to be the most suitable operator due to the consistency in test results. The results also showed that the heat generated by the camera sensor significantly affects the lens temperature and, ultimately, the target temperature of the lens was defined at −1.8°C. Finally, the test results are discussed, including thermal vacuum, vibration, total ionization dose, and the effect of exposure to direct sunlight on the CMOS sensor.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-11-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130335919","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Development of an inexpensive 3D clinostat and comparison with other microgravity simulators using Mycobacterium marinum","authors":"Joseph L. Clary, Creighton S. France, Kara R. Lind, Runhua Shi, J. Alexander, J. Richards, R. Scott, Jian Wang, Xiao-Hong Lu, Lynn Harrison","doi":"10.3389/frspt.2022.1032610","DOIUrl":"https://doi.org/10.3389/frspt.2022.1032610","url":null,"abstract":"2D and 3D Clinostats are used to simulate microgravity on Earth. These machines continuously alter the sample’s orientation, so the acceleration vector changes faster than the biological endpoint being monitored. Two commercially available microgravity simulators are the Rotary Cell Culture System (Synthecon Inc.), which is a 2D clinostat, and the RPM 2.0 (Yuri), which is a 3D clinostat that can operate as a random positioning machine or in constant frame velocity mode. We have developed an inexpensive 3D clinostat that can be 3D printed and assembled easily. To determine the optimal combination of inner (I) and outer (O) frame velocities to simulate microgravity, two factors were considered: the time-averaged magnitude and the distribution of the acceleration vector. A computer model was developed to predict the acceleration vector for combinations of frame velocities between 0.125 revolutions per minute (rpm) and 4 rpm, and a combination of I = 1.5 rpm and O = 3.875 rpm was predicted to produce the best microgravity simulation. Two other frame velocity combinations were also used in further tests: I = 0.75 rpm and O = 3.625 rpm, and I = 2 rpm and O = 1.125 rpm. By operating the RPM 2.0 in constant velocity mode at these three velocity combinations, the RPM 2.0 algorithm data confirmed that these operating conditions simulated microgravity. Mycobacterium marinum was selected for biological comparison experiments as this bacterium can grow as a biofilm or a planktonic culture. Biofilm experiments revealed that the RPM 2.0 and the 3D clinostat with I = 1.5 rpm and O = 3.825 rpm produced similar structures in attached biofilm, and similar changes in transcriptome for the bacteria in suspension compared to the normal gravity transcriptome. Operating the 3D clinostat at I = 2 rpm and O = 1.125 rpm, and the Synthecon 2D clinostat in simulated microgravity orientation at 25 rpm resulted in the same decreased planktonic growth and increased rifampicin survival compared to normal gravity. This study validates the inexpensive 3D clinostat and demonstrates the importance of testing the operating conditions of lab-developed clinostats with biological experiments.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115330082","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Editorial: Astrodynamics, guidance, navigation and control in chaotic multi-body environments","authors":"A. Colagrossi, S. Lizy-Destrez, N. Baresi, J. Masdemont, Lorenzo Bucci","doi":"10.3389/frspt.2022.1063163","DOIUrl":"https://doi.org/10.3389/frspt.2022.1063163","url":null,"abstract":"Modern space missions are frequently targeted towards new and unexplored regions of space, such as the region between the Earth and the Moon, which is denoted as the Cislunar space (NASA, 2020; International Space Exploration Coordination Group – ISECG, 2018); binary asteroid systems (Rivkin et al., 2021); comets and other irregularly shaped celestial objects; satellites of other Solar system planets. In all of these mission scenarios, the spacecraft dynamics is governed by an intriguing, yet complex and chaotic dynamical environment that is driven by the presence of multiple and/or non-spherical massive bodies. The gravitational influence of these objects shall be addressed with methods and techniques that are different from the standard Keplerian tools available in the classic Two-Body Problem. In recent years, the space community has shown a renovated scientific and technological interest in mastering the multi-body nonKeplerian astrodynamics for practical applications. Immediately, new technological and engineering challenges emerged in order to cope with this uninvestigated portion of outer space. In particular, the Guidance, Navigation and Control (GNC) and the Propulsive subsystems developments have been strongly supportive of this endeavor. Future lunar and solar system exploration missions will be supported by a complex infrastructure of space systems orbiting in multi-body regions and influenced by chaotic dynamics (Whitley and Martinez, 2016). They will guarantee continuous human and robotic presence well beyond Earth orbits, broadcast of communication relay networks, Solar system exploration and advanced navigation systems. This new space race demands the upgrade of consolidated space technologies to handle the unique features of multi-body environments, by OPEN ACCESS","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-10-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128939460","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Linking remote sensing, in situ and laboratory spectroscopy for a Ryugu analog meteorite sample","authors":"A. Maturilli, S. Schwinger, E. Bonato, J. Helbert, M. Baqué, M. Hamm, G. Alemanno, M. d'Amore","doi":"10.3389/frspt.2022.1023393","DOIUrl":"https://doi.org/10.3389/frspt.2022.1023393","url":null,"abstract":"In 2022 JAXA issued an Announcement of Opportunity (AO) for receiving Hayabusa2 samples returned to Earth. We responded to the AO submitting a proposal based on using a multi-prong approach to achieve two main goals. The first goal is to address the subdued contrast of remote-sensing observations compared to measurements performed under laboratory conditions on analog materials. For this we will link the hyperspectral and imaging data collected from the spacecraft and the in-situ observations from the MASCOT lander instruments (MARA and MASCam) with laboratory-based measurements of Hayabusa2 samples using bi-directional reflectance spectroscopy under simulated asteroid surface conditions from UV to MIR/FIR achieved using three Bruker Vertex 80 V spectrometers in the Planetary Spectroscopy Laboratory. The second goal is the investigation of the mineralogy and organic matter of the samples collected by Hayabusa2, to better understanding the evolution of materials characterizing Ryugu and in general of protoplanetary disk and organic matter, investigating the aqueous alteration that took place in the parent body, and comparing the results with data collected from pristine carbonaceous chondrite analog meteorites. Spectral data will be complemented by Raman spectroscopy under simulated asteroid surface conditions, X-ray diffraction, would also allow us to define the bulk mineralogy of the samples as well as investigate the presence and nature of organic matter within the samples. In situ mineralogical and geochemical characterization will involve a pre-characterization of the sample fragments through scanning electron microscopy low voltage electron dispersive X-ray (EDX) maps, and micro IR analyses of the fragments. If allowed, a thin section of one grain will be used for electron microprobe analyses to geochemically characterize its mineralogical composition. To train our data collection and analysis methods on a realistic sample, we selected a piece of the Mukundpura meteorite, as one of the closer analogs to Ryugu’s surface (Ray et al., Planetary and Space Science, 2018, 151, 149–154). The Mukundpura chunk we selected for this study measures 3 mm in its maximum dimension, and we chose it so to have a test sample of the same size as the Hayabusa2 grain we requested in our proposal to JAXA’s AO. The test gave us confidence that we can measure with good SNR measurements in bi-directional reflectance for samples around 3 mm in size (see Figures 3, 4 below). To address our second goal the spectral data was complemented by Raman spectroscopy measured again under simulated asteroid surface conditions in our Raman Mineralogy and Biodetection Laboratory at DLR.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116852306","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A novel evaluation method for in situ space debris detection based on conductive traces","authors":"Sebastian Fexer","doi":"10.3389/frspt.2022.867853","DOIUrl":"https://doi.org/10.3389/frspt.2022.867853","url":null,"abstract":"To enable the detection of micrometeoroids and small-sized space debris (MMSD) in the sub-mm range, in situ detectors aboard a spacecraft are the tool of choice. Unfortunately, only a few projects have been sent to space until today. However, knowledge of the MMSD population is important to keep the reference models up-to-date and gain more insights into factors like the amount of debris and its distribution along certain orbits. This will be crucial for the safety of current and future spaceflight missions. Present-day in situ detection systems mostly rely on impact recognition and characterization using different methods. One of them is the perforation of a special detection area during such an event. These areas consist of one or more layers provided with conductive traces. Any interruption of one of these lines can be recognized using some kind of electrical continuity testing method or the determination of the resistance. This goes along with some drawbacks, like the difficult or even impossible multi-event recognition along one line. The proposed concept relies on a reflectometric approach. In doing so, for example, pulses are being sent along a well-defined transmission line, which is a part of the detection area. Any alteration in the characteristic line impedance, for instance, due to an impact, will generate reflections back into the generator. Their evaluation can provide the location as well as the complex impedance of the perturbation.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-10-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128139151","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"MOVE-III: A CubeSat for the detection of sub-millimetre space debris and meteoroids in Low Earth Orbit","authors":"X. Oikonomidou, E. Karagiannis, Dominik Still, F. Strasser, Felix S. Firmbach, Jonathan Hettwer, Allan G. Schweinfurth, Paul Pucknus, Deniz Menekay, Tianyi You, Maximilian Vovk, Selina Weber, Zeyu Zhu","doi":"10.3389/frspt.2022.933988","DOIUrl":"https://doi.org/10.3389/frspt.2022.933988","url":null,"abstract":"The Munich Orbital Verification Experiment (MOVE) is a CubeSat student project housed at the Scientific Workgroup for Rocketry and Spaceflight at the Technical University of Munich. MOVE-III is the fourth CubeSat under development, and the first 6U mission of the MOVE project that will carry a dedicated scientific payload in orbit. The mission aims at acquiring in-situ observations of sub-millimetre space debris and meteoroids in Low Earth Orbit, with the objective of compiling a dataset of flux, as well as object mass and velocity measurements that can be used for the validation of the small object estimates of space debris models and support further studies related to the characterisation of the space environment. The MOVE-III CubeSat employs the MOVE-BEYOND platform and is planned to carry three Debris Density Retrieval and Analysis (DEDRA) plasma ionization sensors. The Preliminary Design Review has been completed in early 2022, with the next milestone being the Critical Design Review, planned for 2023. The paper elaborates on the scientific objectives of the mission and the expected data products, provides an overview of the detector operation principle and presents the overall system architecture, the platform configuration and the subsystem interaction. Considerations on the debris mitigation aspects of the mission are additionally discussed.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-10-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131682647","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Dynamics and control analysis during rendezvous in non-Keplerian Earth—Moon orbits","authors":"M. Innocenti, Giordana Bucchioni, G. Franzini, Michele Galullo, Fabio D’ Onofrio, A. Cropp, M. Casasco","doi":"10.3389/frspt.2022.929179","DOIUrl":"https://doi.org/10.3389/frspt.2022.929179","url":null,"abstract":"The paper describes the development of a framework capable of addressing some fundamental issues in the analysis of proximity operations between two spacecraft that are operating within a three-body model defined by two primaries and the spacecraft themselves. The main objective is to enable the capability of analysing dynamic and control issues during an automated rendezvous between a vehicle and a passive space station orbiting around the Earth - Moon L2 Lagrangian point on a near rectilinear halo orbit. The paper presents first a restricted three body model dynamics and a nominal approach trajectory, followed by an analysis of the influence of assumed actuators and sensors. Critical aspects such as selected failures are investigated, in order to ensure passive safety of the mission using impulsive maneuvers. An example of closed loop guidance in the near range is also presented and the overall performance are validated with an Ephemeris model available in the literature.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-10-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132403377","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Analysis of upper atmospheric effects on material per onboard atomic oxygen monitor system of SLATS","authors":"Y. Kimoto, Yuta Tsuchiya, E. Miyazaki, Aki Goto, K. Yukumatsu, S. Imamura","doi":"10.3389/frspt.2022.891753","DOIUrl":"https://doi.org/10.3389/frspt.2022.891753","url":null,"abstract":"JAXA has proposed an innovative idea for satellites in Low Earth Orbit (LEO). The Super-Low Altitude Test Satellite (SLATS), also known as TSUBAME, is the first Earth observation satellite to occupy a Super-Low Orbit (S-LEO) or Very Low Earth Orbit (VLEO), below 300 km. The purposes of SLATS are 1) testing the maintenance of the satellite’s altitude with its ion engine against high atmospheric drag at a super-low altitude, 2) acquiring data on atmospheric density and atomic oxygen (AO), and 3) testing optical Earth observation. SLATS was successfully launched on 23 December 2017. SLATS was then altitude-controlled for 636 days to 271.7 km using chemical thrusters, aerodynamic drag, and ion engine propulsion. SLATS finally maintained its orbit of 167.4 km for 7 days and finished its operation on 1 October 2019. All the SLATS and Atomic oxygen MOnitor (AMO) data was acquired during these operations. The AMO is one of the mission sensors that monitor AO and its effects on spacecraft materials. The data from the AMO contributes to the choice of materials in future S-LEO satellite design. The data obtained by the AMO are valuable in that they provide considerable knowledge on AO fluence and its effects on space materials. A precise atmospheric density model and atmospheric composition model are indispensable for predicting the trajectory or re-entry of debris in orbit. Atmospheric models such as NRLMSISE-00, JB 2008, and DTM2013 have been developed, but few studies compare these models and the actual atmospheric environment in LEO. The average atmospheric density obtained from SLATS is lower than the value predicted by the atmospheric models (NRLMSISE-00, JB 2008, and DTM 2013). Understanding the model’s accuracy will contribute to the orbit control of future S-LEO satellites and the orbit prediction and control of debris in LEO.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-10-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130333067","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"The wedge-pentahedra method (WPM): Topographic reduction of local terrain in the context of solar system surface gravimetry and robotic exploration","authors":"M. Noeker, Ö. Karatekin","doi":"10.3389/frspt.2022.982873","DOIUrl":"https://doi.org/10.3389/frspt.2022.982873","url":null,"abstract":"In classical gravimetry, different corrections are applied, e.g. to correct for the measurement elevation above a reference plane and the gravitational attraction of the material lying between the measurement point and reference plane. Additionally, and especially in non-flat regions, a correction for the topography is generally needed. While this contribution is relatively small on spherical celestial objects, it can be more important for irregularly shaped bodies, such as small bodies or some natural satellites. With the surface gravity being much smaller, the relative importance of the topographic correction increases, while the approximation errors of the surface will become larger. In this work, the novel Wedge-Pentahedra Method (WPM) for topographic correction for (near-) surface gravimetric measurements and simulations is presented that allows precise topographic corrections for asteroids and natural satellites. For a first study, the WPM is applied to the Martian moon Phobos. Taking an exemplary surface location, a high-resolution artificial terrain is added to the surrounding, and the gravitational influence of this topography compared to the original surface is assessed. It is found that the influence of topography on the surface gravity of a small body such as Phobos can be in the order of a few percent, making it an important correction not only for surface gravity science, but likewise for landing and surface operations, to best ensure the mission success. Therefore, the here presented WPM opens a manifold of possible future applications in the context of Solar System exploration, regarding both space science and space technology.","PeriodicalId":137674,"journal":{"name":"Frontiers in Space Technologies","volume":"176 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-09-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115549090","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}