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69th International Astronautical Congress: #InvolvingEveryone, IAC 2018

作者： Lai, Peter C. Sternberg, David C. Haw, Robert J. Gustafson, Eric D. Adell, Phillipe C. Baker, John D. Flight System Engineering Section NASA Jet Propulsion Laboratory California Institute of Technology 4800 Oak Grove Dr PasadenaCA91109 United States

JPL is developing the Lunar Flashlight (LF) CubeSat mission, a 6U 14 kg spacecraft whose objective is to measure potential surface water ice deposits in the permanently shadowed region (PSR) of the moon in preparation of future possible human lunar exploration. This mission will become the first interplanetary CubeSat to orbit the Moon. It uses a green propulsion system as well as an instrument with IR laser technology to search for volatiles in a specific region of the moon. The Guidance, Navigation and Control (GNC) system is crucial for delivering the spacecraft from Earth to Lunar orbit and to execute scientific measurement. Due to the challenging lunar orbit insertion and high spin rate out of launch vehicle's dispenser, the initial design concept using solar sail propulsion accompanied with small commercial-on-the-shelf (COTS) reaction wheels was abandoned mid-course and replaced by a green propulsion system along with larger reaction wheels, both newly developed for LF. However, using thrusters for small CubeSat created additional difficulties in controlling the spacecraft attitude. The story of the GNC system development, qualifications, technical challenges encountered, and lessons learned are discussed in this paper. Copyright © 2018 by the International Astronautical Federation.

关键词： Surface waters

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Fast attitude maneuvers for the lunar reconnaissance orbiter 42nd

Fast attitude maneuvers for the lunar reconnaissance orbiter

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42nd AAS Rocky Mountain section Guidance and Control Conference, 2019

作者： Karpenko, Mark Lippman, Travis Ross, I. Michael Halverson, Julie K. McClanahan, Timothy Barker, Michael Mazarico, Erwan Besser, Rebecca Dennehy, Cornelius J. VanZwieten, Tannen Wolf, Aron Department of Mechanical and Aerospace Engineering Naval Postgraduate School MontereyCA93943 United States Department of Mechanical and Aerospace Engineering Naval Postgraduate School MontereyCA93943 United States Department of Mechanical and Aerospace Engineering Naval Postgraduate School MontereyCA93943 United States NASA Goddard Space Flight Center GreenbeltMD20771 United States Solar System Exploration Division NASA Goddard Space Flight Center GreenbeltMD20771 United States NASA Goddard Space Flight Center GreenbeltMD20771 United States KBRWyle Government Services HuntsvilleAL35806 United States Goddard Space Flight Center GreenbeltMD20771 United States NASA Engineering and Safety Center John F. Kennedy Space Center Kennedy Space Center FL32899 United States Guidance and Control Section Jet Propulsion Laboratory PasadenaCA91109 United States

ISBN: (纸本)9780877036616

This paper describes a new operational capability for fast attitude maneuvering that is being developed for the Lunar Reconnaissance Orbiter (LRO). The LRO hosts seven scientific instruments. For some instruments, it is necessary to perform large off-nadir slews to collect scientific data. The accessibility of off-nadir science targets has been limited by slew rates and/or occultation, thermal and power constraints along the standard slew path. The new fast maneuver (Fast-Man) algorithm employs a slew path that autonomously avoids constraint violations while simultaneously minimizing the slew time. The FastMan algorithm will open regions of observation that were not previously feasible and improve the overall science return for LRO’s extended mission. The design of an example fast maneuver for LRO’s Lunar Orbiter Laser Altimeter that reduces the slew time by nearly 40% is presented. Pre-flight, ground-test, end-to-end tests are also presented to demonstrate the readiness of FastMan. This pioneering work is extensible and has potential to improve the science data collection return of other NASA spacecraft, especially those observatories in extended mission phases where new applications are proposed to expand their utility. © 2019, Univelt Inc. All rights reserved.

关键词： NASA

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Coronal Heating Rate in the Slow Solar Wind

arXiv

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arXiv 2023年

作者： Telloni, Daniele Romoli, Marco Velli, Marco Zank, Gary P. Adhikari, Laxman Downs, Cooper Burtovoi, Aleksandr Susino, Roberto Spadaro, Daniele Zhao, Lingling Liberatore, Alessandro Shi, Chen De Leo, Yara Abbo, Lucia Frassati, Federica Jerse, Giovanna Landini, Federico Nicolini, Gianalfredo Pancrazzi, Maurizio Russano, Giuliana Sasso, Clementina Andretta, Vincenzo Deppo, Vania Da Fineschi, Silvano Grimani, Catia Heinzel, Petr Moses, John D. Naletto, Giampiero Stangalini, Marco Teriaca, Luca Uslenghi, Michela Berlicki, Arkadiusz Bruno, Roberto Capobianco, Gerardo Capuano, Giuseppe E. Casini, Chiara Casti, Marta Chioetto, Paolo Corso, Alain J. D’Amicis, Raffaella Fabi, Michele Frassetto, Fabio Giarrusso, Marina Giordano, Silvio Guglielmino, Salvo L. Magli, Enrico Massone, Giuseppe Messerotti, Mauro Nisticò, Giuseppe Pelizzo, Maria G. Reale, Fabio Romano, Paolo Schühle, Udo Solanki, Sami K. Straus, Thomas Ventura, Rita Volpicelli, Cosimo A. Zangrilli, Luca Zimbardo, Gaetano Zuppella, Paola Bale, Stuart D. Kasper, Justin C. National Institute for Astrophysics Astrophysical Observatory of Torino Via Osservatorio 20 Pino TorineseI-10025 Italy University of Florence Department of Physics and Astronomy Via Giovanni Sansone 1 Sesto FiorentinoI-50019 Italy Earth Planetary and Space Sciences University of California Los AngelesCA90095 United States Center for Space Plasma and Aeronomic Research University of Alabama in Huntsville HuntsvilleAL35805 United States Department of Space Science University of Alabama in Huntsville HuntsvilleAL35805 United States Predictive Science Inc. San DiegoCA92121 United States National Institute for Astrophysics Astrophysical Observatory of Arcetri Largo Enrico Fermi 5 FirenzeI-50125 Italy National Institute for Astrophysics Astrophysical Observatory of Catania Via Santa Sofia 78 CataniaI-95123 Italy Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States Max Planck Institute for Solar System Research Justus-von-Liebig-Weg 3 GöttingenD-37077 Germany University of Catania Department of Physics and Astronomy Via Santa Sofia 64 CataniaI-95123 Italy National Institute for Astrophysics Astronomical Observatory of Trieste Località Basovizza 302 TriesteI-34149 Italy National Institute for Astrophysics Astronomical Observatory of Capodimonte Salita Moiariello 16 NapoliI-80131 Italy National Research Council Institute for Photonics and Nanotechnologies Via Trasea 7 PadovaI-35131 Italy University of Urbino Carlo Bo Department of Pure and Applied Sciences Via Santa Chiara 27 UrbinoI-61029 Italy National Institute for Nuclear Physics Section in Florence Via Bruno Rossi 1 Sesto FiorentinoI-50019 Italy Czech Academy of Sciences Astronomical Institute Fričova 298 OndřejovCZ-25165 Czech Republic University of Wroclaw Centre of Scientific Excellence – Solar and Stellar Activity ul. Kopernika 11 WroclawPL-51-622 Poland National Aeronautics and Space Administration Headquarters WashingtonDC20546 Un

This Letter reports the first observational estimate of the heating rate in the slowly expanding solar corona. The analysis exploits the simultaneous remote and local observations of the same coronal plasma volume with the Solar Orbiter/Metis and the Parker Solar Probe instruments, respectively, and relies on the basic solar wind magnetohydrodynamic equations. As expected, energy losses are a minor fraction of the solar wind energy flux, since most of the energy dissipation that feeds the heating and acceleration of the coronal flow occurs much closer to the Sun than the heights probed in the present study, which range from 6.3 to 13.3 R☉. The energy deposited to the supersonic wind is then used to explain the observed slight residual wind acceleration and to maintain the plasma in a non-adiabatic state. As derived in the Wentzel-Kramers-Brillouin limit, the present energy transfer rate estimates provide a lower limit, which can be very useful in refining the turbulence-based modeling of coronal heating and subsequent solar wind acceleration. © 2023, CC BY.

关键词： Magnetohydrodynamics

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Numerical and experimental aerodynamic characterization of the HEXAFLY-INT hypersonic glider 21

Numerical and experimental aerodynamic characterization of t...

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21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017

作者： Marini, Marco Pezzella, Giuseppe Schettino, Antonio Di Benedetto, Sara Villace, Victor Fernandez Steelant, Johan Gubanov, Anatoly Voevodenko, Nina Reimann, Bodo Walton, Craig Space Division Technology Integration CIRA Italian Aerospace Research Center Via Maiorise CapuaCE81043 Italy Aerothermodynamic Section Analysis and Extrapolation to Flight Lab. CIRA Italian Aerospace Research Center Via Maiorise CapuaCE81043 Italy Aerothermodynamic Section CIRA Italian Aerospace Research Center Via Maiorise CapuaCE81043 Italy Aeronautics Division System Engineering CIRA Italian Aerospace Research Center Via Maiorise CapuaCE81043 Italy ESA-ESTEC Aerothermodynamics and Propulsion Analysis Section TEC-MPA European Space Agency Keplerlaan 1 Noordwijk2200 AZ Netherlands Central Aerohydrodynamic Institute TsAGI Zhukovsky140180 Russia Lilienthalplatz 7 Braunschweig38108 Germany Gas Dynamics Ltd FarnboroughGU148LX United Kingdom

ISBN: (数字)9781624104633

ISBN: (纸本)9781624104633

As a fundamental step towards the development of a civil high-speed transport concept, the European Community (EC) co-funded HEXAFLY-INT international project (with partners from Europe, Russian Federation, Brazil and Australia), has the aim to design, manufacture and test in flight an innovative gliding hypersonic vehicle, based on the configuration developed in previous EC co-funded projects LAPCAT I, II and HEXAFLY. The flight experiment is focused on a self-controlled glider configuration characterized by high aerodynamic efficiency and equipped with several breakthrough technologies on-board, in order to provide valuable aerodynamic and aero-structural flight data to validate methods and technologies used to design the hypersonic vehicle. In this framework, this paper provides a detailed overview on research efforts carried out in assessing the aerodynamic performance of the expendable Experimental flight Test Vehicle under development in the programme. Aerodynamic results are obtained by means of a massive number of CFD simulations of increasing level of accuracy and through an experimental test campaign carried out at TsAGI in their T-116 wind tunnel facility. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.

关键词： Hypersonic vehicles

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STATE OF THE CLIMATE IN 2021

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BULLETIN OF THE AMERICAN METEOROLOGICAL SOCIETY 2022年第8期103卷 S1-S1页

作者： Blunden, Jessica NOAA/NESDIS National Centers for Environmental Information Asheville NC United States NOAA NESDIS National Centers for Environmental Information Silver Spring MD United States Met Office Hadley Centre Exeter United Kingdom Cooperative Institute for Satellite Earth System Studies North Carolina State University Asheville NC United States Communications and Outreach NOAA/NESDIS National Centers for Environmental Information Asheville NC United States Innovative Consulting and Management Services LLC NOAA/NESDIS National Centers for Environmental Information Asheville NC United States European Centre for Medium-Range Weather Forecasts Reading United Kingdom CMNS-Earth System Science Interdisciplinary Center University of Maryland College Park MD United States Department of Meteorology National Centre for Earth Observation University of Reading Reading United Kingdom Department of Atmospheric and Planetary Science Hampton University Hampton VA United States National Research Institute for Agriculture Food and Environment (INRAE) CARRTEL Université Savoie Mont Blanc Thonon les Bains France Graduate School of Life and Environmental Sciences Osaka Prefecture University Osaka Sakai Japan University of Bremen Bremen Germany NOAA Global Monitoring Laboratory Boulder CO United States Centro de Investigaciones sobre Desertificación Spanish National Research Council (CIDE CSIC-UV-Generalitat Valenciana) Climate Atmosphere and Ocean Laboratory (Climatoc-Lab) Moncada Valencia Spain Instituto de Geografía Pontificia Universidad Católica de Valparaíso Valparaíso Chile Climatic Research Unit School of Environmental Sciences University of East Anglia Norwich United Kingdom Joint Research Centre of the European Commission Ispra Italy GloH2O Almere Netherlands University of Reading Reading United Kingdom School of Engineering Newcastle University Newcastle-upon-Tyne United Kingdom Université de Paris Cité Institut de physique du globe de Paris CNRS IGN Paris

Editors note: For easy download the posted pdf of the State of the Climate in 2021 is a low-resolution file. A high-resolution copy of the report is available by clickinghere. Please be patient as it may take a few mi... 详细信息

关键词： Greenhouse gases

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On the origin & thermal stability of Arrokoth’s and Pluto’s ices

arXiv

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arXiv 2020年

作者： Lisse, Carey M. Young, L.A. Cruikshank, D.P. Sandford, S.A. Schmitt, B. Stern, S.A. Weaver, H.A. Umurhan, O. Pendleton, Y.J. Keane, J.T. Gladstone, G.R. Parker, J.M. Binzel, R.P. Earle, A.M. Horanyi, M. El-Maarry, M. Cheng, A.F. Moore, J.M. McKinnon, W.B. Grundy, W.M. Kavelaars, J.J. Linscott, I.R. Lyra, W. Lewis, B.L. Britt, D.T. Spencer, J.R. Olkin, C.B. McNutt, R.L. Elliott, H.A. Dello-Russo, N. Steckloff, J.K. Neveu, M. Mousis, O. Space Exploration Sector Johns Hopkins University Applied Physics Laboratory 11100 Johns Hopkins Rd LaurelMD20723 United States Southwest Research Institute BoulderCO80302 United States Astrophysics Branch Space Sciences Division NASA/Ames Research Center Moffett FieldCA94035 United States Université Grenoble Alpes CNRS CNES Institut de Planétologie et Astrophysique de Grenoble Grenoble France Solar System Exploration Research Virtual Institute NASA/Ames Research Center Moffett FieldCA94035 United States Astrophysics and Space Sciences Section Jet Propulsion Laboratory/Caltech PasadenaCA91109 United States Southwest Research Institute San AntonioTX28510 United States Dept. of Earth Atmospheric and Planetary Sciences Massachusetts Institute of Technology CambridgeMA02139 United States Laboratory for Atmospheric & Space Physics University of Colorado BoulderCO80303 United States Birkbeck University of London LondonWC12 7HX United Kingdom Department of Earth and Planetary Sciences and McDonnell Center for Space Sciences Washington University One Brookings Drive St. LouisMO63130 United States Lowell Observatory 1400 West Mars Hill Road FlagstaffAZ86001 United States NRC Herzberg Inst of Astrophysics 5071 W Saanich Road Victoria BCBCV9E 2E7 Canada Hansen Experimental Physics Laboratory Stanford University StanfordCA94305-9515 United States Dept. of Astronomy New Mexico State University PO BOX 30001 MSC 4500 Las CrucesNM88003-8001 United States Department of Astronomy Columbia University 550 W. 120th St. New YorkNY10027 United States Division of Astronomy and Astrophysics University of California Los Angeles 475 Portola Plaza Los AngelesCA90025 United States Department of Physics University of Central Florida OrlandoFL32816 United States Physics and Astronomy Department University of Texas at San Antonio San AntonioTX78249 United States Planetary Science Institute TucsonAZ85719 United States Department of Aerospace

In this paper we discuss in a thermodynamic, geologically empirical way the long-term nature of the stable majority ices that could be present in Kuiper Belt object (KBO) 2014 MU69 (also called Arrokoth;hereafter "MU69") after its 4.6 Gyr residence in the Edgeworth-Kuiper belt (EKB) as a cold classical object. We compare the upper bounds for the gas production rate (~1024 molecules/sec) measured by the New Horizons (NH) spacecraft flyby on 01 Jan 2019 to estimates for the outgassing flux rates from a suite of common cometary and KBO ices at the average ~40K sunlit surface temperature of MU69, but do not find the upper limit very constraining except for the most volatile of species (e.g. CO, N2, CH4). More constraining is the stability versus sublimation into vacuum requirement over Myr to Gyr, and from this we find only 3 common ices that are truly refractory: HCN, CH3OH, and H2O (in order of increasing stability), while NH3 and H2CO ices are marginally stable and may be removed by any positive temperature excursions in the EKB, as produced every 108 – 109 yrs by nearby supernovae and passing O/B stars. To date the NH team has reported the presence of abundant CH3OH and H2O on MU69’s surface (Stern et al. 2019, Grundy et al. 2020). NH3 has been searched for, but not found. We predict that future absorption feature detections, if any are ever derived from higher signal-to-noise ratio spectra, will be due to an HCN or poly-H2CO based species. Consideration of the conditions present in the EKB region during the formation era of MU69 lead us to state that it is highly likely that it "formed in the dark", in an optically thick mid-plane, unable to see the nascent, variable, highly luminous Young Stellar Object (YSO)/TTauri Sun, and that KBOs contain HCN and CH3OH ice phases in addition to the H2O ice phases found in their short period (SP) comet descendants. Finally, when we apply our ice thermal stability analysis to bodies/populations related to MU69, we find that meth

关键词： Signal to noise ratio

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Decision-making for unmanned aerial vehicle operation in icing conditions

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CEAS Aeronautical Journal 2016年第4期7卷 663-675页

作者： Armanini, S.F. Polak, M. Gautrey, J.E. Lucas, A. Whidborne, J.F. Faculty of Aerospace Engineering Section Control and Simulation Delft University of Technology Kluyverweg 1 Delft2629HS Netherlands Institute of Flight System Dynamics Technische Universität München Boltzmannstraße 15 Garching85748 Germany National Flying Laboratory Centre School of Aerospace Transport and Manufacturing Cranfield University BedfordshireMK43 0AL United Kingdom Dynamics Simulation and Control Group School of Aerospace Transport and Manufacturing Cranfield University BedfordshireMK43 0AL United Kingdom AOS Group Ltd Sheraton House CB3 0AX CambridgeCastle Park United Kingdom

With the increased use of unmanned aerial systems (UAS) for civil and commercial applications, there is a strong demand for new regulations and technology that will eventually permit for the integration of UAS in unsegregated airspace. This requires new technology to ensure sufficient safety and a smooth integration process. The absence of a pilot on board a vehicle introduces new problems that do not arise in manned flight. One challenging and safety-critical issue is flight in known icing conditions. Whereas in manned flight, dealing with icing is left to the pilot and his appraisal of the situation at hand;in unmanned flight, this is no longer an option and new solutions are required. To address this, an icing-related decision-making system (IRDMS) is proposed. The system quantifies in-flight icing based on changes in aircraft performance and measurements of environmental properties, and evaluates what the effects on the aircraft are. Based on this, it determines whether the aircraft can proceed, and whether and which available icing protection systems should be activated. In this way, advice on an appropriate response is given to the operator on the ground, to ensure safe continuation of the flight and avoid possible accidents. © 2016, The Author(s).

关键词： Decision making

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A technique to evaluate on-orbit thermal deformation for large precise structures in ASTRO-H 56

A technique to evaluate on-orbit thermal deformation for lar...

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56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference 2015

作者： Kawano, Taro Ishimura, Kosei Minesugi, Kenji Omagari, Kuniyuki Tanaka, Kentaro ISAS/JAXA Mechanics and Materials Group 3-1-1 Yoshinodai Chuo-ku SagamiharaKanagawa252-5210 Japan ISAS/JAXA Department of Space Flight Systems 3-1-1 Yoshinodai Chuo-ku SagamiharaKanagawa252-5210 Japan NEC Corporation Department Space systems division 1-10 Nisshin-Cho Fuchu Tokyo183-8501 Japan Nippi Corporation System Design Section Engineering department Aerospace Division NIPPI YokohamaKanagawa236-8540 Japan

ISBN: (数字)9781624103421

ISBN: (纸本)9781624103421

ASTRO-H is a next-generation X-ray observatory satellite planned for launch in fiscal 2015. Because ASTRO-H is a large structure and requires precise and accurate pointing, an understanding of on-orbit thermal deformation behavior is particularly important to the success of the ASTRO-H mission. In the conventional technique for predicting thermal deformation, testing is performed in a thermal vacuum chamber so asto simulate the temperature distribution on orbit. However, when using this conventional technique it is difficult to observe the detailed characteristics of the tested structures due to the limits of the applied temperature distribution cases. To overcome this problem, we propose a new evaluation technique for ASTRO-H. In our technique, on-orbit prediction of thermal deformation is performed thorough numerical simulation using a finite element (FE) model. The validation and correlation of the FE model are carried out by comparing results with thermal deformation test data collected in advance. This technique is especially suitable for satellites that are exposed to various thermal conditions on orbit. Using this technique, we confirmed all of the requirements for on-orbit pointing accuracy and precision in ASTRO-H. © 2015, American Institute of Aeronautics and Astronautics Inc. All rights Reserved.

关键词： Temperature distribution

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In-flight operation of the dawn ion propulsion system through the preparations for escape from Vesta

In-flight operation of the dawn ion propulsion system throug...

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48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012

作者： Garner, Charles E. Rayman, Marc D. Brophy, John R. Mikes, Steven C. Jet Propulsion Laboratory California Institute of Technology Pasadena CA 91109 United States Propulsion and Materials Engineering Section Jet Propulsion Laboratory California Institute of Technology Pasadena CA 91109 United States Flight System Avionics Section Jet Propulsion Laboratory California Institute of Technology Pasadena CA 91109 United States

ISBN: (纸本)9781600869358

The Dawn mission, part of NASA's Discovery Program, has as its goal the scientific exploration of the two most massive main-belt asteroids, 4 Vesta, and the dwarf planet 1 Ceres. The Dawn spacecraft was launched from the Cape Canaveral Air Force Station on September 27, 2007 on a Delta-II 7925H-9.5 rocket that placed the 1218-kg spacecraft into an Earth-escape trajectory. On-board the spacecraft is an ion propulsion system (IPS) developed at the Jet Propulsion Laboratory which will provide a total delta-V of approximately 11 km/s for the heliocentric transfer to Vesta, orbit capture at Vesta, transfer between Vesta science orbits, departure and escape from Vesta, heliocentric transfer to Ceres, orbit capture at Ceres, transfer between Ceres science orbits, and orbit maintenance maneuvers for all Vesta and Ceres science orbits. Full-power thrusting from December 2007 through October 2008 was used to successfully target a Mars gravity assist flyby in February 2009 that provided an additional delta-V of 2.6 km/s. Deterministic thrusting for the heliocentric transfer to Vesta resumed in June 2009 and concluded with orbit capture at Vesta on July 16, 2011. An additional 231 hours of IPS thrusting was used to enter the first Vesta science orbit, called Survey orbit, on August 3, 2011 at an altitude of about 2,735 km. The IPS was then used over the next year to transfer the spacecraft to the other science orbits: a high altitude mapping orbit (HAMO-1) in September 2011 at an altitude of approximately 673 km, a low altitude mapping orbit (LAMO) at approximately 210 km altitude, and a second high altitude mapping orbit (HAMO-2) at approximately 673 km altitude. To date the IPS has been operated for approximately 24,327 hours, consumed approximately 260 kg of xenon, and provided a delta-V of approximately 7 km/s. IPS performance characteristics are very close to the expected performance based on analysis and testing performed pre-launch. Thrusting for escape from Vesta and cr

关键词： Orbits

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Cloud computing for mission design and operations

Cloud computing for mission design and operations

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12th International Conference on Space Operations, SpaceOps 2012

作者： Arrieta, Juan Beswick, Robert Gerasimatos, Dimitrios Jet Propulsion Laboratory California Institute of Technology Flight Path Control Section 4800 Oak Grove Drive M/S 230-205 Pasadena CA 91109 United States Jet Propulsion Laboratory California Institute of Technology Navigation and Mission Design System Engineering Section 4800 Oak Grove Drive M/S 301-121 Pasadena CA 91109 United States

The space mission design and operations community already recognizes the value of cloud computing and virtualization. However, natural and valid concerns, like security, privacy, up-time, and vendor lock-in, have prevented a more widespread and expedited adoption into official workflows. In the interest of alleviating these concerns, we propose a series of guidelines for internally deploying a resource-oriented hub of data and algorithms. These guidelines provide a roadmap for implementing an architecture inspired in the cloud com- puting model: associative, elastic, semantical, interconnected, and adaptive. The architec- ture can be summarized as exposing data and algorithms as resource-oriented Web services, coordinated via messaging, and running on virtual machines;it is simple, and based on widely adopted standards, protocols, and tools. The architecture may help reduce com- mon sources of complexity intrinsic to data-driven, collaborative interactions and, most importantly, it may provide the means for teams and agencies to evaluate the cloud com- puting model in their specific context, with minimal infrastructure changes, and before committing to a specific cloud services provider. © 2012 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Cloud computing

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