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AIAA Infotech @ Aerospace 2015

作者： Fesq, Lorraine M. Jacome, Raquel Weitl Jet Propulsion Laboratory California Institute of Technology Systems Engineering and Formulation Division 4800 Oak Grove Drive PasadenaCA91109 United States

ISBN: (数字)9781624103384

ISBN: (纸本)9781624103384

NASA designs and builds systems that achieve incredibly ambitious goals, as evidenced by the Curiosity rover traversing on Mars, the highly complex International Space Station orbiting our Earth, and the compelling plans for capturing, retrieving and redirecting an asteroid into a lunar orbit to create a nearby a target to be investigated by astronauts. In order to accomplish these feats, the missions must be imbued with sufficient knowledge and capability not only to realize the goals, but also to identify and respond to offnominal conditions. Fault Management (FM) is the discipline of establishing how a system will respond to preserve its ability to function even in the presence of faults. In 2012, NASA released a draft FM Handbook in an attempt to coalesce the field by establishing a unified terminology and a common process for designing FM mechanisms. However, FM approaches are very diverse across NASA, especially between the different mission types such as Earth orbiters, launch vehicles, deep space robotic vehicles and human spaceflight missions, and the authors were challenged to capture and represent all of these views. The authors recognized that a necessary precursor step is for each sub-community to codify its FM policies, practices and approaches in individual, focused guidebooks. Then, the sub-communities can look across NASA to better understand the different ways off-nominal conditions are addressed, and to seek commonality or at least an understanding of the multitude of FM approaches. This paper describes the development of the "Deep Space Robotic Fault Management Guidebook," which is intended to be the first of NASA’s FM guidebooks. Its purpose is to be a field-guide for FM practitioners working on deep space robotic missions, as well as a planning tool for project managers. Publication of this Deep Space Robotic FM Guidebook is expected in early 2015. The guidebook will be posted on NASA’s engineering Network on the FM Community of Practice websit

关键词： NASA

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Transformers of extreme environments and their integration in a solar power infrastructure

Transformers of extreme environments and their integration i...

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AIAA Space and Astronautics Forum and Exposition, SPACE 2016

作者： Stoica, Adrian Quadrelli, Marco B. Ingham, Michel Tamppari, Leslie Mitchell, Karl Gutt, Gary Robotics and Mobility Systems Section Autonomous Systems Division Jet Propulsion Laboratory California Institute of Technology Mail Stop 198-219 4800 Oak Grove Drive PasadenaCA91109-8099 United States Autonomous Systems Division Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109-8099 United States Systems Engineering and Formulation Division Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109-8099 United States Science Division Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109-8099 United States Optical Section Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109-8099 United States

ISBN: (纸本)9781624104275

TransFormers (TF) are adaptive, shape-changing robotic systems that transform a region of an extreme environment, by projecting energy to it, making it milder at the targeted locale, with less environmental constraints on robots or humans operating there. This paper focuses on TF that project solar energy into dark and cold areas, such as permanently shaded craters, to provide illumination and heat and enable long-duration low-cost missions. Thus, TF offer an attractive solution for operations in ice-harboring craters on polar regions of the Moon or Mercury, and caves on Mars and lava tubes on Moon, of high interest not only for great scientific value, but also as shielded habitats for human bases. We performed high-level analysis of four mission scenarios. For a mission scenario involving operations up to 10km deep into the Moon’s Shackleton crater at below 80K temperatures we performed optical and thermal analyses to provide 300W of power to the solar panels of an MSL-class rover. The area of TFs reflecting sunlight from the rim must be more than ~1000m2. A network of TFs would form the backbone of an integrated Solar Power Infrastructure, in which the combined illumination provided to regions of interest is continuous, even though none of the individual TransFormers is continuously illuminated year-round. A Lunar South Pole Solar Power Infrastructure around Shackleton Crater is briefly introduced. © 2016 California Institute of Technology.

关键词： Solar energy

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GraCE-FO: The gravity recovery and climate experiment follow-on mission

GraCE-FO: The gravity recovery and climate experiment follow...

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作者： Kornfeld, Richard P. Arnold, Bradford W. Gross, Michael A. Dahya, Neil T. Klipstein, William M. Gath, Peter F. Bettadpur, Srinivas Systems Engineering and Formulation Division Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States MWI Instrument Manager Communications Tracking and Radar Division Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States GRACE-FO Project Office Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States Airbus Earth Observation Systems Airbus Defence and Space GmbH Immenstaad88090 Germany Center for Space Research University of Texas at Austin AustinTX78759 United States

The Gravity Recovery and Climate Experiment Follow-On mission was conceived to continue the successful legacy of the recently decommissioned Gravity Recovery and Climate Experiment mission and, at the same time, serve as a platform to demonstrate the first-ever in-space intersatellite laser ranging interferometer as a technology pathfinder for future gravity mapping missions. Launched in May of 2018, the Gravity Recovery and Climate Experiment Follow-On observatory builds on the design of the original Gravity Recovery and Climate Experiment satellites, but incorporates a number of improvements based on lessons learned, and features significantly increased complexity due to the accommodation of the laser ranging interferometer. This paper provides an overview of the challenging requirements levied on the observatory, and the mission and spacecraft design necessary to meet them. As the original Gravity Recovery and Climate Experiment spacecraft design has not been, to date, broadly discussed in the engineering literature, this paper further highlights original design rationales, where still applicable. As future satellite-based geodesy missions with similar constraints and challenges emerge, the implementation of the Gravity Recovery and Climate Experiment Follow-On observatory described herein can serve as a pathfinder and guide for the successful realization of these endeavors. © 2019 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Interferometers

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Preliminary verification and validation test suite for the CFD component of supersonic parachute deployment FSI simulations

Preliminary verification and validation test suite for the C...

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AIAA Aerospace Sciences Meeting, 2018

作者： Rabinovitch, Jason Huang, Daniel Z. Avery, Philip Farhat, Charbel Derkevorkian, Armen Peterson, Lee D. Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States Stanford University StanfordCA94305 United States Entry Descent and Landing and Formulation Group 4800 Oak Grove Drive M/S T1708-112 United States Institute for Computational and Mathematical Engineering United States Department of Aeronautics and Astronautics William F. Durand Building Room 028A United States Department of Aeronautics and Astronautics Department of Mechanical Engineering Institute for Computational and Mathematical Engineering William F. Durand Building Room 257 United States Dynamics Environments Group 4800 Oak Grove Drive M/S 157-410 United States Mechanical Systems Engineering Fabrication and Test Division 4800 Oak Grove Drive M/S 125-224 United States

ISBN: (纸本)9781624105241

Motivated by recent parachute anomalies during NASA’s recent Low-Density Supersonic Decelerator Project, the Jet Propulsion Laboratory, California Institute of Technology, and Stanford University have initiated a research collaboration with the goal of advancing the state-of-the-art for modeling supersonic parachute deployments. This paper serves as a status update of the project, specifically focusing on validation and verification efforts for the CFD component. © 2018, AIAA Aerospace Sciences Meeting. All rights reserved.

关键词： Parachutes

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Model verification and validation assessment for the simulation of supersonic parachute infl during martian entry

Model verification and validation assessment for the simulat...

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AIAA Aerospace Sciences Meeting, 2018

作者： Peterson, Lee D. Derkevorkian, Armen Rabinovitch, Jason Farhat, Charbel Avery, Philip Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States Stanford University StanfordCA94305 United States Mechanical Systems Engineering Fabrication and Test Division 4800 Oak Grove Dr PasadenaCA91109 United States Dynamics Environments Group 4800 Oak Grove Drive M/S 157-410 United States Entry Descent and Landing and Formulation Group 4800 Oak Grove Drive M/S T1708-112 United States Department of Aeronautics and Astronautics Department of Mechanical Engineering Institute for Computational and Mathematical Engineering William F. Durand Building Room 257 United States Department of Aeronautics and Astronautics William F. Durand Building Room 028A United States

ISBN: (纸本)9781624105241

This paper reports a model verification and validation assessment to support the development and application of a new supersonic parachute inflation simulation capability. The new capability is under development by the Farhat Research Group at Stanford University in a collaboration with the NASA Jet Propulsion Laboratory. The objective of the new simulation capability is to enable the physics based modeling of the inflation of a parachute decelerator in supersonic flow during entry into the Martian atmosphere. The reported model verification and validation assessment was undertaken to identify key gaps in the modeling capability of the software, to select verification tests of the software, and to anticipate validation tests for the modeled phenomena. A phenomena identification and ranking table (PIRT) of the simulation was developed to support this gap analysis. The results of this assessment have been incorporated into the software development plan, and into model verification and validation test suites reported in companion papers. This paper presents the development of the PIRT and discusses the results of the assessment. © 2018, AIAA Aerospace Sciences Meeting. All rights reserved.

关键词： Parachutes

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Control strategy and methods for continuous direct compression processes

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Asian Journal of Pharmaceutical Sciences 2021年第2期16卷 253-262页

作者： Yasuhiro Suzuki Hirokazu Sugiyama Manabu Kano Ryutaro Shimono Gosuke Shimada Ryoichi Furukawa Eichi Mano Keiichi Motoyama Tatsuo Koide Yasuhiro Matsui Kazuki Kurasaki Issei Takayama Shunin Hikage Noriko Katori Masahiko Kikuchi Hiroshi Sakai Yoshihiro Matsuda Formulation Technology Research Laboratories Daiichi Sankyo Co.Ltd.Kanagawa 254-0014Japan Department of Chemical System Engineering The University of TokyoTokyo 113-8656Japan Department of Systems Science Kyoto UniversityKyoto 606-8501Japan CMC Sciences Department Regulatory Affairs DivisionR&D DivisionJanssen Pharmaceutical K.K.Tokyo 101-0065Japan EuroTechno Ltd. Kanagawa 223-0057Japan Pharmaceutical Research Department Mitsubishi Tanabe Pharma CorporationOsaka 532-8505Japan Chemical Products CMC Regulatory Affairs Area Japan DevelopmentMSD K.K.Tokyo 102-8667Japan Graduate School of Pharmaceutical Sciences Kumamoto UniversityKumamoto 862-0973Japan Division of Drugs National Institute of Health SciencesKawasaki 210-9501Japan Technology Research&Development Sumitomo Dainippon Pharma Co.Ltd.Osaka 564-0053Japan Formulation Development Department Chugai pharmaceutical Co.Ltd.Tokyo 115-8543Japan Office of New Drug IV Pharmaceuticals and Medical Devices AgencyShin-Kasumigaseki Bldg.Tokyo 100-0013Japan Office of Generic Drugs Pharmaceuticals and Medical Devices AgencyShin-Kasumigaseki Bldg.Tokyo 100-0013Japan KOKANDO Co. Ltd.Toyama 930-8580Japan Pharmaceuticals and Medical Devices Agency Shin-Kasumigaseki Bldg.Tokyo 100-0013Japan

We presented a control strategy for tablet manufacturing processes based on continuous direct *** work was conducted by the experts of pharmaceutical companies,machine suppliers,academia,and regulatory authority in *** different items in the process,the component ratio and blended powder content were selected as the items requiring the control method specific to continuous manufacturing different from the conventional batch *** control and management of the Loss in Weight(LIW)feeder were deemed the most important,and the Residence Time Distribution(RTD)model were regarded effective for setting the control range and for controlling of the LIW *** on these ideas,the concept of process control using RTD was summarized.

关键词： Continuous manufacturing Solid drug products Process control Residence time distribution Loss in weight feeder Regulatory science

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Building ships as a system: An approach to total ship integration

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NAVAL ENGINEERS JOURNAL 1997年第5期109卷 47-60页

作者： Duren, BG Pollard, JR Bernard G. Duren:is an operations research analyst in the Combat Systems Department of the. Naval Surface Warfare Center Dahlgren Division. Mr. Duren received an A.B. degree in mathematics from Indiana University and an M.S. degree in operations research from the Georgia Institute of Technology. His major duties involve development of system concepts and system engineering methodology. His primary areas of achievement include startup of a strategic planning process at the Dahlgren Division analysis of seaskimmer defense issues and formulation of concepts for counter-command warfare. His areas of interest include information integration group problem solving methods warfare analysis and strategic planning. Mr. Duren is currently conducting studies in design of future shipboard combat systems. James R. Pollard:serves as principal systems engineer in the Combat Systems Department of the Naval Surface Warfare Center Dahlgren Division. Dr. Pollard received a B.S. degree in physics from Roanoke College an M.S. degree in electrical engineering from The George Washington University and a Ph.D. in systems engineering from the University of Virginia. After joining the Dahlgren Division in 1962 he performed research in antennas and electromagnetic coupling. He subsequently managed the Special Effects Weapon Research Program which focused on high power electromagnetic devices. After serving as head of the Weapon Systems Division and the Search and Track Division he formed the Strategic Planning Group. In 1985 he received the Bernard Smith Award for creative development and implementation of a strategic planning process for the Division. From 1985 to 1987 he served as warfare systems architect in the Space and Naval Warfare Systems Command. Dr. Pollard is currently conducting studies in design of future shipboard combat systems.

This paper considers an effort to reinvent the process by which the Navy transforms operational requirements into warships. The objective is to articulate a framework and strategy for implementing a total ship system engineering approach. Three factors drive the effort: involve the warfighters in the design process;adopt a ''system of systems'' framework for integration;and continually improve the acquisition process. The strategy is illustrated by consideration of control structure on a total ship basis. The work has been conducted as a collaborative effort involving three Navy warfare centers and various headquarters activities in Washington, D.C.

关键词： Shipbuilding

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Evaluation of an advanced suite of numerical codes for structural simulation of parachute fabric

Evaluation of an advanced suite of numerical codes for struc...

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AIAA Aerospace Sciences Meeting, 2018

作者： Derkevorkian, Armen Rabinovitch, Jason Peterson, Lee D. Avery, Philip Farhat, Charbel Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States Stanford University StanfordCA94305 United States Dynamics Environments Group 4800 Oak Grove Drive M/S 157-410 United States Entry Descent and Landing and Formulation Group 4800 Oak Grove Drive M/S T1708-112 United States Mechanical Systems Engineering Fabrication and Test Division 4800 Oak Grove Drive M/S 125-224 United States Department of Aeronautics and Astronautics William F. Durand Building Room 028A United States Department of Aeronautics and Astronautics Department of Mechanical Engineering Institute for Computational and Mathematical Engineering William F. Durand Building Room 257 United States

ISBN: (纸本)9781624105241

Parachutes are increasingly used to land space structures on Earth and other planets (e.g., Mars). Supersonic parachute deployment is a challenging fluid structure interaction (FSI) problem, and its physics-based computational simulation is a daunting task. A research collaboration between the Farhat Research Group (FRG) at Stanford University and the Jet Propulsion Laboratory (JPL) at the California Institute of Technology (Caltech) intends to assess the viability of a sophisticated suite of multi-physics codes, namely, the AERO Suite developed by FRG, and to enhance it further so that it can be exploited for simulating supersonic parachute deployment. This Suite features unique capabilities for the simulation of highly nonlinear FSI problems that have been verified and validated for related nonlinear aeroelasticity problems, and for underwater explosion and implosion problems. As part of the effort, a suite of purely structural mechanics and structural dynamics test problems (VERTS) relevant to parachute behavior has been developed for verifying AERO-S, the structural analyzer component of this software Suite. This paper summarizes the findings from the application of this verification test suite to AERO-S. Specifically, the study correlates the AERO-S VERTS results with analytical solutions (when available), results from other finite-element codes, and results reported in the literature. The reported VERTS results intend to highlight the existing capabilities of AERO-S and identify potential technology gaps to be incorporated into AERO-S during this collaborative effort. © 2018, AIAA Aerospace Sciences Meeting. All rights reserved.

关键词： Structural dynamics

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V&V of Fault Management: Challenges and Successes

V&V of Fault Management: Challenges and Successes

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AIAA Infotech at Aerospace (I at A) Conference

作者： Fesq, Lorraine M. Costello, Ken Ohi, Don Lu, Tiffany Newhouse, Marilyn Jet Propulsion Laboratory California Institute of Technology Systems Engineering and Formulation Division 4800 Oak Grove Drive Pasadena CA 91109 United States NASA Independent Verification and Validation Facility SMA Support Office 100 University Avenue Fairmont WV 26554 United States NASA Independent Verification and Validation Facility IV and V Office 100 University Avenue Fairmont WV 26554 United States Federal Civil Business Unit TASC El Segundo CA 90245 United States CSC NASA Marshall Space flight Center MSFC/EO50 Huntsville AL 35812 United States

This paper describes the results of a special breakout session of the NASA Independent Verification and Validation (IV&V) Workshop held in the fall of 2012 entitled "V&V of Fault Management: Challenges and Successes." The NASA IV&V Program is in a unique position to interact with projects across all of the NASA development domains. Using this unique opportunity, the IV&V program convened a breakout session to enable IV&V teams to share their challenges and successes with respect to the V&V of Fault Management (FM) architectures and software. The presentations and discussions provided practical examples of pitfalls encountered while performing V&V of FM including the lack of consistent designs for implementing faults monitors and the fact that FM information is not centralized but scattered among many diverse project artifacts. The discussions also solidified the need for an early commitment to developing FM in parallel with the spacecraft systems as well as clearly defining FM terminology within a project.

关键词： NASA

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Simulation of parachute inflation dynamics using an eulerian computational framework for evolving fluid-structure interfaces in high speed turbulent flows

Simulation of parachute inflation dynamics using an eulerian...

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AIAA Aerospace Sciences Meeting, 2018

作者： Huang, Daniel Z. Farhat, Charbel Avery, Philip Rabinovitch, Jason Derkevorkian, Armen Peterson, Lee D. Stanford University StanfordCA94305 United States US Army Research Laboratory AdelphiMD United States Jet Propulsion Laboratory California Institute of Technology PasadenaCA91109 United States Institute for Computational and Mathematical Engineering Stanford University Durand Building Room 226 StanfordCA94305-3035 United States Vivian Church Hoff Professor of Aircraft Structures Department of Aeronautics and Astronautics Stanford University Durand Building Room 257 StanfordCA94305-3035 United States Department of Aeronautics and Astronautics Stanford University Durand Building Room 214 StanfordCA94305-3035 United States Entry Descent Landing and Formulation Group 4800 Oak Grove Drive M/S T1708-112 United States Dynamics Environments Group 4800 Oak Grove Drive M/S 157-410 United States Mechanical Systems Engineering Fabrication and Test Division 4800 Oak Grove Drive M/S 125-224 United States

ISBN: (纸本)9781624105241

A high fidelity multiphase computational framework is presented for the simulation of parachute inflation in supersonic turbulent flows. Unlike previous investigations in this area, the framework considers the effect of the initial folded state of the parachute, flow compressibility in the porous fabric material, and the interactions between the fluid and the suspension lines. This framework is applied to a set of quasi-2D preliminary parachute inflation simulations. The results show (a) the loss of drag performance in supersonic regimes is due to the shock suspension line interactions, and (b) the maximum stress in the parachute canopy differs significantly when starting from an initial folded configuration and a flat (post-inflated) configuration. © 2018, AIAA Aerospace Sciences Meeting. All rights reserved.

关键词： Parachutes

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