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  • Other Sources  (10)
  • Spacecraft Design, Testing and Performance  (10)
  • 1
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    Mission Analysis for the Don Quijote Phase-A Study (2007)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The Don Quijote Phase-A study is a definition study funded by ESA and devoted to the analysis of the possibilities to deflect a Near Earth Object (NEO) in the range of 300-800 m diameter. DEIMOS Space S.L. and EADS Astrium have teamed up within this study to form one of the three consortia that have analyzed these aspects for ESA. Target asteroids for the mission are 1989 ML, 2002 AT4 and Apophis. This paper presents the mission analysis activities within the consortium providing: low-thrust interplanetary rendezvous Orbiter trajectories to the target asteroids, ballistic interplanetary trajectories for the Impactor, Orbiter arrival description at the asteroids, Orbiter stable orbits characterization at the asteroid, deflection determination by means of a Radio Science Experiment (RSE) as well as the mission timelines and overall mission scenarios.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Proceedings of the 20th International Symposium on Space Flight Dynamics; NASA/CP-2007-214158
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  • 2
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    BioSentinel - A 6U Nanosatellite for Deep Space Biological Science (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN34580 , Annual AIAA/USU Conference on Small Satellites; Logan, UT; United States
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  • 3
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    Starling1 - Mission Technologies Overview (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Starling series of demonstration missions will test technologies required to achieve affordable, distributed spacecraft ("swarm") missions that: are scalable to at least 100 spacecraft for applications that include synchronized multipoint measurements; involve closely coordinated ensembles of two or more spacecraft operating as a single unit for interferometric, synthetic aperture, or similar sensor architectures; or use autonomous or semi-autonomous operation of multiple spacecraft functioning as a unit to achieve science or other mission objectives with low-cost small spacecraft.Starling1 will focus on developing technologies that enable scalability and deep space application. The mission goals include the demonstration of a Mobile Ad-hoc NETwork (MANET) through an in-space communication experiment, vision based relative navigation through the Starling Formation-flying Optical eXperiment (StarFOX), and demonstration of autonomous spacecraft reconfiguration using technologies developed by the Distributed System Autonomy (DSA) project.
    Keywords: Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN59780 , Small Satellite Conference; Aug 04, 2018 - Aug 09, 2018; Logan, UT; United States
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  • 4
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    Technology of Bare Tether Current Collection (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The outstanding problem for useful applications of electrodynamic tethers is obtaining sufficient electron current from the ionospheric plasma. Bare tether collectors, in which the conducting tether itself, left uninsulated over kilometers of its length, acts as the collecting anode, promise to attain currents of 10 A or more from reasonably sized systems. Current collection by a bare tether is also relatively insensitive to drops in electron density, which are regularly encountered on each revolution of an orbit. This makes nighttime operation feasible. We show how the bare tether's high efficiency of current collection and ability to adjust to density variations follow from the orbital motion limited collection law of thin cylinders. We consider both upwardly deployed (power generation mode) and downwardly deployed (reboost mode) tethers, and present results that indicate how bare tether systems would perform as their magnetic and plasma environment varies in low earth orbit.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Tether Technology Interchange Meeting; 379-398; NASA/CP-1998-206900
    Format: text
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  • 5
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    Electrodynamic Tether Propulsion for Spacecraft and Upper Stages (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Relatively short electrodynamic tethers can use solar power to 'push' against a planetary magnetic field to achieve propulsion without the expenditure of propellant. The groundwork has been laid for this type of propulsion. Important recent milestones include retrieval of a tether in space (TSS-1, 1992), successful deployment of a 20-km-long tether in space (SEDS-1, 1993), and operation of an electrodynamic tether with tether current driven in both directions (PMG, 1993). The planned Propulsive Small Expendable Deployer System (ProSEDS) experiment will use the flight-proven Small Expendable Deployer System (SEDS) to deploy a 5 km bare copper tether from a Delta II upper stage to achieve approximately 0.4 N drag thrust, thus deorbiting the stage. The experiment will use a predominantly 'bare' tether for current collection in lieu of the endmass collector and insulated tether approach used on previous missions. The flight experiment is a precursor to utilization of the technology on the International Space Station for reboost and the electrodynamic tether upper stage demonstration mission which will be capable of orbit raising, lowering and inclination changes, all using electrodynamic thrust. In addition, the use of this type of propulsion may be attractive for future missions at Jupiter.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Propulsion; Jul 13, 1998 - Jul 16, 1998; Cleveland, OH; United States
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  • 6
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    International Space Station Payload Training Overview (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes payload crew training-related activities performed by NASA and the U.S. Payload Developer (PD) community for the International Space Station (ISS) Program. It describes how payloads will be trained and the overall training planning and integration process. The overall concept, definition, and template for payload training are described. The roles and responsibilities of individuals, organizations, and groups involved are discussed. The facilities utilized during payload training and the primary processes and activities performed to plan, develop, implement, and administer payload training for ISS crews are briefly described. Areas of improvement to crew training processes that have been achieved or are currently being worked are identified.
    Keywords: Spacecraft Design, Testing and Performance
    Type: AIAA Paper 2001-5121 , International Space Station Utilization 2001 Conference and Exhibit; Oct 15, 2001 - Oct 18, 2001; Cape Canaveral, FL.; United States
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  • 7
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    The Propulsive Small Expendable Deployer System Experiment (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Relatively short electrodynamic tethers can extract orbital energy to 'push' against a planetary magnetic field to achieve propulsion without the expenditure of propellant. The Propulsive Small Expendable Deployer System experiment will use the flight-proven Small Expendable Deployer System (SEDS) to deploy a 5 km bare copper tether from a Delta II upper stage to achieve approximately 0.4 N drag thrust, thus lowering the altitude of the stage. The experiment will use a predominantly 'bare' tether for current collection in lieu of the endmass collector and insulated tether approach used on previous missions. The flight experiment is a precursor to a more ambitious electrodynamic tether upper stage demonstration mission which will be capable of orbit raising, lowering and inclination changes - all using electrodynamic thrust. The expected performance of the tether propulsion system during the experiment is described.
    Keywords: Spacecraft Design, Testing and Performance
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  • 8
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    The EDSN Intersatellite Communications Architecture (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN17046 , Small Satellite Conference; Aug 02, 2014 - Aug 07, 2014; Logan, Ut.; United States
    Format: application/pdf
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  • 9
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    Electrodynamic Tethers for Spacecraft Propulsion (1998)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: Relatively short electrodynamic tethers can use solar power to 'push' against a planetary magnetic field to achieve propulsion without the expenditure of propellant. The groundwork has been laid for this type of propulsion. NASA began developing tether technology for space applications in the 1960's. Important recent milestones include retrieval of a tether in space (TSS-1, 1992), successful deployment of a 20-km-long tether in space (SEDS-1, 1993), and operation of an electrodynamic tether with tether current driven in both directions-power and thrust modes (PMG, 1993). The planned Propulsive Small Expendable Deployer System (ProSEDS) experiment will demonstrate electrodynamic tether thrust during its flight in early 2000. ProSEDS will use the flight-proven Small Expendable Deployer System (SEDS) to deploy a 5 km bare copper tether from a Delta II upper stage to achieve approximately 0.4 N drag thrust, thus deorbiting the stage. The experiment will use a predominantly 'bare' tether for current collection in lieu of the endmass collector and insulated tether approach used on previous missions. Theory and ground-based plasma chamber testing indicate that the bare tether is a highly-efficient current collector. The flight experiment is a precursor to utilization of the technology on the International Space Station for reboost application and the more ambitious electrodynamic tether upper stage demonstration mission which will be capable of orbit raising, lowering and inclination changes - all using electrodynamic thrust. In addition, the use of this type of propulsion may be attractive for future missions at Jupiter and any other planetary body with a magnetosphere.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Aerospace Sciences; Jan 12, 1998 - Jan 15, 1998; Reno, NV; United States
    Format: text
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  • 10
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    The Imaging X-Ray Polarimetry Explorer (IXPE): Technical Overview II (2019)
    In:  CASI
    Details
    Publication Date: 2019-09-17
    Description: The Imaging X-ray Polarimetry Explorer (IXPE) will add polarization to the properties (time, energy, and position) observed in x-ray astronomy. A NASA Astrophysics Small Explorer (SMEX) in partnership with the Italian Space Agency (ASI), IXPE will measure the 28-keV polarization of a few dozen sources during the first 2 years following its 2021 launch. The IXPE Observatory includes three identical x-ray telescopes, each comprising a 4-m-focal-length (grazingincidence) mirror module assembly (MMA) and a polarization-sensitive (imaging) detector unit (DU), separated by a deployable optical bench. The Observatorys Spacecraft provides typical subsystems (mechanical, structural, thermal, power, electrical, telecommunications, etc.), an attitude determination and control subsystem for 3-axis stabilized pointing, and a command and data handling subsystem communicating with the science instrument and the Spacecraft subsystems.
    Keywords: Spacecraft Design, Testing and Performance
    Type: MSFC-E-DAA-TN72945 , SPIE Optical Engineering + Applications; Aug 11, 2019 - Aug 15, 2019; San Diego, CA; United States|Proceedings of SPIE (ISSN 0277-786X) (e-ISSN 1996-756X); 11118; 111180V
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