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  • 1
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    Stretched lens array squarerigger (SLASR): A unique high-power solar array for exploration missions (2006)
    Elsevier
    Details
    Publication Date: 2006-07-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Evaluation and comparison of space solar power concepts (2003)
    Elsevier
    Details
    Publication Date: 2003-08-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    BOLAS: A Canadian-US Ionospheric Tether Mission (1997)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: Everyday, international broadcasters, ships, and aircraft use a naturally conducting atmospheric layer, the ionosphere, to reflect communications signals over the Earth's horizon. A better understanding of this layer, with its irregularities, instabilities, and dynamics, would improve communications transmission and reception. This atmospheric layer is also a lens that can distort signal transmissions from communications, navigation, and surveillance satellites. The ionosphere over Canada and other high latitude countries can carry large currents and is particularly dynamic, so that a scientific understanding of this layer is critical. The BOLAS (Bistatic Observations using Low Altitude Satellites) mission would characterize reflective and transmissive properties of the ionosphere by flying two satellites, each with identical HF receivers, dipole antennas, particle probes, and GPS receivers. The satellites would be connected by a non-conducting tether to maintain a 100 m separation, and would cartwheel in the orbit plane to spatially survey the ionosphere. The six-month mission would fly in a high inclination, 350 x 600 km orbit, and would be active during passes over the auroral region of Canada. This paper discusses the system requirements and architecture, spacecraft and operations concepts, and mission design, as well as team organization, international cooperation and the scientific and technological benefits that are expected.
    Keywords: Law, Political Science and Space Policy
    Type: The Sixth Alumni Conference of the International Space University; 73-88; NASA-CP-3355
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Orbiter-Towed Reboost for ISS (1998)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: Orbiter towing provides a backup reboost capability for the International Space Station (ISS). Results from recent studies are presented, showing performance, system configuration, mission operations, and programmatics. A proposed flight demonstration to mitigate risks is also discussed.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Tether Technology Interchange Meeting; 285-303; NASA/CP-1998-206900
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Small expendable deployer system measurement analysis (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The first on-orbit experiment of the Small Expendable Deployer System (SEDS) for tethered satellites will collect telemetry data for tether length, rate of deployment, and tether tension. The post-flight analysis will use this data to reconstruct the deployment history and determine dynamic characteristics such as tether shape and payload position. Linearized observability analysis has determined that these measurements are adequate to define states for a two-mass tether model, and two state estimators were written.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Alabama Univ., Research Reports: 1988 NASA(ASEE Summer Faculty Fellowship Program; 16 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Thermal Examination of an Orbiting Cryogenic Fuel Depot (2002)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: For many years NASA has been interested in the storage and transfer of cryogenic fuels in space. Lunar, L2 and other chemical propulsive space vehicle missions now have staged refueling needs that a fuel depot would satisfy. The depot considered is located in lower earth orbit. Many considerations must go into designing and building such a station. Multi-layer insulation systems, thermal shielding and low conductive structural supports are the principal means of protecting the system from excessive heat loss due to boiloff. This study focuses on the thermal losses associated with storing LH2 in a passively cooled fuel depot in a lower earth equatorial orbit. The corresponding examination looks at several configurations of the fuel depot. An analytical model has been developed to determine the thermal advantages and disadvantages of three different fuel depot configurations. Each of the systems consists of three Boeing rocket bodies arranged in various configurations. The first two configurations are gravity gradient stabilized while the third one is a spin-stabilized concept. Each concept was chosen for self-righting capabilities as well as the fuel settling capabilities, however the purpose of this paper is to prove which of the three concepts is the most efficient passively cooled system. The specific areas to be discussed are the heating time from the fusion temperature to the vaporization temperature and the amount of boiloff for a specific number of orbits. Each of the previous points is compared using various sun exposed surface areas of the tanks.
    Keywords: Propellants and Fuels
    Type: Twelfth Thermal and Fluids Analysis Workshop; NASA/CP-2002-211783
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The Magnetosphere Imager Mission Concept Definition Study (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For three decades, magnetospheric field and plasma measurements have been made by diverse instruments flown on spacecraft in many different orbits, widely separated in space and time, and under various solar and magnetospheric conditions. Scientists have used this information to piece together an intricate, yet incomplete view of the magnetosphere. A simultaneous global view, using various light wavelengths and energetic neutral atoms, could reveal exciting new data and help explain complex magnetospheric processes, thus providing us with a clear picture of this region of space. The George C. Marshall Space Flight Center (MSFC) is responsible for defining the Magnetosphere Imager mission which will study this region of space. A core instrument complement of three imagers (with the potential addition of one or more mission enhancing instrument) will fly in an elliptical polar Earth orbit with an apogee of 44,600 kilometers and a perigee of 4,800 km. This report will address the mission objectives, spacecraft design concepts, and the results of the MSFC concept definition study.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-RP-1401 , NAS 1.61:1401 , M-832
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Kalman estimation for SEDS measurements (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The first on-orbit experiment of the Small Expendable Deployer System (SEDS) for tethered satellites will collect telemetry data for tethered length, rate of deployment, and tether tension. The post-flight analysis will use this data to reconstruct the deployment history and determine payload position and tether shape. Two Kalman estimator algorithms were written, and output using simulated measurement data was compared. Both estimators exhibited the same estimated state histories, indicating that numerical instability in the traditional algorithm was not the cause of filter divergence. Estimation of acceleration biases was added, which reduced the error but did not correct the divergence. An add-a-bead estimator that adds lumped masses as the tether is deployed was written, which provides a state model that matches the BEADSIM simulation providing the true measurements and states. This twenty-one bead estimator produced state histories similar to those of the two-bead estimator, indicating that the filter divergence was not caused by a reduced-order model. The noise models used to date are relatively simple and may be the source of estimator divergence. The investigation of colored noise models, cross-correlated measurement and process covariances, and noise-adaptive filter techniques is recommended.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Alabama Univ., Research Reports: 1989 NASA(ASEE Summer Faculty Fellowship Program; 20 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Space Solar Power Concepts: Demonstrations to Pilot Plants (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The availability of abundant, affordable power where needed is a key to the future exploration and development of space as well as future sources of clean terrestrial power. One innovative approach to providing such power is the use of wireless power transmission (WPT). There are at least two possible WPT methods that appear feasible; microwave and laser. Microwave concepts have been generated, analyzed and demonstrated. Technologies required to provide an end-to-end system have been identified and roadmaps generated to guide technology development requirements. Recently, laser W T approaches have gained an increased interest. These approaches appear to be very promising and will possibly solve some of the major challenges that exist with the microwave option. Therefore, emphasis is currently being placed on the laser WPT activity. This paper will discuss the technology requirements, technology roadmaps and technology flight experiments demonstrations required to lead toward a pilot plant demonstration. Concepts will be discussed along with the modeling techniques that are used in developing them. Feasibility will be addressed along with the technology needs, issues and capabilities for particular concepts. Flight experiments and demonstrations will be identified that will pave the road from demonstrations to pilot plants and beyond.
    Keywords: Spacecraft Propulsion and Power
    Type: 53rd IAF; Oct 10, 2002 - Oct 19, 2002; Houston, TX; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    A Cryogenic Propellant Production Depot for Low Earth Orbit (2001)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: The cost of access to space beyond low Earth orbit can be lowered if vehicles can refuel in orbit. The power requirements for a propellant depot that electrolyzes water and stores cryogenic oxygen and hydrogen can be met using technology developed for space solar power. A propellant depot is described that will be deployed in a 400 km circular equatorial orbit, receive tanks of water launched into a lower orbit from Earth by gun launch or reusable launch vehicle, convert the water to liquid hydrogen and oxygen, and store up to 500 metric tonnes of cryogenic propellants. Orbital maneuvering vehicles will transfer the Earth-launched propellant tanks from the lower orbit to the depot orbit. The propellant stored in the depot can support transportation from low Earth orbit to geostationary Earth orbit, the Moon, LaGrange points, Mars, etc. The propellant tanks on the depot are modified versions of those used in the Delta IV-Heavy launch vehicle. The tanks are configured in an in-line gravity-gradient configuration to minimize drag and settle the propellant. Temperatures can be maintained by body-mounted radiators; these will also provide some shielding against orbital debris. Power is supplied by a pair of solar arrays mounted perpendicular to the orbital plane, which rotate once per orbit to track the Sun. The majority of the power will be used to run the electrolysis system. Technology needed for an orbiting propellant depot can be tested and demonstrated in the near-term on the ground, on a Shuttle-deployed free-flyer, and on the International Space Station. Further along, an orbital depot can be deployed that stores liquid hydrogen and oxygen launched from Earth, to be followed by a full conversion and storage depot.
    Keywords: Propellants and Fuels
    Type: International Space Development; May 24, 2001 - May 28, 2001; Albuquerque, NM; United States
    Format: text
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    NASA TECHNICAL REPORTS
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