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  • 1
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    Planar High-Thrust and Low-Thrust Orbital Transfers from Earth to Europa (2004)
    Springer
    Details
    Publication Date: 2004-12-01
    Print ISSN: 0021-9142
    Electronic ISSN: 2195-0571
    Topics: Physics
    Published by Springer
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    PAPER CURRENT
  • 2
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    A Functional Simulator of Spacecraft Resources (1997)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: The SPAcecraft SIMulator (SPASIM) simulates the functions and resources of a spacecraft to quickly perform Phase A trade-off analyses and uncover any operational bottlenecks during any part of the mission. Failure modes and operational contingencies can be evaluated allowing optimization for a range of mission scenarios. The payloads and subsystems are simulated, using a hierarchy of graphical models, in terms of how their functions affect resources such as propellant, power, and data. Any of the inputs and outputs of the payloads and subsystems can be plotted during the simulation. Most trade-off analyses, including those that compare current versus advanced technology, can be performed by changing values in the parameter menus. However, when a component is replaced by one with a different functional architecture, its graphical model can also be modified or replaced by drawing from a component library. SPASIM has been validated using several spacecraft designs which were at least at the Critical Design Review level. The user and programmer guide, including figures, is available on line as a hyper text document. This is an easy-to-use and expand tool which is based on MATLAB and SIMULINK. It runs on SGI workstations and PCs under Windows 95 or NT.
    Keywords: Cybernetics, Artificial Intelligence and Robotics
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    International Space Station (ISS) Accommodation of a Single US Assured Crew Return Vehicle (ACRV) (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The following report was generated to give the International Space Station (ISS) Program some additional insight into the operations and issues associated with accommodating a single U.S. developed Assured Crew Return Vehicle (ACRV). During the generation of this report, changes in both the ISS and ACRV programs were factored into the analysis with the realization that most of the work performed will eventually need to be repeated once the two programs become more integrated. No significant issues associated with the ISS accommodating the ACRV were uncovered. Kinematic analysis of ACRV installation showed that there are viable methods of using Shuttle and Station robotic manipulators. Separation analysis demonstrated that the ACRV departure path clears the Station structure for all likely contingency scenarios. The payload bay packaging analysis identified trades that can be made between payload bay location, Shuttle Remote Manipulator System (SRMS) reach and eventual designs of de-orbit stages and docking adapters.
    Keywords: Launch Vehicles and Space Vehicles
    Type: NASA/TM-97-206272 , NAS 1.15:206272 , L-17683
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Restructured Freedom configuration characteristics (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In Jan. 1991, the LaRc SSFO performed an assessment of the configuration characteristics of the proposed pre-integrated Space Station Freedom (SSF) concept. Of particular concern was the relationship of solar array operation and orientation with respect to spacecraft controllability. For the man-tended configuration (MTC), it was determined that torque equilibrium attitude (TEA) seeking Control Moment Gyroscope (CMG) control laws could not always maintain attitude. The control problems occurred when the solar arrays were tracking the sun to produce full power while flying in an arrow or gravity gradient flight mode. The large solar array articulations that sometimes result from having the functions of the alpha and beta joints reversed on MTC induced large product of inertia changes that can invalidate the control system gains during an orbit. Several modified sun tracking techniques were evaluated with respect to producing a controllable configuration requiring no modifications to the CMG control algorithms. Another assessment involved the permanently manned configuration (PMC) which has a third asymmetric PV unit on one side of the transverse boom. Recommendations include constraining alpha rotations for MTC in the arrow and gravity gradient flight modes and perhaps developing new non-TEA seeking control laws. Recommendations for PMC include raising the operational altitude and moving to a symmetric configuration as soon as possible.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-104057 , NAS 1.15:104057
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Pre-integrated structures for Space Station Freedom (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An in-space construction (erectable) approach to assembling Freedom is planned but the increasing complexity of the station design along with a decrease in shuttle capability over the past several years has led to an assembly sequence that requires more resources (EVA, lift, volume) than the shuttle can provide given a fixed number of flights. One way to address these issues is to adopt a pre-integrated approach to assembling Freedom. A pre-integrated approach combines station primary structure and distributed systems into discrete sections that are assembled and checked out on the ground. The section is then launched as a single structural entity on the shuttle and attached to the orbiting station is then launched as a single structural entity on the shuttle and attached to the orbiting station with a minimum of EVA. The feasibility of a pre-integrated approach to assembling Freedon is discussed. The structural configuration, packaging, and shuttle integration of discrete pre-integrated elements for Freedom assembly are discussed. It is shown that the pre-integrated approach to assembly reduces EVA and increases shuttle margin with respect to mass, volume, and center of gravity limits when compared to the baseline Freedom assembly sequence.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-102780 , NAS 1.15:102780
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Space Station Freedom assembly and operation at a 51.6 degree inclination orbit (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This study examines the implications of assembling and operating Space Station Freedom at a 51.6 degree inclination orbit utilizing an enhanced lift Space Shuttle. Freedom assembly is currently baselined at a 220 nautical mile high, 28.5 degree inclination orbit. Some of the reasons for increasing the orbital inclination are (1) increased ground coverage for Earth observations, (2) greater accessibility from Russian and other international launch sites, and (3) increased number of Assured Crew Return Vehicle (ACRV) landing sites. Previous studies have looked at assembling Freedom at a higher inclination using both medium and heavy lift expendable launch vehicles (such as Shuttle-C and Energia). The study assumes that the shuttle is used exclusively for delivering the station to orbit and that it can gain additional payload capability from design changes such as a lighter external tank that somewhat offsets the performance decrease that occurs when the shuttle is launched to a 51.6 degree inclination orbit.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-107731 , NAS 1.15:107731
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Space Station Freedom contingency reboost and resupply strategies (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The objective of this study was to determine the requirements necessary to ensure a viable Space Station Freedom (SSF) in the event of a delay in the date of the first element launch, and/or in the event that the nominal assembly sequence is interrupted, perhaps due to a delay in the Space Shuttle Launch Schedule. Orbit lifetimes, reboost fuel requirements, and controllability requirements were calculated for each stage of the SSF assuming anywhere from a 6 to 24 month delay/interruption in the baseline SSF assembly sequence. These results were assessed in order to formulate strategies to assure SSF viability in the presence of assembly sequence delays and interruptions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-104169 , NAS 1.15:104169
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Orbiter utilization as an ACRV (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Assuming that a Shuttle Orbiter could be qualified to serve long duration missions attached to Space Station Freedom in the capacity as an Assured Crew Return Vehicle (ACRV), a study was conducted to identify and examine candidate attach locations. Baseline, modified hardware, and new hardware design configurations were considered. Dual simultaneous Orbiter docking accommodation were required. Resulting flight characteristics analyzed included torque equilibrium attitude (TEA), microgravity environment, attitude controllability, and reboost fuel requirements. The baseline Station could not accommodate two Orbiters. Modified hardware configurations analyzed had large TEA's. The utilization of an oblique docking mechanism best accommodated an Orbiter as an ACRV.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-102700 , NAS 1.15:102700
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Shuttle-C utilization for assembly of the rephased Freedom configuration (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The utilization of the Shuttle-C Heavy Lift Launch Vehicle (HLLV) to augment the Shuttle orbiter to deliver to earth orbit elements for assembly of a rephased definition of Space Station Freedom is assessed. A past history of previous HLLV studies performed with respect to Freedom launch and assembly is reviewed and conclusions extrapolated that are appropriate to consider for the new rephased Freedom definition. The rephased Freedom definition is explained, two utilization scenarios are developed and related assessments are provided for Shuttle-C utilization early in the assembly sequence or utilization later in theon-orbit build up phase.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-101658 , NAS 1.15:101658
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Satellite Systems Design/Simulation Environment: A Systems Approach to Pre-Phase A Design (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A toolset for the rapid development of small satellite systems has been created. The objective of this tool is to support the definition of spacecraft mission concepts to satisfy a given set of mission and instrument requirements. The objective of this report is to provide an introduction to understanding and using the SMALLSAT Model. SMALLSAT is a computer-aided Phase A design and technology evaluation tool for small satellites. SMALLSAT enables satellite designers, mission planners, and technology program managers to observe the likely consequences of their decisions in terms of satellite configuration, non-recurring and recurring cost, and mission life cycle costs and availability statistics. It was developed by Princeton Synergetic, Inc. and User Systems, Inc. as a revision of the previous TECHSAT Phase A design tool, which modeled medium-sized Earth observation satellites. Both TECHSAT and SMALLSAT were developed for NASA.
    Keywords: Communications and Radar
    Type: AIAA Paper 97-0231 , 34th AIAA Aerospace Sciences Meeting and Exhibit; Jan 06, 1997 - Jan 09, 1997; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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