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  • 1
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    Therapeutic targeting of constitutive PARP activation compromises stem cell phenotype and survival of glioblastoma-initiating cells (2013)
    Springer Nature
    Details
    Publication Date: 2013-10-11
    Print ISSN: 1350-9047
    Electronic ISSN: 1476-5403
    Topics: Biology , Medicine
    Published by Springer Nature
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    PAPER CURRENT
  • 2
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    MAX: A space station computer option (1985)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Information on Max, a space station computer option, is given in viewgraph form. The computer option is characterized by embedded, real-time applications; synchronous, cyclic operation and asynchronous, event driven operation; computationally intensive and data intensive processing; a wide range of throughput and memory requirements; a range of fault tolerant requirements from none to full; and maintainability, including capability for on-line substitution in critical systems.
    Keywords: COMPUTER OPERATIONS AND HARDWARE
    Type: NASA, Washington, Proceedings: Computer Science and Data Systems Technical Symposium, Volume 2; 12 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Attitude and articulation control for CRAF/Cassini (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The Comet Rendezvous/Asteroid Flyby (CRAF) and Cassini planetary missions provide exciting pointing and control challenges. The mission and science objectives, and an attitude and articulation control concept designed to meet these challenges, are described. CRAF/Cassini mission characteristics which drive pointing and control include: close range flybys of asteroids and icy satellites; Huygens probe guidance and communication; Saturn orbit insertion; comet rendezvous and orbit insertion; closed loop target tracking from a comet orbit perturbed by gas and dust pressure; fine spacecraft pointing for Titan radar mapping and Earth communications; requirements for autonomous failure detection; isolation; recovery; and 13.5 year lifetime. The philosophy and approach chosen to meet these challenges and the overall control architecture are addressed, including operational and autonomous safe modes. Critical functions are highlighted, such as charge coupled device imaging of stars and extended bodies which provide references for inertial and target referenced pointing respectively. Tradeoffs and rationale for the selection and location of sensors and actuators are reviewed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ESA, Spacecraft Guidance, Navigation and Control Systems; p 23-32
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    State knowledge representation in the mission data system (2002)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: This paper describes the MDS approach to state knowledge representation, contrasting it with past efforts, and offering motivation for the approach as a general recipe for similar efforts.
    Type: 2002 IEEE Aerospace Conference; Big Sky, MT; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Modeling relationships using graph state variables (2002)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: This paper shows example GSV representations for spacecraft orientation, location, trajectories, dynamics, and kinematics.
    Keywords: Astrodynamics
    Type: 2002 IEEE Aerospace Conference; Big Sky, MT; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Goal based fault tolerance for space systems using the mission data system (2000)
    In:  Other Sources
    Details
    Publication Date: 2018-06-08
    Description: This paper describes the MDS approach to fault tolerance, contrasting it with past efforts, and offering motivation for the approach as a general recipe for similar efforts.
    Type: 2001 IEEE Conference; Big Sky, MT; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Attitude and articulation control system testing for Project Galileo (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A type of facility required to integrate and test a complex autonomous spacecraft subsystem is presented, using the attitude and articulation control subsystem (AACS) of Project Galileo as an example. The equipment created for testing the AACS at both the subsystem and spacecraft system levels is described, including a description of the support equipment (SE) architecture in its two main configurations, closed loop simulation techniques, the user interface to the SE, and plans for the use of the facility beyond the test period. This system is capable of providing a flight-like functional environment through the use of accurate real-time models and carefully chosen points of interaction, and flexible control capability and high visibility to the test operator.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: AAS PAPER 81-033 , Annual Rocky Mountain Guidance and Control Conference; Jan 31, 1981 - Feb 04, 1981; Keystone, CO
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Computing in the presence of soft bit errors (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: It is shown that single-event-upsets (SEUs) due to cosmic rays are a significant source of single bit error in spacecraft computers. The physical mechanism of SEU, electron hole generation by means of Linear Energy Transfer (LET), it discussed with reference made to the results of a study of the environmental effects on computer systems of the Galileo spacecraft. Techniques for making software more tolerant of cosmic ray effects are considered, including: reducing the number of registers used by the software; continuity testing of variables; redundant execution of major procedures for error detection; and encoding state variables to detect single-bit changes. Attention is also given to design modifications which may reduce the cosmic ray exposure of on-board hardware. These modifications include: shielding components operating in LEO; removing low-power Schottky parts; and the use of CMOS diodes. The SEU parameters of different electronic components are listed in a table.
    Keywords: SPACECRAFT INSTRUMENTATION
    Type: 1984 American Control Conference; Jun 06, 1984 - Jun 08, 1984; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A Voyager attitude control perspective on fault tolerant systems (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In current spacecraft design, a trend can be observed to achieve greater fault tolerance through the application of on-board software dedicated to detecting and isolating failures. Whether fault tolerance through software can meet the desired objectives depends on very careful consideration and control of the system in which the software is imbedded. The considered investigation has the objective to provide some of the insight needed for the required analysis of the system. A description is given of the techniques which have been developed in this connection during the development of the Voyager spacecraft. The Voyager Galileo Attitude and Articulation Control Subsystem (AACS) fault tolerant design is discussed to emphasize basic lessons learned from this experience. The central driver of hardware redundancy implementation on Voyager was known as the 'single point failure criterion'.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-1812 , Guidance and Control Conference; Aug 19, 1981 - Aug 21, 1981; Albuquerque, NM
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Attitude and articulation control solutions for Project Galileo (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Design problems and the solutions adopted for them in the attitude and articulation control subsystem for the Galileo spacecraft are discussed as an illustration of the application of dual-spin control to an interplanetary spacecraft. Following a review of the baseline design of the Galileo system and mission, consideration is given to problems encountered in the areas of autonomous attitude determination, attitude control, spacecraft dynamics and software margins. Design issues raised by subsequent changes in spacecraft configuration are also indicated. It is pointed out that although difficulties associated with control system complexity in a dual-spin interplanetary spacecraft have been satisfactorily resolved for the Galileo mission, the future application of dual spin in interplanetary flight is in doubt.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS 80-019 , Annual Rocky Mountain Conference; Feb 17, 1980 - Feb 21, 1980; Keystone, CO
    Format: text
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    NASA TECHNICAL REPORTS
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