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  • 1
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    Visualizing fast electron energy transport into laser-compressed high-density fast-ignition targets (2016)
    Springer Nature
    Details
    Publication Date: 2016-05-04
    Description: Nature Physics 12, 499 (2016). doi:10.1038/nphys3614 Authors: L. C. Jarrott, M. S. Wei, C. McGuffey, A. A. Solodov, W. Theobald, B. Qiao, C. Stoeckl, R. Betti, H. Chen, J. Delettrez, T. Döppner, E. M. Giraldez, V. Y. Glebov, H. Habara, T. Iwawaki, M. H. Key, R. W. Luo, F. J. Marshall, H. S. McLean, C. Mileham, P. K. Patel, J. J. Santos, H. Sawada, R. B. Stephens, T. Yabuuchi & F. N. Beg
    Print ISSN: 1745-2473
    Electronic ISSN: 1745-2481
    Topics: Physics
    Published by Springer Nature
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    PAPER CURRENT
  • 2
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    Attitude control study for a large flexible spacecraft using a Solar Electric Propulsion System (SEPS) (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The attitude control performance of the solar electric propulsion system (SEPS) was evaluated. A thrust vector control system for powered flight control was examined along with a gas jet reaction control system, and a reaction wheel system, both of which have been proposed for nonpowered flight control. Comprehensive computer simulations of each control system were made and evaluated using a 30 mode spacecraft model. Results obtained indicate that thrust vector control and reaction wheel systems offer acceptable smooth proportional control. The gas jet control system is shown to be risky for a flexible structure such as SEPS, and is therefore, not recommended as a primary control method.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-162878 , JPL-PUB-80-14
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Spacecraft drag-free technology development: On-board estimation and control synthesis (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Estimation and control methods for a Drag-Free spacecraft are discussed. The functional and analytical synthesis of on-board estimators and controllers for an integrated attitude and translation control system is represented. The framework for detail definition and design of the baseline drag-free system is created. The techniques for solution of self-gravity and electrostatic charging problems are applicable generally, as is the control system development.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-169141 , JPL-Pub-82-45 , NAS 1.26:169141
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    NASA Space controls research and technology program (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: The NASA technological organization is outlined. The Office of Aeronautics and Space Technology (OAST) is one of the four major technical offices that comprise NASA. The Office of Space Science and Applications administers programs directed towards using space-based or related techniques to further understanding of the total universe and to apply that understanding to practical applications in such areas as Astrophysics, Solar System exploration, Earth Sciences, Life Sciences, Communications and Information Systems. The Office of Space Flight administers the programs for all U.S. civil launch capability, plus Spacelab development and operations. The Office of Space Tracking & Data Systems administers the programs that operate and maintain a world-wide network of facilities for data acquisition, processing, and ground to spacecraft communications for all NASA missions. The OAST has primary responsibility within NASA for conducting space research and technology development to support commercial and military as well as NASA space interests.
    Keywords: ADMINISTRATION AND MANAGEMENT
    Type: JPL Proc. of the Workshop on Identification and Control of Flexible Space Struct., Vol. 1; p 1-11
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    A spacecraft attitude and articulation control system design for the Comet Halley intercept mission (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An attitude and articulation control system design for the Comet Halley 1986 intercept mission is presented. A spacecraft dynamics model consisting of five hinge-connected rigid bodies is used to analyze the spacecraft attitude and articulation control system performance. Inertial and optical information are combined to generate scan platform pointing commands. The comprehensive spacecraft model has been developed into a digital computer simulation program, which provides performance characteristics and insight pertaining to the control and dynamics of a Halley Intercept spacecraft. It is shown that scan platform pointing error has a maximum value of 1.8 milliradians during the four minute closest approach interval. It is also shown that the jitter or scan platform pointing rate error would have a maximum value of 2.5 milliradians/second for the nominal 1000 km closest approach distance trajectory and associated environment model.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 81-193 , Astrodynamics Specialist Conference; Aug 03, 1981 - Aug 05, 1981; Lake Tahoe, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
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