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  • 1
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    Mariner 4 maneuver and attitude control (1969)
    In:  CASI
    Details
    Publication Date: 2006-06-28
    Keywords: unknown
    Type: MARINER 4 MISSION TO MARS, PT. 2 15 DEC. 1965; P 36-39
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Attitude control of nonrigid spacecraft (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Flexible spacecraft attitude control and classification systems based on mathematical models
    Keywords: SPACE VEHICLES
    Type: ; TROPHYSICAL JOURNAL
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The Mariner-IV attitude control system. (1965)
    In:  Other Sources
    Details
    Publication Date: 2011-08-11
    Description: Three-axis control system of Mariner IV for midcourse maneuver, communication, scientific instruments orientation, etc
    Keywords: SPACE VEHICLES
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Mariner 4 maneuver and attitude control. (1965)
    In:  Other Sources
    Details
    Publication Date: 2011-08-11
    Description: Mariner IV maneuver and attitude control using Sun and star Canopus for reference frame
    Keywords: SPACE VEHICLES
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Management of the Galileo attitude and articulation control flight software development (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Management concepts are presented for software development for a new technology area, i.e., real-time autonomous, computer-based spacecraft control. Flight computer selection and sizing are done initially to maximize performance within constraints of size, power, and cost. A higher order language is chosen to enhance productivity. Because the computer is embedded in the control systems hardware and is tied to the iterative design process of the spacecraft, the management and configuration control of the software is different from more typical applications. The development process must permit early coding but accept late changes. Margin management must be a continuing process in the development. Validation and verification is a special problem because it is not feasible to test the software in the actual operating environment prior to launch.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: AIAA PAPER 81-2127 , In: Computers in Aerospace Conference; Oct 26, 1981 - Oct 28, 1981; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Three-axis attitude control for solar-powered electric propulsion spacecraft (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Spacecraft utilizing solar electric propulsion (SEP) for certain long-term interplanetary missions will depend on large, flexible solar arrays. The resulting spacecraft configurations present some complex flight control problems. Questions regarding a general design approach are discussed along with options for three-axis control forces, tradeoffs for three-axis control forces, controllers for SEP attitude control, sensors for SEP attitude control, aspects of nonrigid vehicle interaction with attitude control, thrust vector control SEP dynamics, and mass expulsion control SEP dynamics. It is found that the state-of-the-art of control system design is mature enough to support an SEP project.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 740874 , Society of Automotive Engineers, National Aerospace Engineering and Manufacturing Meeting; Oct 01, 1974 - Oct 03, 1974; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
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