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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE
  • 1985-1989  (36)
  • 1975-1979
  • 1985  (36)
  • 1
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    Shuttle electrical environment (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Part of an AFGL payload flown on the STS-4 mission consisted of experiments to measure in-situ electric fields, electron densities, and vehicle charging. During this flight some 11 hours of data were acquired ranging from 5 minute snapshots up to continuous half-orbits. These experiments are described and results presented for such vehicle induced events as a main engine burn, thruster firings and water dumps in addition to undisturbed periods. The main characteristic of all the vehicle induced events is shown to be an enhancement in the low frequency noise (less than 2 kHz), in both the electrostatic and electron irregularity (delta N/N) spectra. The non-event results indicate that the electrostatic broadband emissions show a white noise characteristic in the low frequency range up to 2 kHz at an amplitude of 10 db above the shuttle design specification limit, falling below that limit above 10 kHz. The vehicle potential remained within the range of -3 to +1 volt throughout the flight which exhibits normal behavior for a satellite in a low equatorial orbit.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Environ. Interactions Technol., 1983; p 43-70
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Navigation study for low-altitude Earth satellites (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This document describes several navigation studies for low-altitude Earth satellites. The use of Global Positioning System Navigation Package data for LANDSAT-5 orbit determination is evaluated. In addition, a navigation analysis for the proposed Tracking and Data Aquisition System is presented. This analysis, based on simulations employing one-way Doppler data, is used to determine the agreement between the Research and Development Goddard Trajectory Determination System and the Sequential Error Analysis Program results. Properties of several geopotential error models are studied and an exploratory study of orbit smoother process noise is presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-177855 , NAS 1.26:177855 , CSC/TM-85/6119
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Vehicle charging on STS-3 Mission (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the Vehicle Charging and Potential experiment on the STS-3 mission, a pulsed electron gun was used to eject known charges and currents from the Shuttle Orbiter, and the resulting perturbations of the surface charge and current densities were studied with appropriate instruments. An ejected current of 100 mA, if maintained for a time sufficiently long for equilibrium to be established, could change the vehicle potential by 50 V or more when the ambient plasma density was low. In general, the observed perturbations could be ordered qualitatively in terms of the plasma density and of the attitude of the shuttle relative to its orbital velocity vector.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Environ. Interactions. Technol., 1983; p 19-32
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Post flight analysis of NASA standard star trackers recovered from the solar maximum mission (1985)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The flight hardware returned after the Solar Maximum Mission Repair Mission was analyzed to determine the effects of 4 years in space. The NASA Standard Star Tracker would be a good candidate for such analysis because it is moderately complex and had a very elaborate calibration during the acceptance procedure. However, the recovery process extensively damaged the cathode of the image dissector detector making proper operation of the tracker and a comparison with preflight characteristics impossible. Otherwise, the tracker functioned nominally during testing.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Proceedings of the SMRM Degradation Study Workshop; p 207-210
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Failure detection and accommodation in structural dynamics systems using analytic redundancy (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The concept of analytic redundancy is extended to identify nonzero constant output failures in large spacecraft active control sensors and actuators, using a set of distributed sensors which do not nominally produce equivalent signals but are related through the structural dynamics of the system. The suboptimal technique uses a Sequential Probability Ratio Test on the residual sequence of a Kalman filter based on a modal structure model, to determine failure of a component based on an assumed failure hypothesis. The specific failure is identified and then the Kalman filter gains are reconfigured for the identified remaining working sensor set. Experimental data using an apparatus whose dynamics are representative of a large spacecraft show the nominal filter performance under failed and unfailed conditions.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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  • 6
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    Space station adaptabilty to tether applications (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: This paper examines the Space Station configuration, requirements, and operations, and considers its adaptability to accommodate each tether application. These include power and thrust generation, rendezvous and docking, science platforms, variable gravity, and satellite boost and deboost. It attempts to uncover incompatibilities, and suggests compromises which would be required to effectively utilize each specific application. The goal is to enhance the overall understanding of the adaptability of the Space Station to tether applications.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
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  • 7
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    System test and flight results from infrared astronomical satellite external thermal subsystem (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The Infrared Astronomical Satellite (IRAS) received its system level thermal testing in a solar simulator in September and October 1982 and was launched in January 1983. In order to reduce costs and meet a tight launch schedule, a system thermal test approach was employed which combined the goals of thermal design development tests, thermal balance tests, and thermal vacuum qualification tests. This approach relied heavily on the use of a computer-controlled automatic data handling and heater control system which reduced reliance on human monitoring of test data in comparison to past projects. The validity of this approach has been borne out by flight results. During the whole mission most temperatures were within the desired range and close to predictions. Included under the external thermal subsystem are room temperature electronics and radiatively cooled surfaces with temperatures below 100 and 200K.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 22; 166-169
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Automatic assembly of space stations (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A problem in the automatic assembly of space stations is the determination of guidance laws for the terminal rendezvous and docking of two structural components or modules. The problem involves the feedback control of both the relative attitude and translational motion of the modules. A suitable mathematical model based on rigid body dynamics was used. The basic requirements, physical constraints and difficulties associated with the control problem are discussed. An approach which bypasses some of the difficulties is proposed. A nonlinear guidance law satisfying the basic requirements is derived. The implementation requirements is discussed. The performance of the resulting feedback control system with rigid and flexible structural components is studied by computer simulation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Proc. of the Workshop on Identification and Control of Flexible Space Struct., Vol. 1; p 67-101
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Flexibility of space structures makes design shaky (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An evaluation is made of the development status of high stiffness space structures suitable for orbital construction or deployment of large diameter reflector antennas, with attention to the control system capabilities required by prospective space structure system types. The very low structural frequencies typical of very large, radio frequency antenna structures would be especially difficult for a control system to counteract. Vibration control difficulties extend across the frequency spectrum, even to optical and IR reflector systems. Current research and development efforts are characterized with respect to goals and prospects for success.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace America (ISSN 0740-722X); 23; 100-103
    Format: text
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  • 10
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    Orbit on demand - Will cost determine best design? (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Eleven design concepts for vertical (V) and horizontal (H) take-off launch-on-demand manned orbital vehicles are discussed. Attention is given to up to three stages, Mach numbers (sub-, 2, or 3), expendable boosters, drop tanks (DT), and storable (S) or cryogenic fuels. All the concepts feature lifting bodies with circular cross-section and most have a 7 ft diam, 15 ft long payload bay as well as a crew compartment. Expendable elements impose higher costs and in some cases reduce all-azimuth launch capabilities. Single-stage vehicles simplify the logistics whether in H or V configuration. A two-stage H vehicle offers launch offset for the desired orbital plane before firing the rocket engines after take-off and subsonic acceleration. A two-stage fully reusable V form has the second lowest weight of the vehicles studied and an all-azimuth launch capability. Better definition of the prospective mission requirements is needed before choosing among the alternatives.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace America (ISSN 0740-722X); 23; 50-53
    Format: text
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