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  • Other Sources  (208)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (208)
  • 2015-2019
  • 1980-1984  (208)
  • 1940-1944
  • 1
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    Hardware verification of distributed/adaptive control (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Adaptive control techniques are studied for their future application to the control of large space structures, where uncertain or changing parameters may destabilize standard control system designs. The approach used is to examine an extended Kalman filter estimator, in which the state vector is augmented with the unknown parameters. The associated Riccatti equation is linearized about the case of exact knowledge of the parameters. By assuming that parameter variations occur slowly, the filter complexity is reduced further yet. Simulations on a two degree-of-freedom oscillator demonstrate the parameter-tracking capability of the filter, and an implementation on the JPL Flexible Beam Facility using an incorrect model shows the adaptive filter/optimal control to be stable where a standard Kalman filter/optimal control design is unstable.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Proc. of the Workshop on Appl. of Distributed System Theory to the Control of Large Space Struct.; p 337-350
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Experimental demonstration of static shape control (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 03, p. 344, Accession no. A82-13998
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0731-5090)
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    NASA TECHNICAL REPORTS
  • 3
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    Experimental demonstration of the control of flexible structures (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The Large Space Structure Technology Flexible Beam Experiment employs a pinned-free flexible beam to demonstrate such required methods as dynamic and adaptive control, as well as various control law design approaches and hardware requirements. An attempt is made to define the mechanization difficulties that may inhere in flexible structures. Attention is presently given to analytical work performed in support of the test facility's development, the final design's specifications, the control laws' synthesis, and experimental results obtained.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 7; 527-534
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    NASA TECHNICAL REPORTS
  • 4
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    Surface step induced gap heating in the Shuttle Thermal Protection System (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 5, p. 606, Accession no. A83-16533
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4560); 21; 156-161
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    NASA TECHNICAL REPORTS
  • 5
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    P78-2 satellite and payload responses to electron beam operations on March 30, 1979 (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The operating modes of the SC4-1 payload, the resultant charging of the spacecraft frame and sample materials on the spacecraft exterior and recorded transient pulses are reported. Arcing was detected by pulse monitors in several electron beam modes of operation. The ejection of a beam of 6 mA of 3 keV electrons caused three distinct payload failures and created a transient problem in the telemetry system. The exact time, nature, and cause of these failures was determined and component failure and why they failed was identified. Analytical and modeling techniques are used to examine possible spacecraft and payload responses to the electron beam ejection which might have contributed to the arcing and payload failures.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 509-559
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    NASA TECHNICAL REPORTS
  • 6
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    Air Revitalization System integration (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents a status review of Spacecraft Air Revitalization System (ARS) integration using regenerable techniques. The paper addresses concepts of integration of individual subsystems into an Air Revitalization System, as well as integration of components within subsystems. An ARS design is presented based on the Electrochemical Depolarized Carbon Dioxide Concentrator Subsystem, the Sabatier Carbon Dioxide Reduction Subsystem, the Static Feed Water Electrolysis Subsystem, a condensing Humidity Control Subsystem, and a Water Handling Subsystem to perform the functions of CO2 removal, CO2 reduction, O2 generation, humidity control and by-product water distribution, respectively. The paper also highlights the numerous advantages of this integration. Trace contaminant control and the nitrogen supply are not included in the ARS described in this paper.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 840959
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    NASA TECHNICAL REPORTS
  • 7
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    Interactive analysis of a large aperture Earth Observations Satellite (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A system level design and analysis has been conducted on an Earth Observation Satellite (EOS) system using the Interactive Design and Evaluation of Advanced Spacecraft (IDEAS) computer-aided design and analysis program. The IDEAS program consists of about 40 user-friendly technical modules and an interactive graphics display. The reflector support system and feed mast of the EOS spacecraft are constructed with a box-truss structural concept, a lattice configuration which can be packaged for delivery in a single Shuttle flight and deployed in orbit. The deployed spacecraft consists of a 120-m by 60-m parabolic reflector, a 120-m-long support structure, and a 30-m feed arc beam on the focal axis. The spacecraft was modeled for structural, thermal, and control systems analysis and structural elements were designed. On-orbit dynamic and thermal loading analyses were conducted and spacecraft weights were determined.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1556
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Orbiter/shuttle carrier aircraft separation: Wind tunnel, simulation, and flight test overview and results (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A summary of the approach and landing test phase of the space shuttle program is given from the orbiter/shuttle carrier aircraft separation point of view. The data and analyses used during the wind tunnel testing, simulation, and flight test phases in preparation for the orbiter approach and landing tests are reported.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-58223
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Mars Orbiter Study. Volume 2: Mission Design, Science Instrument Accommodation, Spacecraft Design (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Spacecraft system and subsystem designs were developed at the conceptual level to perform either of two Mars Orbiter Missions, a Climatology Mission and an Aeronomy Mission. The objectives of these missions are to obtain and return data to increase knowledge of Mars.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166429 , NAS 1.26:166429 , REPT-82(44)00361/F1886-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Analysis of gap heating due to stepped tiles in the shuttle thermal protection system (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Analytical methods used to investigate entry gap heating in the Shuttle orbiter thermal protection system are described. Analytical results are given for a fuselage lower-surface location and a wing lower-surface location. These are locations where excessive gap heating occurred on the first flight of the Shuttle. The results of a study to determine the effectiveness of a half-height ceramic fiber gap filler in preventing hot-gas flow in the tile gaps are also given.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-2209 , L-15636 , NAS 1.60:2209
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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