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  • Other Sources  (94)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (94)
  • 1990-1994
  • 1980-1984  (94)
  • 1955-1959
  • 1984  (50)
  • 1983  (44)
  • 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)
    Format: text
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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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    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
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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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
  • 7
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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
  • 8
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    Thermal mathematical modeling and system simulation of Space Shuttle less subsystem (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Applications, validation tests, and upgrades of the two- and three-dimensional system level thermal mathematical system simulation models (TMSSM) used for thermal protection system (TPS) analyses are described. The TMSSM were developed as an aid to predicting the performance requirements and configurations of the Shuttle wing leading edge (WLE) and nose cone (NC) TPS tiles. The WLE and its structure were subjected to acoustic, thermal/vacuum, and air loads tests to simulate launch, on-orbit, and re-entry behavior. STS-1, -2 and -5 flight data led to recalibration of on-board instruments and raised estimates of the thermal shock at the NC and WLE. Baseline heating data are now available for the design of future TPS.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-1772
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Conceptual spacecraft systems design and synthesis (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An interactive systems design and synthesis is performed on future spacecraft concepts using the Interactive Design and Evaluation of Advanced Systems (IDEAS) computer-aided design and analysis system. The capabilities and advantages of the systems-oriented interactive computer-aided design and analysis system are described. The synthesis of both large antenna and space station concepts, and space station evolutionary growth designs is demonstrated. The IDEAS program provides the user with both an interactive graphics and an interactive computing capability which consists of over 40 multidisciplinary synthesis and analysis modules. Thus, the user can create, analyze, and conduct parametric studies and modify earth-orbiting spacecraft designs (space stations, large antennas or platforms, and technologically advanced spacecraft) at an interactive terminal with relative ease. The IDEAS approach is useful during the conceptual design phase of advanced space missions when a multiplicity of parameters and concepts must be analyzed and evaluated in a cost-effective and timely manner.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1622
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    NASA TECHNICAL REPORTS
  • 10
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    Operational awareness in future space transportation system concepts and technology selections (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An analysis of operations for a two-stage, fully reusable future space transportation system has been performed, and the results are discussed. The value of conducting an analysis of operations in the conceptual design phase to produce a highly productive system was demonstrated by obtaining estimated reductions in resources and ground turnaround time and comparing them with estimated mature Shuttle program requirements. Cooperative efforts by users, future vehicle designers, and operations analysts during the conceptual design phase are shown to produce an efficient vehicle design with broad market potential. The synergistic effects of vehicle design configuration, subsystems, and procedures can enhance productivity of the transportation system as measured by flexibility, availability, and viability. Advanced technologies and subsystems beneficial to such a system are identified.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AAS PAPER 83-382
    Format: text
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    NASA TECHNICAL REPORTS
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