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  • Other Sources  (227)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (227)
  • 2010-2014
  • 1980-1984  (227)
  • 2014
  • 1983  (227)
  • 1
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    Active control technology development at NASA (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: It is noted that the large space systems deployable by means of the Space Shuttle will have increased flexibility, and therefore unprecedented interaction between control and other subsystems. Open loop performance in such systems would be grossly inadequate, prompting active control method development to achieve the required performance levels. The structures in question encompass those of projected science and communications platforms, interplanetary space transportation systems, and manned permanent space stations.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Deployable optical systems; january 18, 19, 1983; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The US space station: Potential base for a spaceborne microwave facility (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: Concepts for a U.S. space station were studied to achieve the full potential of the Space Shuttle and to provide a more permanent presence in space. The space station study is summarized in the following questions: Given a space station in orbit in the 1990's, how should it best be used to achieve science and applications objectives important at that time? To achieve those objectives, of what elements should the station be comprised and how should the elements be configured and equipped. These questions are addressed.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: JPL Spaceborne Imaging Radar Symp.; p 144-156
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Stochastic analysis of the control of the movement of the spacecraft in the vicinity of the colinear libration point by means of the forces of luminous pressure (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: This paper is dedicated to the possible investigation of the utilization of the solar radiation pressure for the spacecraft motion control in the vicinity of collinear libration point of planar restricted ring problem of three bodies. The control is realized by changing the solar sail area at its permanent orientation. In this problem the influence of the trajectory errors and the errors of the execution control is accounted. It is worked out, the estimation method of the solar sail sizes, which are necessary for spacecraft keeping in the vicinity of collinear libration point during the certain time with given probability. The main control parameters were calculated for some examples in case of libration points of the Sun-Earth and Earth-Moon systems.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-77224 , NAS 1.15:77224
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Dynamic isolation of a spacecraft science platform via momentum compensation (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The dynamic isolation of a two degree of freedom inertially stabilized science platform from the spacecrft basebody is examined. The important implications of a momentum compensated platform for pointing performance and cost are discussed, and the concept of a new system called the Integrated Platform Pointing and Attitude Control Subsystem utilizing the above property is presented. The results established in this paper are demonstrated by a computer simulation.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Modeling and simulation.; Apr. 21, 22, 1983; Pittsburgh, PA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Developing sensitivity coefficients for a state variable model of a flexible spacecraft with modular attitude control (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The numerical value for the sensitivity coefficient of each scalar state variable with respect to each parameter of a five body model of the rotational dynamics of a flexible spacecraft with modular attitude control is generated. The maximum magnitudes of these sensitivity coefficients are arranged in descending order in one table while the final time (steady state) values of these sensitivity coefficients are arranged in order of descending magnitude in a second table.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Modeling and simulation.; Apr. 21, 22, 1983; Pittsburgh, PA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Structural control research and experiments at NASA/LaRC (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Research progress in the area of structural dynamics and control using the flexible beam facility at the NASA Langley Research Center is reviewed. Particular attention is placed on the progress in adaptive control and reliability improvements using advanced control concepts. Both theoretical and experimental results are given to indicate the nature of the work being undertaken. In the adaptive control area, emphasis is placed on parameter and system identification and in comparison of competing on-line algorithms. Also, results are presented for on-line modal control laws that are interfaced to a parameter identification scheme. This provides an on-line distributed adaptive control system. In the reliability area, a design process is outlined that incorporates reliability over the design mission life.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Deployable optical systems; january 18, 19, 1983; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Comparing attitude control effectiveness for actuators on two bodies of a six body model of a flexible spacecraft with that for actuators restricted to a single body (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A ten rigid body model of a prototype flexible space platform was approximated by a six body model to facilitate comparison of attitude control effectiveness for actuators on two bodies with control effectiveness for actuators restricted to a single body of the same model. Actuators and sensors were found to be required on two of the six bodies for effective attitude control.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Modeling and simulation.; Apr. 21, 22, 1983; Pittsburgh, PA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    On identifiability of flexible structure parameters (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: This report investigates the identifiability of modal parameters of flexible structures. Expressions are derived for Cramer-Rao lower bounds for the modal parameters, that is, frequencies, damping ratios and mode shapes or slopes. The optimal initial state, which maximizes the trace of the Fisher information matrix in the absence of persistent input, is obtained. The concepts discussed are applied to a finite-element model of the 122 meter hoop/column antenna. The numerical results show that the identifiability of the structural frequencies is excellent, followed by that of the damping ratios and the mode-slopes.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-173049 , NAS 1.26:173049
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    On parameter identification for large space structures (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The design of a controller for large space structures (LSS) based on the LQG theory requires the knowledge of the LSS parameters. Since apriori knowledge of the parameters is usually not reliable, the parameters must be identified prior to the controller synthesis, using methods such as the maximum likelihood technique. An expression is obtained for the Fisher information matrix for LSS, from which Cramer-Rao bounds can be obtained in order to determine the accuracy with which the parameters can be identified.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-170306 , NAS 1.26:170306
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Structural assembly demonstration experiment, phase 1 (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The goal of this phase of the structural assembly and demonstration experiment (SADE) program was to begin to define a shuttle flight experiment that would yield data to compare on-orbit assembly operations of large space structures with neutral buoyancy simulations. In addition, the experiment would be an early demonstration of structural hardware and human capabilities in extravehicular activity (EVA). The objectives of the MIT study, as listed in the statement of work, were: to provide support in establishing a baseline neutral buoyancy testing data base, to develop a correlation technique between neutral buoyancy test results and on-orbit operations, and to prepare the SADE experiment plan (MSFC-PLAN-913).
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-193967 , NAS 1.26:193967 , SSL-10-83
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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