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  • NONMETALLIC MATERIALS  (3)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (3)
  • 1975-1979  (6)
  • 1
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    Manufacture of DPFC-DMS polymer in the SKG range (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: BPFC-DMS block copolymers were synthesized on a pre-pilot scale (i.e., to 5 Kg lots) and subsequently fabricated into clear, colorless films. Details of the synthesis procedures, property determinations, and film casting techniques are presented. Solubility, viscosity and molecular weight characteristics of the resulting product are reported.
    Keywords: NONMETALLIC MATERIALS
    Type: NASA-CR-166276 , NAS 1.26:166276
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Flammability screening tests of resins (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Selected flammability characteristics of glass cloth laminates of thermosetting resins are evaluated. A protocol for the evaluation of the flammability hazards presented by glass cloth laminates of thermosetting resins and the usefulness of that protocol with two laminates are presented. The glass laminates of an epoxy resin, M-751 are evaluated for: (1) determination of smoke generation from the laminates; (2) analysis of products of oxidative degradation of the laminates; (3) determination of minimum oxygen necessary to maintain flaming oxidation; (4) evaluation of toxicological hazards.
    Keywords: NONMETALLIC MATERIALS
    Type: NASA-CR-152312 , UTEC-79-140
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Determination of mechanical properties of polymer film materials (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Five polymeric film materials, Tedlar, Teflon, Kapton H, Kapton F, and a fiberglass reinforced polyimide, PG-402, in thickness ranging from 0.002 to 0.005 inch, were tested over a temperature range of -195 to 200 C in the "machine" and transverse direction to determine: elastic modulus, Poisson's ratio, three percent offset yield stress, fracture stress, and strain to fracture. The elastic modulus, yield stress and fracture stress decreased with increasing temperature for all the materials while the fracture strain increased. Teflon and Tedlar had the greatest temperature dependence and PG-402 the least. At 200 C the Poisson ratio values ranged from 0.39 to 0.5; they diminished as the temperature decreased covering a range of 0.26 to 0.42 at -195 C. Shortening the gauge length from eight inches to one inch increased the strain to fracture and lowered the elastic modulus values.
    Keywords: NONMETALLIC MATERIALS
    Type: NASA-CR-147115 , KD-75-9
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Flexible space structure model reduction by modal cost analysis (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: It is noted that reduced models and reduced controllers for flexible space structures are obtained by retaining those modes which make the greatest contribution to quadratic control objectives. Attention is given to the relative importance of damping, frequency and mode shapes in the mode truncation decisions for the following control objectives: attitude control, vibration suppression and figure control. It is also shown that using Modal Cost Analysis (MCA) on the closed loop modes of the optimally controlled system allows the construction of reduced control policies which feedback only those closed loop coordinates which are most critical to the quadratic control performance criterion. In this manner, the modes which need to be controlled are deduced from truncations of the optimal controller.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Dynamics and control of large flexible spacecraft; Jun 21, 1979 - Jun 23, 1979; Blacksburg, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Controllability and observability for flexible spacecraft (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Current interest in extended sensing and actuation for the control of flexible spacecraft has led to the use of modern multivariable control theory and the associated concepts of controllability and observability. This paper shows how to evaluate these properties on a mode-by-mode basis for flexible spacecraft control analysis. Relatively simple criteria are derived which indicate the degree of controllability (observability) of each mode in simple literal terms. These criteria provide physical insight and practical guidance on the type, number, and positioning of sensors and actuators. The results are interpreted for force and torque actuators, and for attitude and deformation measurements. To illustrate these ideas, sample controllability and observability 'surfaces' are presented for the Purdue generic flexible spacecraft model.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Dynamics and control of large flexible spacecraft; Jun 21, 1979 - Jun 23, 1979; Blacksburg, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Dynamics of incremental motion devices associated with planetary exploration spacecraft (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Incremental motion devices provide accurate and rapid movement of spacecraft science platforms, antennas and related mechanisms. The paper considers the computerized simulation of a stepper motor/gear train/ science platform system that will be launched on the Mariner Jupiter Saturn 1977. It was determined that a smaller stepper motor could be used as the prime mover for the science platform, and it was concluded that the existing digital controller was unable to achieve the required pointing accuracy, and a new controller design was necessary.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Annual Symposium on Incremental Motion Control Systems and Devices; Apr 01, 1975 - Apr 03, 1975; Urbana, IL
    Format: text
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    NASA TECHNICAL REPORTS
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