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  • 1
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    Unknown
    On the design of an adjustable high precision latching hinge (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design and test details of a high precision hinge and locking mechanism created principally in support of the Lockheed space deployable Flexrib Parabolic Antenna concept are presented. These developed improvements in the detail design of ultra-precise rib hinge and contour adjustment mechanisms will allow radio frequency antenna reflectors to expand into the 15-50 meter diameter size class and to support the .013 mm. deployment repeatability tolerance required to support the 12+ GHz frequency range.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA. Johnson Space Center The 13th Aerospace Mech. Symp.; p 127-136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    On the design of large space deployable modular antenna reflectors (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The deployment kinematics, stowing philosophy, and deployment sequencing for large deployable antenna modules were verified. Mesh attachment methods compatible with full scale modules were devised. Parametric studies of large modular reflectors established size, mass, and aperture frequency capabilities for these assemblies. Preliminary studies were made devising means of delivering modules to orbit, and once there, of assembling the modules into complete modular antenna reflectors. The basic feasibility of creating mass efficient modules erectable into large structures in space was established.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 147-157
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Modular antenna design study (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The mechanical design of a modular antenna concept was developed sufficiently to allow manufacture of a working demonstration model of a module, to predict mass properties, and to make performance estimates for antenna reflectors composed of these modules. The primary features of this concept are: (1) each module is an autonomous structural element which can be attached to adjacent modules through a three point connection; (2) the upper surface is a folding hexagonal truss plate mechanism which serves as the supporting structure for a reflective surface; and (3) the entire truss and surface can be folded into a cylindrical envelope in which all truss elements are essentially parallel. The kinematic studies and engineering demonstration model fully verified the deployment kinematics, stowing philosophy, and deployment sequencing for large antenna modules. It was established that such modules can be stowed in packages as small as 25 cm in diameter, using 1.27 cm diameter structural tubes. The development activity indicates that this deployable modular approach towards building large structures in space will support erection of 450 m apertures for operation up to 3 GHz with a single space shuttle flight.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-3316 , LMSC-D714622
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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