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  • 1
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    OSBORNE, "Strategic Hamlets in South Viet-Nam: A Survey and a Comparison" (Book Review) (1966)
    Ann Arbor, Mich., etc., : Periodicals Archive Online (PAO)
    Journal of Asian Studies. 25:3 (1966:May) 552 
    Details
    ISSN: 0021-9118
    Topics: Political Science , Economics
    Notes: BOOK REVIEWS
    URL: http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&res_dat=xri:pao:&rft_dat=xri:pao:article:1113-1966-025-03-000067
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Structural studies of two aerobrake heatshield panel concepts (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Structural sizing and performance data are presented for two different aerobrake hexagonal heatshield panel structural concepts. One concept features a sandwich construction with an aluminum honeycomb core and thin quasi-isotropic graphite-epoxy face sheets. The other concept features a skin-rib isogrid construction with thin quasi-isotropic graphite-epoxy skins, and graphite-epoxy ribs oriented at 0, +60, and -60 deg along the panel. Linear static, linear bifurcation buckling, and nonlinear static analyses were performed to compare the structural performance of the two panel concepts and assess their feasibility for a Lunar Transfer Vehicle aerobrake application.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: In: Engineering, construction, and operations in space - III: Space '92; Proceedings of the 3rd International Conference, Denver, CO, May 31-June 4, 1992. Vol. 1 (A93-41976 17-12); p. 921-932.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A space crane concept for performing on-orbit assembly (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The topics are presented in viewgraph form and include: in-space assembly and construction enhances future mission planning flexibility; in-space assembly and construction facility concept; space crane concept with mobile base; fundamental characteristics; space crane research approach; spacecraft component positioning and assembly test-bed; and articulating joint testbed.
    Keywords: CYBERNETICS
    Type: Automation and Robotics for Space-Based Systems, 1991; p 111-121
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Development of a Tendon-Actuated Lightweight In-Space MANipulator (TALISMAN) (2014)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: An invention of a new and novel space robotic manipulator is described. By using a combination of lightweight truss links, a novel hinge joint, tendon-articulation and passive tension stiffening, this new robotic manipulator architecture achieves compact packaging, high strength, stiffness and dexterity while being very lightweight compared to conventional manipulators. The manipulator is also very modular; easy to scale for different reach, load and stiffness requirements; enabling customization for a diverse set of applications. Novel features of the new manipulator concept are described as well as some of the approaches to implement these design features. Two diverse applications are presented to show the versatility of the concept. First generation prototype hardware was designed, manufactured and has been assembled into a working manipulator that is being used to refine and extend development efforts.
    Keywords: Mechanical Engineering
    Type: The 42nd Aerospace Mechanism Symposium; 405-420; NASA/CP-2014-217519
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Airframe Integration Trade Studies for a Reusable Launch Vehicle (1999)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: Future launch vehicles must be lightweight, fully reusable and easily maintained if low-cost access to space is to be achieved. The goal of achieving an economically viable Single-Stage-to-Orbit (SSTO) Reusable Launch Vehicle (RLV) is not easily achieved and success will depend to a large extent on having an integrated and optimized total system. A series of trade studies were performed to meet three objectives. First, to provide structural weights and parametric weight equations as inputs to configuration-level trade studies. Second, to identify, assess and quantify major weight drivers for the RLV airframe. Third, using information on major weight drivers, and considering the RLV as an integrated thermal structure (composed of thrust structures, tanks, thermal protection system, insulation and control surfaces), identify and assess new and innovative approaches or concepts that have the potential for either reducing airframe weight, improving operability, and/or reducing cost.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Structural performance of two aerobrake hexagonal heat shield panel concepts (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Structural sizing and performance are presented for two structural concepts for an aerobrake hexagonal heat shield panel. One concept features a sandwich construction with an aluminum honeycomb core and thin quasi-isotropic graphite-epoxy face sheets. The other concept features a skin-rib isogrid construction with thin quasi-isotropic graphite-epoxy skins and graphite-epoxy ribs oriented at 0, +60, and -60 degs along the panel. Linear static, linear bifurcation buckling, and nonlinear static analyses were performed to compare the structural performance of the two panel concepts and assess their feasibility for a lunar transfer vehicle aerobrake application.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-4372 , L-17056 , NAS 1.15:4372
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Structural design of an in-line bolted joint for the space shuttle solid rocket motor case segments (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results of a structural design study of an in-line bolted joint concept which can be used to assemble Space Shuttle Solid Rocket Motor (SRM) case segments are presented. Numerous parametric studies are performed to characterize the in-line bolted joint behavior as major design variables are altered, with the primary objective always being to keep the inside of the joint (where the O-rings are located) closed during the SRM firing. The resulting design has 180 1-inch studs, an eccentricity of -0.5 inch, a flange thickness of 3/4 inch, a bearing plate thickness of 1/4 inch, and the studs are subjected to a preload which is 70% of ultimate. The mass penalty per case segment joint for the in-line design is 346 lbm more than the weight penalty for the proposed capture tang fix.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-89027 , NAS 1.15:89027
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Structurally adaptive space crane concept for assembling space systems on orbit (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Many future human space exploration missions will probably require large vehicles that must be assembled on orbit. Thus, a device that can move, position, and assemble large and massive spacecraft components on orbit becomes essential for these missions. A concept is described for such a device: a space crane concept that uses erectable truss hardware to achieve high-stiffness and low-mass booms and uses articulating truss joints that can be assembled on orbit. The hardware has been tested and shown to have linear load-deflection response and to be structurally predictable. The hardware also permits the crane to be reconfigured into different geometries to satisfy future assembly requirements. A number of articulating and rotary joint concepts have been sized and analyzed, and the results are discussed. Two strategies were proposed to suppress motion-induced vibration: placing viscous dampers in selected truss struts and preshaping motion commands. Preliminary analyses indicate that these techniques have the potential to greatly enhance structural damping.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-3307 , L-17175 , NAS 1.15:3307
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Minimum accommodation for aerobrake assembly. Phase 2: Structural concepts for a lunar transfer vehicle aerobrake which can be assembled on orbit (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A multidisciplinary conceptual study was conducted to define a reusable lunar transfer vehicle (LTV) aerobrake which could be launched on a Space Shuttle of Titan 4 and assembled on orbit at Space Station Freedom. A major objective was to design an aerobrake, with integrated structure and thermal protection systems, which has a mass less than 20 percent (9040 lb) of the LTV lunar return mass. The aerobrake segmentation concepts, the structural concepts, a joint concept for assembly, and a structural design with analysis of the aerobrake are described. Results show that a 50-foot diameter LTV aerobrake can be designed for on-orbit assembly which will achieve the 20 percent mass budget.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-107610 , NAS 1.15:107610
    Format: application/pdf
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  • 10
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    An integrated in-space construction facility for the 21st century (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preliminary results are presented of studies being conducted by NASA on the construction of very large spacecraft. The various approaches are discussed for constructing spacecraft and their relative merits. It is observed that the Space Station Freedom has all of the basic design characteristics to permit its growth into an in-space construction facility for very large spacecraft. Also it is noted that if disturbances from construction operations are intolerable to other Space Station experiments, a co-orbiting construction facility could be built using previously developed Space Station truss hardware and systems. A discussion is also presented of a new PATHFINDER research initiative on on-orbit construction. This research effort is aimed at developing construction methods for very large spacecraft and includes the development of a 100 meter long space crane.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-101515 , NAS 1.15:101515
    Format: application/pdf
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