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  • 1
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    Buckling of nearly cylindrical shells under lateral pressure. (1972)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: The effect of slight meridional curvature on the buckling of shells subjected to an external constant directional lateral pressure is examined. A class of nearly cylindrical shells with constant meridional curvature, a central radius-to-thickness ratio of 500, and central rise-to-shell-length ratios varying from plus 5% to minus 5% is considered. A brief study is presented of the dependence of the critical lateral pressure on the meridional curvature and on the length and meridional edge restraint.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: AIAA Journal; 10; Feb. 197
    Format: text
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  • 2
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    Vibration characteristics of aluminum plates reinforced with boron-epoxy composite material. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Analytical and experimental data on the vibration characteristics of cantilevered winglike flat trapezoidal aluminum plates are presented. The plates had been reinforced with boron-epoxy composite material which had been placed symmetrically about the plate middle surface. The effect of filament orientation on the mode shapes and frequencies of the first ten modes and on the damping coefficients of several of the lowest frequency modes has been investigated experimentally. Experimental data are compared with results from a finite-element analysis. Stiffness properties of the composite material for use in the analysis were determined from vibration tests of composite reinforced aluminum beams.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Composite Materials; 7; July 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Interactive design of large end rings on stiffened conical shells using composites (1974)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Design study methods and results for a composite reinforced base ring for the conical aeroshell structure of the planetary lander vehicle for Project Viking, an unmanned mission to Mars, are presented. The aeroshell is a ring and stringer-stiffened conical shell structure having a half angle of 70 degrees with a large base ring mounted at the outer edge of the cone and a large pay-load ring in the interior with many smaller rings spaced along the inside shell surface. The purpose of the structure is to develop the aerodynamic drag required to decelerate the lander in the Mars atmosphere to facilitiate a soft landing. The design of a shell structure of this complexity requires the use of the latest technology available in a large general-purpose shell buckling program. The large general-purpose non-linear shell buckling program (BOSOR 2) which was used for this purpose is described.
    Schlagwort(e): STRUCTURAL MECHANICS
    Format: text
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  • 4
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    Selective reinforcement of wing structure for flutter prevention. (1972)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: The results of an analytical study are presented on the use of boron polyimide filamentary composite material for the purpose of increasing the flutter speed of a simple titanium full depth sandwich wing structure designed for strength. The results clearly demonstrate that selective reinforcement of wing surfaces, using judiciously placed filamentary composites, promises sizable mass savings in the design of advanced aircraft structures.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Journal of Aircraft; 9; Nov. 197
    Format: text
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  • 5
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    Experiences with the use of axisymmetric elements in cosmic NASTRAN for static analysis (1991)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-31
    Beschreibung: Discussed here are some recent finite element modeling experiences using the axisymmetric elements CONEAX, TRAPAX, and TRIAAX, from the COSMIC NASTRAN element library. These experiences were gained in the practical application of these elements to the static analysis of helicopter rotor force measuring systems for two design projects for the NASA Ames Research Center. These design projects were the Rotor Test Apparatus and the Large Rotor Test Apparatus, which are dedicated to basic helicopter research. Here, a genetic axisymmetric model is generated for illustrative purposes. Modeling considerations are discussed, and the advantages and disadvantages of using axisymmetric elements are presented. Asymmetric mechanical and thermal loads are applied to the structure, and single and multi-point constraints are addressed. An example that couples the axisymmetric model to a non-axisymmtric model is demonstrated, complete with DMAP alters. Recommendations for improving the elements and making them easier to use are offered.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Computer Software Management and Information Center, Nineteenth NASTRAN (R) Users' Colloquium; p 119-161
    Format: application/pdf
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  • 6
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    The use of NASTRAN in the design of wind tunnel research aircraft (1987)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-31
    Beschreibung: The relationship between NASTRAN and the wind tunnel model design process is discussed. Specific cases illustrating the use of NASTRAN for static, heat transfer, dynamic, and aeroelastic analyses are presented. Advantages and disadvantages of using NASTRAN are summarized.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: COSMIC, 15th NASTRAN (R) Users' Colloquium; p 166-183
    Format: application/pdf
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  • 7
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    IBM JCL made easy by means of ISPF dialog application (1987)
    In:  CASI
    Details
    Publikationsdatum: 2013-08-31
    Beschreibung: An interactive cathode ray tube (CRT) terminal application has been developed which automatically generates the job control language (JCL) and submits NASTRAN batch jobs at an IBM mainframe installation. The relevant parameters for each NASTRAN batch job are stored in a table. Once a table entry is defined, the corresponding NASTRAN batch job may be submitted as often as desired with a minimum of keystrokes. For most users, there is no need for any knowledge of JCL.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: COSMIC, 15th NASTRAN (R) Users' Colloquium; p 36-55
    Format: application/pdf
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  • 8
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    Mini-mast CSI testbed user's guide (1992)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The Mini-Mast testbed is a 20 m generic truss highly representative of future deployable trusses for space applications. It is fully instrumented for system identification and active vibrations control experiments and is used as a ground testbed at NASA-Langley. The facility has actuators and feedback sensors linked via fiber optic cables to the Advanced Real Time Simulation (ARTS) system, where user defined control laws are incorporated into generic controls software. The object of the facility is to conduct comprehensive active vibration control experiments on a dynamically realistic large space structure. A primary goal is to understand the practical effects of simplifying theoretical assumptions. This User's Guide describes the hardware and its primary components, the dynamic characteristics of the test article, the control law implementation process, and the necessary safeguards employed to protect the test article. Suggestions for a strawman controls experiment are also included.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: NASA-TM-102630 , NAS 1.15:102630
    Format: application/pdf
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  • 9
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    Thermally induced stresses in cross-ply composite tubes (1986)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An approximate solution for determining stresses in cross-ply composite tubes subjected to a circumferential temperature gradient is presented. The solution is based on the principle of complementary virtual work (PCVW) in conjunction with a Ritz approximation on the stress field and accounts for the temperature dependence of material properties. The PCVW method is compared with a planar elasticity solution using temperature-independent material properties and a Navier approach. The net effect of including temperature-dependent material properties is that the peak absolute values of the stresses are reduced. The dependence of the stresses on the circumferential location is also reduced in comparison with the case of temperature-independent properties.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: AIAA PAPER 86-0968
    Format: text
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  • 10
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    Advantages of multipoint control for vibration testing of complete Ranger flight spacecraft (1966)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-05-29
    Beschreibung: Vibration tests on Ranger spacecraft with single point control of input vibratory accelerations
    Schlagwort(e): STRUCTURAL MECHANICS
    Format: text
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