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  • STRUCTURAL MECHANICS  (13)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (9)
  • SPACECRAFT PROPULSION AND POWER  (4)
  • CHEMISTRY AND MATERIALS (GENERAL)  (3)
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  • 1
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    Recent advances in thermal-structural analysis and design (1978)
    In:  CASI
    Details
    Publikationsdatum: 2006-06-13
    Beschreibung: A continuing effort to develop a comprehensive capability for thermal-structural analysis and automated design (sizing) is reviewed. A principal role in the activity is played by the finite element program SPAR which contains both an efficient structural and thermal analysis capability. The benefit of having thermal and structural analyses in the same finite element program is illustrated by the application of SPAR to design calculations for the National Transonic Facility - a cryogenic wind tunnel under construction at Langley. Some experience with large-scale thermal structural analysis problems, particularly the space shuttle orbiter, has led to the identification of some analysis needs. Those needs include automated model generation and data output for lumped parameter thermal analysis, faster solution methods for nonlinear transient heat transfer, automated interpolation of temperature data from a thermal finite element model to a dissimilar structural finite model, and automated techniques to identify the times at which the critical combinations of transient heating and loads occur on a structure.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: Recent Advan. in Structures for Hypersonic Flight, Pt.2; p 897-941
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Teflon, Kapton surface and bulk effects (1985)
    In:  CASI
    Details
    Publikationsdatum: 2006-02-14
    Beschreibung: Two samples of 2 mil aluminized/Kapton thermal blanket and two samples of Teflon were received for evaluation. Their location on the solar maximum is given. The Kapton top layer of the thermal blanket had been exposed to the LEO atomic oxygen environment and shows the surface degradation due to atomic oxygen attack resulting in a diffuse character over most of the surface. The backside Kapton layer which was unexposed appeared to the eye to be in virgin condition. Another sample exhibited similar properties, but was, in large part, covered with Kapton adhesive tape and it was not possible to obtain usable specimens for analysis. One of the Teflon samples which was exposed shows signs of heavy degradation including attack on the Ag/Inconel backside by ultraviolet and atomic oxygen. The other Teflon sample which was unexposed was only slightly fogged on the Teflon side and the Ag/Inconel appeared untouched. These samples were subjected to several chemical and physical analyses, the results of which are discussed.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA. Goddard Space Flight Center Proceedings of the SMRM Degradation Study Workshop; p 287-316
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Effect of out-of-planeness of membrane quadrilateral finite elements. (1973)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Investigation of the effect of using plane quadrilateral membrane elements for modeling nonplanar structures. The effect is assessed by analyzing a simplified finite element model with the aid of the structure network analysis program. The results obtained indicate that the use of planar quadrilateral membrane elements for modeling bending problems can lead to large errors if the four points that define the quadrilateral are not in the same plane.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: AIAA Journal; 11; May 1973
    Format: text
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  • 4
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    Stress and buckling analysis of a double-bubble tank structure (1972)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: An analytical study of a two-lobed circular arc pressure vessel (double-bubble tank) with a local perturbation from the cylindrical shape was made. It can be concluded that NASTRAN provides a good linear buckling analysis capability for structures that cannot be handled by other analysis techniques. However, solutions are relatively expensive from a computational standpoint. Two worthwhile additions to the NASTRAN program would be the inclusion of a new beam element that adequately represents the shear transfer when modeling stiffeners on a shell and the capability, in a rigid format, to keep certain prescribed loads constant during the eigenvalue extraction process.
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: NASTRAN: Users' Experiences; p 53-71
    Format: application/pdf
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  • 5
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    External tank space debris considerations (1992)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Orbital debris issues associated with maintaining a Space Shuttle External Tank (ET) on orbit are presented. The first issue is to ensure that the ET does not become a danger to other spacecraft by generating space debris, and the second is to protect the pressurized ET from penetration by space debris or meteoroids. Tests on shield designs for penetration resistance showed that when utilized with an adequate bumper, thermal protection system foam on the ET is effective in preventing penetration.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AIAA PAPER 92-1411
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 6
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    Analysis of a Hot Elevon Structure (1971)
    In:  CASI
    Details
    Publikationsdatum: 2014-09-03
    Beschreibung: Comparison of ASKA and NASTRAN programs analyses of space shuttle hot elevon test article deformed under thermal and mechanical loads
    Schlagwort(e): STRUCTURAL MECHANICS
    Materialart: NASA. Langley Res. Center NASTRAN: Users Experiences; p 163-180
    Format: text
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  • 7
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    TSS tether cable meteoroid/orbital debris damage analysis (1993)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This report summarizes the damage analyses performed on the tether cable used for the tethered satellite system (TSS), for the damage that could be caused by meteoroid or orbital debris impacts. The TSS consists of a tethered satellite deployer and a tethered satellite. The analytical studies were performed at Marshall Space Flight Center (MSFC) with the results from the following tests: (1) hypervelocity impact tests to determine the 'critical' meteoroid particle diameter, i.e., the maximum size of a meteoroid particle which can impact the tether cable without causing 'failure'; (2) electrical resistance tests on the damaged and undamaged tether cable to determine if degradation of current flow occurred through the damaged tether cables; and (3) tensile load tests to verify the load carrying capability of the damaged tether cables. Finally, the HULL hydrodynamic computer code was used to simulate the hypervelocity impact of the tether cable by particles at velocities higher than can be tested, to determine the extent of the expected tether damage.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA-TM-108404 , NAS 1.15:108404
    Format: application/pdf
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  • 8
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    Chemical vapor deposition coatings for oxidation protection of titanium alloys (1991)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Results of an experimental investigation of the oxidation protection afforded to Ti-14Al-21Nb and Ti-14Al-23Nb-2V titanium aluminides and Ti-17Mo-3Al-3Nb titanium alloy by aluminum-boron-silicon and boron-silicon coatings are presented. These coatings are applied by a combination of physical vapor deposition (PVD) and chemical vapor deposition (CVD) processes. The former is for the application of aluminum, and the latter is for codeposition of boron and silicon. Coating thickness is in the range of 2 to 7 microns, and coating weights are 0.6 to 2.0 mg/sq cm. Oxidation testing was performed in air at temperatures to 1255 K in both static and hypersonic flow environments. The degree of oxidation protection provided by the coatings is determined from weight change measurements made during the testing and post test compositional analyses. Temperature-dependent total normal emittance data are also presented for four coating/substrate combinations. Both types of coatings provided excellent oxidation protection for the exposure conditions of this investigation. Total normal emittances were greater than 0.80 in all cases.
    Schlagwort(e): CHEMISTRY AND MATERIALS (GENERAL)
    Materialart: In: Damage and oxidation protection in high temperature composites. Vol. 1; Proceedings of the Symposium, 112th ASME Winter Annual Meeting, Atlanta, GA, Dec. 1-6, 1991 (A93-53937 23-24); p. 1-8.
    Format: text
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  • 9
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    The effectiveness of multi-layer insulation as meteoroid and orbital debris shielding (1992)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: This paper presents the results of a study of the penetration resistance of Type I Multi-Layer Insulation (MLI) to meteoroid and orbital debris particles. Hypervelocity impact tests on MLI were performed and the collected data was compared to data and empirical equations developed for aluminum. The study results indicate that MLI can be an effective shield from meteoroids and orbital debris for short duration missions and for non-critical elements. However, long missions which require high levels of protection cannot rely on MLI without a thorough investigation of the overall system reliability.
    Schlagwort(e): CHEMISTRY AND MATERIALS (GENERAL)
    Materialart: AIAA PAPER 92-1460
    Format: text
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  • 10
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    Preliminary design of a meteoroid/orbital debris shield system for a Mars mission spacecraft (1992)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A preliminary design of a spacecraft shield system to defeat meteoroids and orbital debris during a Mars mission is presented. The mission scenario is first defined in terms of stage times which include LEO, transit, low-Mars orbit, and Mars surface periods. The environment definitions for earth-orbital space debris, planetary meteoroids, and interplanetary meteoroids are next introduced. Shield system design approaches incorporate stochastic simulation, hydrocode analyses, hypervelocity impact testing, and optimization techniques. Structural design trades presented include spacecraft configuration, mission schedule, penetration risk, and total standoff distance between the bumper and wall.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AIAA PAPER 92-1406
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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