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  • 1
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    Comments on the paper ‘the steady-state format of global climate’ (1981)
    Wiley
    Details
    Publication Date: 1981-01-01
    Print ISSN: 0035-9009
    Electronic ISSN: 1477-870X
    Topics: Geography , Physics
    Published by Wiley
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    PAPER CURRENT
  • 2
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    Analytical comparison of two wing structures for Mach 5 cruise airplanes (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 12, p. 1701, Accession no. A83-29806
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 21; 272-277
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Structures and subsystems (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: New and improved materials combined with efficient structural design concepts have made an essential contribution towards the shaping of the present transportation system (STS), and now, for the replacement of the STS in the year 2005, new materials and novel designs are being studied to identify the technologies which should be developed for a low-cost future space transportation system (FSTS). Three basic structural arrangements were considered for the FSTS orbiter. They include a nonintegral tank arrangement, an integral-tank arrangement, and a hybrid of the first two. Three representative arrangements regarding wall constructions are considered. Each employs a blade-stiffened aluminum tank with reinforced closed-cell-foam cryogenic insulation. Attention is given to an aluminum-alloy structure, a graphite-epoxy structure, a graphite-polyimide structure, a carbon-carbon surface panel structure, a graphite-composite fuselage structure, serviceability and all-weather considerations, and structural concept ratings.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Astronautics and Aeronautics (ISSN 0004-6213); 21; June 198
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Vortex Lift Augmentation by Suction (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Lift performance is improved on a 60 degrees swept Gothic wing. Vortex lift at moderate to high angles of attack on highly swept wings used to improve takeoff performance and maneuverability. New design proposed in which suction of propulsion system augments vortex. Turbofan placed at down stream end of leading-edge vortex system induces vortex to flow into inlet which delays onset of vortex breakdown.
    Keywords: MECHANICS
    Type: LAR-12969 , NASA Tech Briefs (ISSN 0145-319X); 7; P. 312
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    An analytical study of reusable flight-weight cryogenic propellant tank designs (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Thermostructural analyses of reusable flight-weight cryogenic tanks for a vertically launched space vehicle have been conducted. An analytical procedure was developed for sizing the tank structure, cryogenic insulation, and thermal protection system. Unstiffened, integrally-stiffened, and honeycomb core sandwich tank skins using aluminum or stainless steel materials were compared for their ability to meet design criteria at least weight. Cryogenic insulation systems were also evaluated, including closed-cell cryogenic foams and evacuated honeycomb core. The results indicate that a 400 F foam-insulated unstiffened-skin aluminum tank structure is the lightest structure for either LOX or LH2 tanks that meet the selected design criteria, but only two to four percent lighter than a stiffened aluminum tank.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 84-0865
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Thermostructural analyses of structural concepts for hypersonic cruise vehicles (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A matrix of structural concepts suitable for Mach 5 hydrogen-fueled hypersonic vehicles are defined, and a thermostructural analysis of each is presented. The thermal environment encountered in this flight regime mandates hot structures of superalloy materials or insulated structures using more conventional materials such as titanium, aluminum, and composites. This paper compares the thermostructural performance of several concepts. The various structures are initially sized to carry a 2.5 g subsonic maneuver load. The structural weights are determined, and these components are then evaluated in a transient heating program along with various thermal protection systems to determine the minimum weight combination. The temperature profiles generated for these minimum weight solutions are used as input to a structural analysis along with a model of the appropriate structural concept to calculate thermal stresses. Generally, hot structure concepts have higher thermal stresses. In most cases, the thermal stresses are below the yield strength of the material. It is shown that integral tanks have weights similar to nonintegral tank concepts for the same level of technology. Moreover, an insulated tubular aluminum-composite structure with nonintegral tanks appear attractive for near-term vehicles.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0407 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Aerodynamics of a turbojet-boosted launch vehicle concept (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Results from analytical and experimental studies of the aerodynamic characteristics of a turbojet-boosted launch vehicle are presented. The success of this launch vehicle concept depends upon several novel applications of aerodynamic technology, particularly in the area of takeoff lift and minimum transonic drag requirements. The take-off mode stresses leading edge vortex lift generated in parallel by a complex arrangement of low aspect ratio booster and orbiter wings. Wind-tunnel tests on a representative model showed that this low-speed lift is sensitive to geometric arrangements of the booster-orbiter combination and is not predictable by standard analytic techniques. Transonic drag was also experimentally observed to be very sensitive to booster location; however, these drag levels were accurately predicted by standard farfield wave drag theory.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-0360 , Aerospace Sciences Meeting; Jan 14, 1980 - Jan 16, 1980; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Structural concepts for future space transportation orbiters (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Two structural concepts for a fully reusable STS orbiter are compared with respect to weight and the ability to satisfy structural goals. The cryogenic propellant tanks for both concepts use welded, blade-stiffened aluminum skins for leak-free containment and compatibility with LOX and LH2. The tanks are sized primarily by pressure, although some areas are sized by bending and fracture mechanics considerations. The tank concept is regarded as state-of-the-art, even though it requires a closed cell foam insulation with a dry air purge to prevent air liquefaction and ice formation. It is noted that the foam will require testing to verify its design life for use in the STS. One concept has nonintegral tanks suspended inside an insulated aluminum airframe and thrust structure. Here, a durable thermal protection system external insulation is mechanically attached to the airframe, allowing a buckled skin design. The other concept uses a novel structural arrangement consisting of a separate tank/thrust structure that supports a hot advanced-carbon-carbon aeroshell structure.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-0210 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    An analytical comparison of two wing structures for Mach 5 cruise airplanes (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Mach 5 cruise research conducted by NASA is related to aerodynamics, propulsion, and structures. The study of structures includes the propulsion system, fuselage, and wings. Various studies have shown that the achievement of adequate range is largely dependent on a low structural mass fraction. The present investigation is concerned with a study of two wing structure configurations for Mach 5 aircraft. An uprated version (Ti-6242 replacing B-120 titanium) of the YF-12/SR-71 wing structure is considered. The B-120 titanium structure represents the current art of high speed aircraft wing structures. The YF-12 wing structure was designed about 20 years ago when the analytical methods for calculating thermal stresses were limited. The second wing structural configuration studied in the present investigation also used Ti-6242 materials but replaced the corrugated-beaded panels with diffusion bonded honeycomb-core sandwich panels, and replaced the z-stiffened shear webs with sine-wave stiffened shear webs.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-0974 , Structures, Structural Dynamics and Materials Conference; May 02, 1983 - May 04, 1983; Lake Tahoe, NV
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Vortex lift augmentation by suction on a 60 deg swept Gothic wing (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation was conducted in the Langley high-speed 7- by 10-foot wind tunnel to determine the aerodynamic performance of suction applied near the wing tips above the trailing edge of a 60 deg swept Gothic wing. Moveable suction inlets were symmetrically mounted in the proximity of the trailing edge, and the amount of suction was varied to maximize wing lift. Tests were conducted at Mach 0.15, 0.30, and 0.45, and the angle of attack was varied from -4 to 50 deg. The suction augmentation increases the lift coefficient over the entire range of angle of attack. The lift improvement exceeds the unaugmented wing lift by over 20%. Moreover, the augmented lift exceeds the lift predicted by vortex lattice theory to 30 deg angle of attack. Suction augmentation is postulated to strengthen the vortex system by increasing its velocity and making it more concentrated. This causes the vortex breakdown to be delayed to a higher angle of attack
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0231 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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    NASA TECHNICAL REPORTS
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