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  • 1
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    Mechanical properties of a fiberglass prepreg system at cryogenic and other temperatures (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 13, p. 2024, Accession no. A82-30099
    Keywords: COMPOSITE MATERIALS
    Type: AIAA Journal (ISSN 0001-1452); 21; 1722-172
    Format: text
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  • 2
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    National Transonic Facility Fan Blade prepreg material characterization tests (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The test program for the basic prepreg materials used in process development work and planned fabrication of the national transonic facility fan blade is presented. The basic prepreg materials and the design laminate are characterized at 89 K, room temperature, and 366 K. Characterization tests, test equipment, and test data are discussed. Material tests results in the warp direction are given for tensile, compressive, fatigue (tension-tension), interlaminar shear and thermal expansion.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-81800
    Format: application/pdf
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  • 3
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    Computer program for determining mass properties of a rigid structure (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program was developed for the rapid computation of the mass properties of complex structural systems. The program uses rigid body analyses and permits differences in structural material throughout the total system. It is based on the premise that complex systems can be adequately described by a combination of basic elemental shapes. Simple geometric data describing size and location of each element and the respective material density or weight of each element were the only required input data. From this minimum input, the program yields system weight, center of gravity, moments of inertia and products of inertia with respect to mutually perpendicular axes through the system center of gravity. The program also yields mass properties of the individual shapes relative to component axes.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-TM-78681
    Format: application/pdf
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  • 4
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    Mechanical properties of a fiberglass prepreg system at cryogenic and other temperatures (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The compressor driving the flow in the National Transonic Facility, which is nearing completion at the Langley Research Center, has 25 fiberglass blades. E-glass cloth with a pre-impregnated epoxy resin has been selected as the material for the fan blades because of its low cost, high damping, and fatigue resistance. A complete characterization is presented of this fan blade fiberglass system at temperatures of 367 K, room temperature, and 89 K. The characterization test results suggest that the material follows the general trends of metals and other glass-reinforced plastics at cryogenic temperatures. A slight diminution in strength was observed at the elevated temperature. The tests included the following: tensile, compression, fatigue, inplane shear, interlaminar shear, thermal expansion, creep, and thermal cycle.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 82-0708 , In: Structures, Structural Dynamics and Materials Conference; May 10, 1982 - May 12, 1982; New Orleans, LA
    Format: text
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  • 5
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    Technologies involved in configuring an advanced earth-to-orbit transport for low structural mass (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A tradeoff study for a single-stage, earth-to-orbit transport spacecraft configured with low structural mass as the prime objective is presented. Among the major design elements affecting vehicle mass are: maneuverability and re-entry heating, the compatibility of an irregular cargo bay geometry to future mission requirements, the fabrication and assembly of large honeycomb structure fuselage sections, and the development of LOX/LH2 engine extendable nozzles and dual-propulsion schemes. It is shown that vehicle geometry and materials and structural technologies will be the critical areas in the development of such a system.
    Keywords: SPACE TRANSPORTATION
    Type: SAWE PAPER 1380 , Annual Conference of the Society of Allied Weight Engineers; May 12, 1980 - May 14, 1980; St. Louis, MO
    Format: text
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  • 6
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    Mass estimating techniques for earth-to-orbit transports with various configuration factors and technologies applied (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A study of an array of advanced earth-to-orbit space transportation systems with a focus on mass properties and technology requirements is presented. Methods of estimating weights of these vehicles differ from those used for commercial and military aircraft; the new techniques emphasizing winged horizontal and vertical takeoff advanced systems are described utilizing the space shuttle subsystem data base for the weight estimating equations. The weight equations require information on mission profile, the structural materials, the thermal protection system, and the ascent propulsion system, allowing for the type of construction and various propellant tank shapes. The overall system weights are calculated using this information and incorporated into the Systems Engineering Mass Properties Computer Program.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1315 , Annual Conference; May 07, 1979 - May 09, 1979; New York, NY
    Format: text
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  • 7
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    Techniques for the determination of mass properties of earth-to-orbit transportation systems (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: One estimating technique involves trending whereby projections of overall mass properties of vehicles are determined with few inputs. The second technique involves trending of individual subsystems using equations of the form KXN to the nth power or KX. Some constants and exponentials are provided for sample subsystems. Mass properties are reported in a format recommended by mil spec - 38310.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-78661
    Format: application/pdf
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  • 8
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    Mass properties of a rigid structure (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Program MASPROP rapidly calculates mass properties of complex, rigid structural systems. Its basic premise is that complex systems can be adequately described by combination of basic elementary structural shapes.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LAR-12454 , NASA Tech Briefs (ISSN 0145-319X); 4; 3; P. 429
    Format: text
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  • 9
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    A shuttle development flight test vehicle study (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study is presented that identifies the potential performance capability of the production shuttle orbiter for powered flight tests using several propulsion systems following vertical takeoff and using J-2 rocket engines following air launch. Of the approaches considered, the air-launched orbiter equipped with J-2 rocket engines appeared to have the highest potential for early shuttle development flights. With this approach, mach 4 appeared attainable using 45.5K kg (100K lb) of internal propellant. Several issues were identified that require resolution to prove feasibility.
    Keywords: SPACE VEHICLES
    Type: NASA-TM-X-71978
    Format: application/pdf
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  • 10
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    Mechanical properties of adhesive systems at cryogenic and other temperatures (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents a summary of the National Transonic Facility (NTF) fan blade adhesive characterization tests. Data was obtained at -300 F, room temperature (RT) and 200 F. The adhesive characterization data was acquired using specimens fabricated from materials orientated to simulate the lay up of the fan blades. Specimen fabrication, characterization tests, test equipment, test data, results and concluding remarks are reported. Adhesive test results are presented for specimens of the following types: lap shear, double lap shear, butt, short beam shear, flexure, and differential strain.
    Keywords: NONMETALLIC MATERIALS
    Type: National Technical Association, Annual Conference; Aug 02, 1982 - Aug 07, 1982; Baltimore, MD
    Format: text
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