Preliminary results from Surveyor 3 analysis
Engineering and scientific analysis of Surveyor 3 dust, TV camera, and structural components
Benson, R. E.↗
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Results for “Structural components”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Preparation and characterization of the Pyrrones as thermal structural materials
Development of technique for preparing foam materials to be used as thermal structural components in spacecraft construction
Kimmel, B. G.↗
Aerospace launch vehicle program factors, structures and advanced materials cost- performance tradeoffs
Cost-performance tradeoffs of aerospace launch vehicle expandable structural components, investigating program factors, materials and construction technologies
Bradshaw, R. B.↗
Investigation of safe-life fail-safe criteria for the space shuttle
An investigation was made to determine the effects of a safe-life design approach and a fail-safe design approach on the space shuttle booster vehicle structure, and to recommend any changes to the structural design criteria. Two configurations of the booster vehicle were considered, one incorporating a delta wing (B-9U configuration) and the other a swept wing (B-16B configuration). Several major structural components of the booster were studied to determine the fatigue life, safe-life, and fail-safe capabilities of the baseline design. Each component was investigated to determine the practicability of applying a safe-life or fail-safe design philosophy, the changes such design approaches might require, and the impact of these changes on weight, cost, development plans, and performance.
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Development of graphite/polyimide composites.
This paper covers the characterization of the HT-S/RS6234 graphite/polyimide system. Processing techniques for vacuum bag, vacuum bag-press augmented, and vacuum bag-autoclave augmented have been developed under sponsorship of the NASA Marshall Space Flight Center (MSFC). Preliminary design properties for the HT-S/RS6234 resin system were developed at -320, 75, and 600 F. The processing techniques and the materials developed during this program are all directly applicable to the fabrication of large structural components such as would be required for the space shuttle and other advanced space vehicles.
Stuckey, J. M.↗
Hail damage to typical aircraft surfaces.
Severe structural damage can occur when aircraft collide with hailstones. Consequently, methods of predicting hail damage to airplane surfaces are needed by the aircraft designer. This paper describes an analytical method of predicting the dent depth and final deformed shape for simple structural components impacted by hailstones. The solution was accomplished by adapting the DEPROSS computer program to the problem of normal impact of hail on flat metallic sheets and spherical metallic caps. Experimental data and analytical predictions are presented for hail damage to typical aircraft surfaces along with a description of the hail gun and hail simulation technique used in the experimental study.
Hayduk, R. J.↗
Composites - Lighter and cheaper.
Composite engineering materials have two distinct parts, including the load-bearing filaments and the matrix. Fibers can range from glass to boron and graphite. Matrix constituents include epoxies for lower temperatures and metals for higher temperatures. Composites appear as tape or combined with metal in structural shapes. The increased use of composites will reduce over-all per pound manufacturing costs. Two major deterrents to further application of composites in advanced commercial transports include a shortage of cost-effective structural design concepts and a lack of confidence in the life characteristics. A program has been outlined by NASA that will, if implemented, provide considerable in-service life experience with structural components on commercial transports.
Goble, R. L.↗
Time-dependent Structural Analysis of Metal-epoxy Composites
In an effort to reduce structural weight while maintaining structural integrity on the space shuttle and other proposed space vehicles, various composite materials are being evaluated to determine their applicability and reliability in load carrying situations. While most of the composites being considered for structural components are of the metal-metal type, there are some applications for which metal-epoxy composites are proposed. An approximate method is presented to analyze plane stress orthotropic linear viscoelastic problems under isothermal conditions. A computer program which is based on the method was used to solve a simple uniaxial creep problem for a Maxwell type material. This solution is presented and compared with the analytical solution.
Dehoff, P. H.↗
Apollo experience report: Spacecraft structural windows
The window structural design and verification experience is presented for the Apollo command and lunar modules. This report presents window design philosophy, design criteria, hardware description, and qualification and acceptance test programs and discusses the problems encountered and solutions developed in these areas. The structural characteristics of glass are not generally well understood by designers. The optics and instrument glass covers were not considered to be structural components and thus were not normally subjected to the design, qualification, and acceptance standards necessary to preclude failures. These two factors contributed significantly to window problems on both Apollo spacecraft.
Pigg, O. E.↗
Methane absorption in the Jovian atmosphere. I - The Lorentz half-width in the 3nu/sub 3/ band at 1.1 micron.
The Lorentz half-width alpha (L), of the fine-structure components of the methane 3nu/sub 3/ R-branch in the Jovian spectrum has been measured from photoelectric observations of the singlet R(1). Curves of growth for the 3nu/sub 3/ R-branch manifolds have been calculated, using the measured value of alpha (L) and assuming a reflecting-layer atmosphere. The Walker-Hayes (1967) equivalent widths have been reanalyzed for rotational temperature and methane abundance. The half-width derived here is significantly different from a similar measurement made by Farmer (1969). The source of the discrepancy remains obscure.
Bergstralh, J. T.↗
Control vane for engine exhaust flow
Vane solves problem of hot-gas exhaust impingement on curved-duct exteriors, shielding, and other nearby structure components. To eliminate secondary egress of exhaust, curved vane is placed upstream of engine exhaust duct and in close proximity to exhaust exit to induce free-stream flow more in line with exit.
Shaw, C. S.↗
Analysis of fatigue, fatique-crack propagation, and fracture data
Analytical methods have been developed for consolidation of fatigue, fatigue-crack propagation, and fracture data for use in design of metallic aerospace structural components. To evaluate these methods, a comprehensive file of data on 2024 and 7075 aluminums, Ti-6A1-4V, and 300M and D6Ac steels was established. Data were obtained from both published literature and unpublished reports furnished by aerospace companies. Fatigue and fatigue-crack-propagation analyses were restricted to information obtained from constant-amplitude load or strain cycling of specimens in air at room temperature. Fracture toughness data were from tests of center-cracked tension panels, part-through crack specimens, and compact-tension specimens.
Jaske, C. E.↗
Engineering report. Part 2: NASA wheel and brake material tradeoff study for space shuttle type environmental requirements
The study included material selection and trade-off for the structural components of the wheel and brake optimizing weight vs cost and feasibility for the space shuttle type application. Analytical methods were used to determine section thickness for various materials, and a table was constructed showing weight vs. cost trade-off. The wheel and brake were further optimized by considering design philosophies that deviate from standard aircraft specifications, and designs that best utilize the materials being considered.
Bok, L. D.↗
Engineering report. Part 3: NASA lightweight wheel and brake sub-system. Lightweight brake development
The development of light weight wheel and brake systems designed to meet the space shuttle type requirements was investigated. The study includes the use of carbon graphite composite and beryllium as heat sink materials and the compatibility of these heat sink materials with the other structural components of the wheel and brake.
Bok, L. D.↗
Thin-film diffusion brazing of titanium alloys
A thin film diffusion brazing technique for joining titanium alloys by use of a Cu intermediate is described. The method has been characterized in terms of static and dynamic mechanical properties on Ti-6Al-4V alloy. These include tensile, fracture toughness, stress corrosion, shear, corrosion fatigue, mechanical fatigue and acoustic fatigue. Most of the properties of titanium joints formed by thin film diffusion brazing are equal or exceed base metal properties. The advantages of thin film diffusion brazing over solid state diffusion bonding and brazing with conventional braze alloys are discussed. The producibility advantages of this process over others provide the potential for producing high efficiency joints in structural components of titanium alloys for the minimum cost.
Mikus, E. B.↗
A parametric analysis of transport aircraft system weights and costs
In determining unit and operating costs for advanced aircraft, it has been found that by having first-order weight and performance approximations for the aircraft systems and structural components, a step increase in cost prediction accuracy results. This paper presents first-order approximation equations for these systems and components. These equations were developed from data for most current jet transports, and they have been ordered to use a minimum number of performance parameters such as aircraft style, number of passengers, empty and gross weight, cargo load, and operating range. A NASA Ames Research Center aircraft cost program has been used to compare calculated and actual weights for the same aircraft. Good aircraft cost correlation is shown to exist between calculated first-order and actual aircraft weight data.
Anderson, J. L.↗
Long base line interferometry of the sun at centimeter wavelengths
The three-element interferometer of the National Radio Astronomy observatory and the two-element interferometer of the Hat Creek Observatory have been used to observe the fine structure of the sun at 11.1-, 3.7-, and 1.3-cm wavelengths. Solar active regions have been synthesized at 11.1- and 3.7-cm wavelengths with angular resolutions of 9 and 3 arc sec, respectively. Structural components on the scale of a few seconds of arc have also been detected in the quiet-sun and flare regions.
Kundu, M. R.↗
Titan 3E/Centaur D-1T Systems Summary
A systems and operational summary of the Titan 3E/Centaur D-1T program is presented which describes vehicle assembly facilities, launch facilities, and management responsibilities, and also provides detailed information on the following separate systems: (1) mechanical systems, including structural components, insulation, propulsion units, reaction control, thrust vector control, hydraulic systems, and pneumatic equipment; (2) astrionics systems, such as instrumentation and telemetry, navigation and guidance, C-Band tracking system, and range safety command system; (3) digital computer unit software; (4) flight control systems; (5) electrical/electronic systems; and (6) ground support equipment, including checkout equipment.
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