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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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At least 307 records · Page 17
All sourcesNASA NTRSDOE OSTI
NASA NTRS1978

Experimental studies of effects of tilt and structural asymmetry on vibration characteristics of thin-wall circular cylinders partly filled with liquid

The effects of tilt and structural asymmetry on the vibration characteristics of partly liquid-filled thin-wall cylinders were experimentally studied. It was found that tilting the longitudinal axis of a partly filled axisymmetric cylinder from the vertical could markedly reduce its resonant frequencies and change significantly the shape of the circumferential modes. For the minimum frequency modes, vibratory motion occurred only on that side of the cylinder where the liquid was deepest. An empirical equation was derived that gives the equivalent liquid depth of an untilted cylinder having the same minimum resonant frequency as a tilted, partly filled cylinder. Circumferential mode shapes of an untilted asymmetric cylinder were similar to those of the tilted, partly filled axisymmetric cylinder. Vibratory motion in the minimum frequency modes occurred in most instances only on the side of minimum thickness. Correlation between test data and results from a reformulated NASTRAN hydroelastic analysis was excellent.

Herr, R. W.↗
NASA NTRS1983

An analysis of the asymmetric part of electron-electron Boltzmann integral

A numerical analysis of the asymmetric part of electon-electron collision integral is presented. The results are given in the form of graphs for two commonly considered plasma situations: the collision-dominated case (symmetric part of electron disribution is Maxwellian) and the field-dominated case (symmetric part of electron distribution is Druyvesteynian). The importance of the asymmetric part of e-e collision integral in the Boltzmann equation is also discussed.

Kunc, J. A.↗
NASA NTRS1984

An intersection algorithm for moving parts

The problem of deciding whether moving mechanical parts will collide during motion arises frequently in computer-aided design of machinery and in robotics. In machinery design, the problem becomes acute when there are various complex curved mechanical parts that will follow planned trajectories. There is a need to know at an early stage in the design process whether there will be collisions between parts necessitating changes in part shapes, trajectories, or in the overall design. This paper describes a collision detection algorithm that is guaranteed to detect a collision if one will occur, and it also computes the earliest point of contact.

Esterling, D. M.↗
NASA NTRS1987

Filament-Winding Technique for Concave Parts

Dummy mold and vacuum bagging yield accurate part girth. Proposed method of filament winding facilitates accurate fabrication of fiber/matrix composite parts having closed sections with concave surfaces. Parts laid up by hand now wound with filaments; reducing time and cost of fabrication and improving quality of parts.

Carter, Donald↗
NASA NTRS1988

Holding Irregularly Shaped Parts For Machining

Part with complicated, irregular outside contours clamped for precise machining of internal passages with aid of simple method. Exterior of part cast in Rigidex, or equivalent epoxy. Forms wall to be clamped. Interior of part machined to finish of 125 microinches or finer. When machining finished, epoxy melted away by heating part to 200 degree F.

Hilton, Burt W.↗
NASA NTRS1987

Part-task vs. whole-task training on a supervisory control task

The efficacy of a part-task training for the psychomotor portion of a supervisory control simulation was compared to that of the whole-task training, using six subjects in each group, who were asked to perform a task as quickly as possible. Part-task training was provided with the cursor-control device prior to transition to the whole-task. The analysis of both the training and experimental trials demonstrated a significant performance advantage for the part-task group: the tasks were performed better and at higher speed. Although the subjects finally achieved the same level of performance in terms of score, the part-task method was preferable for economic reasons, since simple pretraining systems are significantly less expensive than the whole-task training systems.

Battiste, Vernol↗
NASA NTRS1986

Certification of Ada parts for reuse

One of the claims made by proponents of Ada is that Ada software is highly reusable. The fact that specifications are compiled and accessible would make reusability seem easily achievable. However, specifications give only a limited amount of information about a package; moreover, a specification cannot help determine whether a package worked, or how well it worked. This problem has led to the concept of certifying Ada parts for reuse; that is, determining the worthiness of a part as a reusable component. Issues that are critical to reuse are addressed: the characterization of part performance, design for reuse, and correct utilization of parts. Current areas of study beneficial in the development of a certification process are then addressed.

Hansen, Gregory A.↗
NASA NTRS1990

Transformational part-count in layered octahedral-tetrahedral truss configurations

The number of component part (nodes, struts and panels) termed part count, is an important factor in the design, manufacture, and assembly of modular space structures. Part count expressions are presented for a variety of profiles derived from the layered octahedral-tetrahedral truss configuration. Referred to as the tetrahedral truss in the NASA projects, this specific geometry has been used in several missions. The general expressions presented here transforms to others as one profile changes to another. Such transformational part count relations provide a measure of flexibility and generality, and may be useful when dealing with a wider range of geometric configurations.

Lalvani, Haresh↗
NASA NTRS1990

Reliability and quality EEE parts issues

NASA policy and procedures are established which govern the selection, testing, and application of electrical, electronic, and electromechanical (EEE) parts. Recent advances in the state-of-the-art of electronic parts and associated technologies can significantly impact the electronic designs and reliability of NASA space transportation avionics. Significant issues that result from these advances are examined, including: recent advances in microelectronics technology (as applied to or considered for use in NASA projects); electron packaging technology advances (concurrent with, and as a result of, the development of the advanced microelectronic devices); availability of parts used in space avionics; and standardization and integration of parts activities between projects, centers, and contractors.

Barney, Dan↗
NASA NTRS1991

Comparative morphology of configurations with reduced part count derived from the octahedral-tetrahedral truss

Morphology (the study of structure and form) of the octahedral-tetrahedral (octet) truss is described. Both the geometry and symmetry of the octet truss are considered. Morphological techniques based on symmetry operations are presented which enable the derivation of reduced-part-count truss configurations from the octet truss by removing struts and nodes. These techniques are unique because their Morphological origination and they allow for the systematic generation and analysis of a large variety of structures. Methods for easily determining the part count and redundancy of infinite truss configurations are presented. Nine examples of truss configurations obtained by applying the derivation techniques are considered. These configurations are structurally stable while at the same time exhibiting significant reductions in part count. Some practical and analytical considerations, such as structural performance, regarding the example reduced-part-count truss geometries are briefly discussed.

Lalvani, Haresh↗
NASA NTRS1991

Generation and analysis of reduced-part-count truss geometries for space-based applications

A technique for deriving truss structures with reduced part count from the octahedral-tetrahedral (octet) truss by removal of struts and nodes is described. The technique is based on an understanding of the geometry and symmetry of the octet truss. Six example reduced-part-count structures are analyzed and compared with the parent octet truss with regard to part count, redundancy, mass, and free-free fundamental frequency. Part count reductions of 12 to 37 percent, mass reductions of 7 to 33 percent, and fundamental frequency reductions of 18 to 30 percent are demonstrated. Increases in strut cross-sectional area and truss depth are considered for the purpose of increasing the stiffness of the reduced structures.

Collins, Timothy J.↗
NASA NTRS1993

Characterization and durability testing of plasma-sprayed zirconia-yttria and hafnia-yttria thermal barrier coatings. Part 1: Effect of spray parameters on the performance of several lots of partially stabilized zirconia-yttria powder

Initial experiments conducted on thermal barrier coatings prepared in the newly upgraded research plasma spray facility and the burner rig test facilities are discussed. Part 1 discusses experiments which establish the spray parameters for three baseline zirconia-yttria coatings. The quality of five similar coating lots was judged primarily by their response to burner rig exposure supplemented by data from other sources such as specimen characterizations and thermal diffusivity measurements. After allowing for burner rig variability, although there appears to be an optimum density (i.e., optimum microstructure) for maximum burner rig life, the distribution tends to be rather broad about the maximum. In Part 2, new hafnia-yttria-based coatings were evaluated against both baseline and alternate zirconia-yttria coatings. The hafnia-yttria coatings and the zirconia-yttria coatings that were prepared by an alternate powder vendor were very sensitive to plasma spray parameters, in that high-quality coatings were only obtained when certain parameters were employed. The reasons for this important observation are not understood. Also not understood is that the first of two replicate specimens sprayed for Part 1 consistently performed better than the second specimen. Subsequent experiments did not display this spray order affect, possibly because a chiller was installed in the torch cooling water circuit. Also, large changes in coating density were observed after switching to a new lot of electrodes. Analyses of these findings were made possible, in part, because of the development of a sensitive density measurement technique described herein in detail. The measured thermal diffusivities did not display the expected strong relationship with porosity. This surprising result was believed to have been caused by increased microcracking of the denser coatings on the stainless steel substrates.

Miller, Robert A.↗
NASA NTRS1991

Consultative Committee for Space Data Systems recommendation for space data system standards: Telecommand. Part 2.1: Command operation procedures

This recommendation contains the detailed specification of the logic required to carry out the Command Operations Procedures of the Transfer Layer. The Recommendation for Telecommand--Part 2, Data Routing Service contains the standard data structures and data communication procedures used by the intermediate telecommand system layers (the Transfer and Segmentation Layers). In particular, it contains a brief description of the Command Operations Procedures (COP) within the Transfer Layer. This recommendation contains the detailed definition of the COP's in the form of state tables, along with definitions of the terms used. It is assumed that the reader of this document is familiar with the data structures and terminology of part 2. In case of conflict between the description of the COP's in part 2 and in this recommendation, the definition in this recommendation will take precedence. In particular, this document supersedes section 4.3.3.1 through 4.3.3.4 of part 2.

Source record↗
NASA NTRS1933

Dynamic Breaking Tests of Airplane Parts

The static stresses of airplane parts, the magnitude of which can be determined with the aid of static load assumptions, are mostly superposed by dynamic stresses, the magnitude of which has been but little explored. The object of the present investigation is to show how the strength of airplane parts can best be tested with respect to dynamic stresses with and without superposed static loading, and to what extent the dynamic strength of the parts depends on their structural design. Experimental apparatus and evaluation methods were developed and tried for the execution of vibration-strength tests with entire structural parts both with and without superposed static loading. Altogether ten metal spars and spar pieces and two wooden spars were subjected to vibration breaking tests.

Hertel, Heinrich↗
NASA NTRS1994

Concept of using a benchmark part to evaluate rapid prototype processes

A conceptual benchmark part for guiding manufacturers and users of rapid prototyping technologies is proposed. This is based on a need to have some tool to evaluate the development of this technology and to assist the user in judiciously selecting a process. The benchmark part is designed to have unique product details and features. The extent to which a rapid prototyping process can reproduce these features becomes a measure of the capability of the process. Since rapid prototyping is a dynamic technology, this benchmark part should be used to continuously monitor process capability of existing and developing technologies. Development of this benchmark part is, therefore, based on an understanding of the properties required from prototypes and characteristics of various rapid prototyping processes and measuring equipment that is used for evaluation.

Cariapa, Vikram↗
NASA NTRS1994

Integrating O/S models during conceptual design, part 2

This report documents the procedures for utilizing and maintaining the Reliability & Maintainability Model (RAM) developed by the University of Dayton for the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) under NASA research grant NAG-1-1327. The purpose of the grant is to provide support to NASA in establishing operational and support parameters and costs of proposed space systems. As part of this research objective, the model described here was developed. Additional documentation concerning the development of this model may be found in Part 1 of this report. This is the 2nd part of a 3 part technical report.

Ebeling, Charles E.↗