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Method extends scope of ion plating technique to include deposition of alloy films without changing composition of plating alloy. Coatings flow with specimen material without chipping or peeling. Technique is most effective vacuum deposition method for depositing alloys for strong and lasting adherence.
Investigating symbolic mathematical computation using PL/1 FORMAC batch system and Scope FORMAC interactive system
The use of free flight models for transonic testing at high Reynolds numbers is discussed. Several specific examples of experimental investigations are briefly reviewed to illustrate the scope of research that can be conducted by utilizing the advantages of free flight models. These advantages are primarily the lack of interference or constraints imposed by test facilities and model support systems and the dynamic freedom possessed by free flight models. High Reynolds numbers are obtained by using large models flown at relatively low altitudes. It is shown that models 10 meters or more in length will be required for research at Reynolds numbers sufficiently high to provide representative simulation of flow conditions for large modern aircraft. Several methods for launching models of this size are discussed. These methods include free drops from airplanes or balloons and ground launches with the use of internal or external rocket motors. All the launching methods discussed have been successfully demonstrated on flight vehicles of the size and weight required to attain the necessary test conditions.
The feasibility of performing inventories of agricultural resources using very small scale aerial or space photography was studied. The results were encouraging on two counts: (1) The very practical problems of an operational survey are being faced and solutions are being found. (2) It seems that a fully operational agricultural inventory using space photography is not beyond the scope of present technology.
The characteristics and capabilities are described of solar electric propulsion (SEP) for performing Mars Surface Sample Return (MSSR) missions. The scope of the study emphasizes trajectory/payload analysis and the comparison of mission/system tradeoff options. The MSSR mission is examined only for the 1981-82 launch opportunity. Several other study constraints which bear directly on the results obtained are: (1) return samples in the range 5-25 kg, (2) use of lifting (offset C.G.) atmospheric entry at Mars which allows a low ratio (1.25) of entry weight to landed weight, and (3) rendezvous and docking in Mars orbit. Major results of the study are presented as performance curves of earth departure mass versus sample size for a number of different mission/system options. These options represent a spectrum of trip time, launch vehicle capability, combinations of low-thrust and ballistic maneuvers, chemical retro type, and earth recovery mode.
The NASA THESAURUS - ALPHABETICAL UPDATE is an alphabetical listing of all subject terms (postable and nonpostable) that are currently approved for use in the NASA scientific and technical information system. Contained in the listing are the subject terms that were listed in the Preliminary Edition of the NASA THESAURUS and the additional subject terms that were approved during the period January 1, 1967 June 30, 1971. Complete Thesaurus structuring, including scope notes, category assignments, and cross-references, is provided for each term as appropriate.
The space shuttle fact sheet is presented. Four important reasons for the program are considered to be: (1) It is the only meaningful new manned space program which can be accomplished on a modest budget. (2) It is needed to make space operations less complex and costly. (3) It is required for scientific applications in civilian and military activities. (4) It will encourage greater international participation in space flight. The space shuttle and orbiter configurations are discussed along with the missions. The scope of the study and the costs of each contract for the major contractor are listed.
This handbook is intended to provide theory and data needed by the thermal design engineer to bridge the gap between research achievements and actual flight systems, within the limits of the current state of the art of phase change materials (PCM) technology. The relationship between PCM and more conventional thermal control techniques is described and numerous space and terrestrial applications of PCM are discussed. Material properties of the most promising PCMs are provided; the purposes and use of metallic filler materials in PCM composites are presented; and material compatibility considerations relevant to PCM design are included. The engineering considerations of PCM design are described, especially those pertaining to the thermodynamic and heat transfer phenomena peculiar to PCM design. Methods of obtaining data not currently available are presented. The special problems encountered in the space environment are described. Computational tools useful to the designer are discussed. In summary, each aspect of the PCM problem important to the design engineer is covered to the extent allowed by the scope of this effort and the state of the art.
Results of a pitot pressure investigation of the flow field on the lee side of a delta wing shuttle orbiter are presented. The results delineate the extent of the lee side separated flow and give a tentative cross sectional definition to the shock wave structure for angles of attack of 15 deg and 30 deg. It is shown that while, in general, the effects of Reynolds number on the flow field are not large, detailed effects are observed that may have significant bearing on the heating estimate. Two examples are cited for an angle of attack of 15 deg; these are: (1) The scope of the vertical tail exposed to the unseparated flow increases with increasing Reynolds number and (2) the depth of the separated flow adjacent ot where the bow wave crosses the wing appears to decrease with increasing Reynolds number. In addition, it is shown that at a spanwise station outboard of the wing-fuselage juncture, increasing Reynolds number decreased the pitot pressure in the unseparated flow. This defect of pitot pressure appears associated with the flow over the wing-fillet-fuselage juncture.
A computer program to analyze Mossbauer data is presented in detail. The least-squares curve fitting techniques described apply to single line spectra, single hyperfine spectra, or when the constituent spectra are separated well enough to let the individual absorption peaks stand alone. The present program is not adapted for complex spectra resulting from the existence of several local environments in the absorber iron alloy. Sample problems are presented to aid the user in setting up and running the program. The program is written in FORTRAN 4 language for the Control Data 6000 series digital computer with the SCOPE 3.0 operating system and requires approximately 115,000 octal locations of core storage. A typical case with one absorption peak runs in 20 seconds, and a typical problem with six absorption peaks requires 50 seconds.
This index is intended to serve as a ready reference tool for the names, places and events that comprise the history of John F. Kennedy Space Center. The period covered is December 1962 through February 1972. The arrangement is alphabetical by subject; under each subject, entries are arranged alphabetically by title. To facilitate use, cross references and scope notes have been provided.
The application of tracking radar for determining the flight paths of migratory birds is discussed. The effects produced by various meteorological parameters are described. Samples of radar scope presentations obtained during tracking studies are presented. The characteristics of the radars and their limitations are examined.
The Apollo real time auxiliary computing function and facility were an extension of the facility used during the Gemini Program. The facility was expanded to include support of all areas of flight control, and computer programs were developed for mission and mission-simulation support. The scope of the function was expanded to include prime mission support functions in addition to engineering evaluations, and the facility became a mandatory mission support facility. The facility functioned as a full scale mission support activity until after the first manned lunar landing mission. After the Apollo 11 mission, the function and facility gradually reverted to a nonmandatory, offline, on-call operation because the real time program flexibility was increased and verified sufficiently to eliminate the need for redundant computations. The evaluation of the facility and function and recommendations for future programs are discussed in this report.
The means are discussed by which the the United States Army Board for Aviation Accident Research (USABAAR) now utilizes the vast store of historical accident data in the application of the system safety concept for developmental aircraft. USABAAR serves as the central agency for the Army Accident Prevention Program which includes the receipt, processing, and analysis of all data and information related to Army aircraft accident experience. It is pointed out that methods which served the cause of accident prevention so well in the past are no longer adequate and that traditional parameters used to measure mishap experience have become obsolete. USABAAR has developed, and recently put into use, completely revised accident reporting forms which greatly expand the scope and detail of information provided as a result of investigation. This and other factors which have resulted in an improved data system are discussed in detail.
The objectives and scope of the Chesapeake Bay study are discussed. The physical, chemical, biological, political, and social phenomena of concern to the Chesapeake Bay area are included in the study. The construction of a model of the bay which will provide a means of accurately studying the interaction of the ecological factors is described. The application of the study by management organizations for development, enhancement, conservation, preservation, and restoration of the resources is examined.
A study was conducted to develop the means to identify skills required of scientist passengers on advanced missions related to the space shuttle and RAM programs. The scope of the study was defined to include only the activities of on-orbit personnel which are directly related to, or required by, on-orbit experimentation and scientific investigations conducted on or supported by the shuttle orbiter. A program summary is presented which provides a description of the methodology developed, an overview of the activities performed during the study, and the results obtained through application of the methodology.
The investigation in a laboratory controlled environment was of the structure of the water surface and the immediate layers above and below the surface. The scope included: (1) the investigation of the capillary waves and their interaction with gravity waves, (2) the formation of whitecaps at different wind speeds and the influence of gravity waves on whitecaps, and (3) the wind-generated spray under different wind and wave conditions.
A summary of the materials property information for aluminum alloy 5456 is presented. The scope of the information includes physical and mechanical property data at cryogenic, ambient, and elevated temperatures. Information on material procurement, metallurgy of the alloy, corrosion, environmental effects, fabrication, and joining techniques is developed.