Computer analysis of space power systems for mission analysis.
Space power systems analysis, using computer program to correlate systems characteristics with mission parameters for automated satellite repair vehicle and space stations
Arno, R. D.↗
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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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Numerical analysis of shells. Volume 1 - Unsymmetric analysis of orthotropic reinforced shells of revolution
Analysis of thin orthotropic shells of revolution subjected to unsymmetric loading - Vol. 1
Svalbonas, V.↗
Optimized Cost/Performance Design Methodology: Volume 3 - Concept Analysis and Model Development, Book 1 - Concept Analysis
Concept analysis for optimized cost orbital space transportation system
Source record↗
Wake analysis for supersonic decelerator applications. Volume 1 - Theoretical analysis and correlation of wind-tunnel and shallow-water tow channel results
Wake analysis and correlation of wind tunnel and shallow water tow channel data
Lau, R. A.↗
Synthesis of calculational methods for the design and analysis of radiation shields for nuclear rocket systems. Volume 2 - Analysis of radiation measurements in a nuclear rocket propellant tank mockup using simulated liquid hydrogen
Calculational methods for nuclear rocket radiation shield design - analysis of radiation measurements in nuclear rocket propellant tank mockup using simulated liquid hydrogen
Disney, R. K.↗
Thermal degradation analysis of polymeric materials by combined mass spectrometric and thermogravimetric analysis
Polymeric materials thermal degradation kinetic parameters using combined mass spectrometric and thermogravimetric analysis /MS-TGA/
Hamaker, F. M.↗
A study of differential thermal analysis /DTA/ - Effluent gas analysis /EGA/ for the determination of planetary environmental parameters
Differential thermal analysis capabilities in mineralogy for determining present/past planetary environmental parameters having significance for biological experiment
Bollin, E. M.↗
Analysis of folding strains on composite bladder structures. Volume 2 - Programming manual. Folding strains analysis program
Computer program for analysis of folding strains on composite bladder structures
Taylor, J. R.↗
Dynamic data analysis techniques used in the Langley times series analysis computer program
User guide for Langley time series analysis computer program used in analyzing random, stationary time series
Ward, R. C.↗
Space station (modular) mission analysis. Volume 1: Mission analysis
The mission analysis on the modular space station considers experimental requirements and options characterized by low initial cost and incremental manning. Features that affect initial development and early operating costs are identified and their impacts on the program are assessed. Considered are the areas of experiment, mission, operations, information management, and long life and safety analyses.
Source record↗
Design, analysis, and tests of a structural prototype Viking aeroshell. I - Aeroshell design and analysis. II - Test procedure and test results.
Two near optimum full-scale Viking aeroshell prototypes (140 deg ring-stiffened conical shells), differing only in base ring size, were designed and tested under uniform pressure to buckling failure. Part I describes the computerized design procedure which iterates between a design program based on approximate equations to determine skin and ring gages and ring spacings, and a sophisticated system of shell of revolution programs for more accurate analysis as a basis for redesign. Part II discusses fabrication techniques, test procedures, and test results. Both buckling and prebuckling data are compared with the theoretical predictions of Part I. Appropriate buckling knockdown factors for this type of construction are identified. Measured strains in skin and rings agreed well with theoretical predictions and the buckling pressure was in close agreement with the design ultimate pressure.
Heard, W. L., Jr.↗
Space tug economic analysis study. Volume 2: Tug concepts analysis. Appendix: Tug design and performance data base
The tug design and performance data base for the economic analysis of space tug operation are presented. A compendium of the detailed design and performance information from the data base is developed. The design data are parametric across a range of reusable space tug sizes. The performance curves are generated for selected point designs of expendable orbit injection stages and reusable tugs. Data are presented in the form of graphs for various modes of operation.
Source record↗
Space shuttle/payload interface analysis (study 2.4). Volume 2: Space shuttle traffic analysis
The transfer is reported of the capability to perform capture/cost analyses to MSFC. Space shuttle performance and direct costs, tug characteristics, reliability, and cost data were provided by NASA. The launch vehicle, mission models, payloads, and computer programs are discussed along with capture/cost analysis, and cost estimates. For Vol. 1, see N74-12493.
Plough, J. A.↗
Frequency modulation television analysis: Threshold impulse analysis
A computer program is developed to calculate the FM threshold impulse rates as a function of the carrier-to-noise ratio for a specified FM system. The system parameters and a vector of 1024 integers, representing the probability density of the modulating voltage, are required as input parameters. The computer program is utilized to calculate threshold impulse rates for twenty-four sets of measured probability data supplied by NASA and for sinusoidal and Gaussian modulating waveforms. As a result of the analysis several conclusions are drawn: (1) The use of preemphasis in an FM television system improves the threshold by reducing the impulse rate. (2) Sinusoidal modulation produces a total impulse rate which is a practical upper bound for the impulse rates of TV signals providing the same peak deviations. (3) As the moment of the FM spectrum about the center frequency of the predetection filter increases, the impulse rate tends to increase. (4) A spectrum having an expected frequency above (below) the center frequency of the predetection filter produces a higher negative (positive) than positive (negative) impulse rate.
Hodge, W. H.↗
Sensitivity analysis of torsional vibration characteristics of helicopter rotor blades. Part 2: Aerodynamics and sensitivity analysis
A theoretical investigation of dynamic response characteristics of rotor blades was carried out with special emphasis on torsional degrees-of-freedom. Coupled equations of motion for flapwise bending and torsion were formulated at varying azimuth positions for rotor blades with noncollinear aerodynamic, elastic and mass axes. Both structural and aerodynamic mass, damping and stiffness coefficients were included. The variations of a sample blade at different flight conditions were investigated from these equations. The obtained numerical results were illustrated. The sensitivity of overall blade vibration characteristics to torsional oscillations was also investigated from the equations of motion for the sample blade. The illustrated results show the importance of torsional degrees-of-freedom in rotor blade analysis. Various possibilities of improving the overall response by tuning blade geometric, structural and aerodynamic characteristics are discussed.
Bratanow, T.↗
Correaltion of full-scale drag predictions with flight measurements on the C-141A aircraft. Phase 2: Wind tunnel test, analysis, and prediction techniques. Volume 1: Drag predictions, wind tunnel data analysis and correlation
The degree of cruise drag correlation on the C-141A aircraft is determined between predictions based on wind tunnel test data, and flight test results. An analysis of wind tunnel tests on a 0.0275 scale model at Reynolds number up to 3.05 x 1 million/MAC is reported. Model support interference corrections are evaluated through a series of tests, and fully corrected model data are analyzed to provide details on model component interference factors. It is shown that predicted minimum profile drag for the complete configuration agrees within 0.75% of flight test data, using a wind tunnel extrapolation method based on flat plate skin friction and component shape factors. An alternative method of extrapolation, based on computed profile drag from a subsonic viscous theory, results in a prediction four percent lower than flight test data.
Macwilkinson, D. G.↗
Trace-element analysis of 1000 environmental samples per year using instrumental neutron activation analysis
The technology and methods developed at the Plum Brook Reactor to analyze 1000 samples per year and report data on as many as 56 elements are described. The manpower for the complete analysis of 20 to 24 samples per week required only 3 to 3.5 hours per sample. The solutions to problems encountered in sample preparation, irradiation, and counting are discussed. The automation of data reduction is described. Typical data on various sample matrices are presented.
Sheibley, D. W.↗
Space shuttle vehicle rocket plume impingement study for separation analysis. Tasks 2 and 3: Definition and preliminary plume impingement analysis for the MSC booster
The results are presented of a space shuttle plume impingement study for the Manned Spacecraft Center configuration. This study was conducted as two tasks which were to (1) define the orbiter main stage engine exhaust plume flow field, and (2) define the plume impingement heating, force and resulting moment environments on the booster during the staging maneuver. To adequately define these environments during the staging maneuver and allow for deviation from the nominal separation trajectory, a multitude of relative orbiter/booster positions are analyzed which map the region that contains the separation trajectories. The data presented can be used to determine a separation trajectory which will result in acceptable impingement heating rates, forces, and the resulting moments. The data, presented in graphical form, include the effect of roll, pitch and yaw maneuvers for the booster. Quasi-steady state analysis methods were used with the orbiter engine operating at full thrust. To obtain partial thrust results, simple ratio equations are presented.
Wojciechowski, C. J.↗