Weekly synoptic analyses 5-, 2-, and 0.4-millibar surfaces for 1968 (based on meteorological rocketsonde and high level rawinsonde observations)
Using rocketsonde and rawinsonde data to analyze high altitude synoptic charts
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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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Electric quadrupole transitions in muonic Pb208
Electric quadrupole atomic transitions in muonic PB208, charting X ray spectrum showing transitions
Jenkins, D. A.↗
Infrared studies of the lunar terrain. I - The background moon
Unlit lunar limb observations at IR wavelengths, presenting temperature charts and thermal abnormalities
Allen, D. A.↗
The design of a weather satellite for the radiation environment - A case history
Spacecraft systems radiation hardening design, discussing Tiros satellite mission hazards and space exposure prediction for electronic parts, using flow chart rationale
Holmes-Siedle, A. G.↗
Design of distributed-active RC filters
Distributed active RC filters design for low pass, bandpass and biquadratic network functions, including charts for element values determination
Huelsman, L. P.↗
Lubricant selection for gear designers
Guide for gear designers, consisting of theory, calculations, charts, curves and references, explains lubrication requirements for gears to insure maximum performance. Mechanical and service variables are considered in order to obtain optimum gear performance under severe operating conditions.
Townsend, D. P.↗
A method for calculating the effects of design errors and measurement errors on pump performance
Technique has been developed for calculating effects of design errors and measurement errors on pump performance. Error equations and charts are utilized to relate amount of error in given performance parameter to amount of error in given design or measured variable. Error equations were derived primarily for axial flow pumps, but are not limited to axial flow.
Anderson, D. A.↗
Experiment S026: Ion wake measurement
Measurements of the ion-wake and electron-wake structure and other perturbations of the ambient medium produced by the Gemini spacecraft in orbit are reported. Thruster firings in the TDA-south configuration produced a decrease in the observed ion flux to the outboard ion sensor, an apparent increase in the ion flux to the inboard ion sensor, and an enhanced electron concentration to the outboard electron sensor. Visual inspection of strip-chart data was indicative that definitive wake-cone angles could be determined. It also was apparent for many cases that the electron distribution followed the ion depletion effects; this was indicative that the wake was a plasma, not an ion wake. Analysis of the data from the GATV orbits was indicative that electron and ion temperatures were higher than was estimated. The high electron temperature accounted for the sensor saturation observed during the mission. This temperature measurement was 0.3 electron volt at a 200-n. mi. altitude during daytime conditions. Spacecraft wake structure has been observed as far as 100 feet from the vehicle.
Medved, D. B.↗
Digital autopilots: Design considerations and simulator evaluations
The development of a digital autopilot program for a transport aircraft and the evaluation of that system's performance on a transport aircraft simulator is discussed. The digital autopilot includes three axis attitude stabilization, automatic throttle control and flight path guidance functions with emphasis on the mode progression from descent into the terminal area through automatic landing. The study effort involved a sequence of tasks starting with the definition of detailed system block diagrams of control laws followed by a flow charting and programming phase and concluding with performance verification using the transport aircraft simulation. The autopilot control laws were programmed in FORTRAN 4 in order to isolate the design process from requirements peculiar to an individual computer.
Osder, S.↗
Mobility systems activity for lunar rovers at MSFC
The Apollo Lunar Roving Vehicle (LRV) mobility system is described. Special emphasis is given to the redundancy aspects and to the selection of the drive motors. A summary chart of the performance on the lunar surface during the Apollo 15 flight is included. An appendix gives details on some development work on high efficiency drive systems and compares these systems to the selected system.
Jones, C. S., Jr.↗
An inventory of aeronautical ground research facilities. Volume 1: Wind tunnels
A survey of wind tunnel research facilities in the United States is presented. The inventory includes all subsonic, transonic, and hypersonic wind tunnels operated by governmental and private organizations. Each wind tunnel is described with respect to size, mechanical operation, construction, testing capabilities, and operating costs. Facility performance data are presented in charts and tables.
Pirrello, C. J.↗
An inventory of aeronautical ground research facilities. Volume 3: Structural
An inventory of test facilities for conducting acceleration, environmental, impact, structural shock, load, heat, vibration, and noise tests is presented. The facility is identified with a description of the equipment, the testing capabilities, and cost of operation. Performance data for the facility are presented in charts and tables.
Pirrello, C. J.↗
Methodologies for optimal resource allocation to the national space program and new space utilizations. Volume 2: Resource allocation and smoothing model, programmer's manual
Appendixes are presented that provide model input requirements, a sample case, flow charts, and a program listing. At the beginning of each appendix, descriptive details and technical comments are provided to indicate any special instructions applicable to the use of that appendix. In addition, the program listing includes comment cards that state the purpose of each subroutine in the complete program and describe operations performed within that subroutine. The input requirements includes details on the many options that adapt the program to the specific needs of the analyst for a particular problem.
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Observations of earth eigen vibrations possibly excited by low frequency gravity waves
A cryogenic gravity meter made of two parts, a magnetic suspension unit and a detection module, was used to monitor earth eigen vibrations. The magnetic field and field gradient are generated by energizing a set of superconducting coils made of niobium-zirconium alloy wire. The detection module is a double Josephson junction magnetometer. The output is printed on a chart recorder and later digitized using a computer; a Fourier transformation is performed on the accumulated data. The measurements of eigen vibrations are summarized in tabular and graphical representations.
Tuman, V. S.↗
Skylab RTCC mass properties system requirements
The computation equations and flow charts are presented for the Real Time Computer Complex mass properties system for computing and maintaining weight and centers of gravity for the CSM and orbital assembly, and SPS engine trim angles.
Hischke, E. R.↗
Recent progress on the Yale zone catalogues
The measurement or reduction of stars in southern zones is reported. The catalog for the -35 deg to -40 deg zone is rapidly nearing completion. All the reductions and comparisons with other catalogs have been completed. The tables and star charts are being prepared in final form for publication.
Hoffleit, D.↗
Flow field analysis of aircraft configurations using a numerical solution to the three-dimensional unified supersonic/hypersonic small disturbance equations, part 1
The unified small disturbance equations are numerically solved using the well-known Lax-Wendroff finite difference technique. The method allows complete determination of the inviscid flow field and surface properties as long as the flow remains supersonic. Shock waves and other discontinuities are accounted for implicity in the numerical method. This technique was programed for general application to the three-dimensional case. The validity of the method is demonstrated by calculations on cones, axisymmetric bodies, lifting bodies, delta wings, and a conical wing/body combination. Part 1 contains the discussion of problem development and results of the study. Part 2 contains flow charts, subroutine descriptions, and a listing of the computer program.
Gunness, R. C., Jr.↗
Characteristics of hingeless rotors with hub moment feedback controls including experimental rotor frequency response, Volume 2
The test obtained from wind tunnel tests of a rigid rotor with hub feedback controls are presented. Four types of tests were conducted and the data from each are presented in separate appendices. The data are presented in the form of tables and charts.
Kuczynski, W. A.↗