A method for more efficient use of the 4B voice/data lines with application to the proposed AAP teleprinter
Use of 4B voice/data lines with application to proposed AAP teleprinter
Dotson, W. P., Jr.↗
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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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A proposal concerning terminology in reduced density matrix theory
Proposed terminology for reduced density matrix theory
Harriman, J. E.↗
Evaluation of the LM guidance system performance over the approach terrain of five of the proposed Apollo landing sites - Apollo program
Evaluation of lunar module guidance system performance over approach terrain of five proposed Apollo landing sites
Dyer, D. A.↗
Hypervelocity impact tests on a proposed lunar tug fuel tank configuration
Hypervelocity impact tests to predict meteoritic damage on proposed lunar tug fuel tank configuration
Jex, D. W.↗
The effect of mission attitude timelines on consumables requirements for the proposed shuttle orbiter heat rejection systems
Effect of mission attitude timelines on consumables requirements for proposed shuttle orbiter heat rejection systems
Cunningham, J. E.↗
Proposed techniques for launching instrumented balloons into tornadoes
A method is proposed to introduce instrumented balloons into tornadoes by means of the radial pressure gradient, which supplies a buoyancy force driving to the center. Presented are analytical expressions, verified by computer calculations, which show the possibility of introducing instrumented balloons into tornadoes at or below the cloud base. The times required to reach the center are small enough that a large fraction of tornadoes are suitable for the technique. An experimental procedure is outlined in which a research airplane puts an instrumented, self-inflating balloon on the track ahead of the tornado. The uninflated balloon waits until the tornado closes to, typically, 750 meters; then it quickly inflates and spirals up and into the core, taking roughly 3 minutes. Since the drive to the center is automatically produced by the radial pressure gradient, a proper launch radius is the only guidance requirement.
Grant, F. C.↗
Three proposed B-associations in the vicinity of zeta puppis
There appear to be three loose B associations in the general vicinity of zeta Puppis, all at distances of approximately 300 to 400 parsecs from the sun. Their diameters, perpendicular to the line of sight, are 20 to 50 parsecs, and their separations are of similar size. All three are situated in bright areas of the Gum nebula. The proposed associations A and C lie in the two brightest parts of the nebula. The three associations are not all of the same age. Association C is about 50 million years old, whereas A and B are decidedly younger. The ages of A and B cannot be determined from the present data, as their color-magnitude diagrams show no clear turnoff from the main sequence. Association A may be young enough to qualify as the birthplace of zeta Puppis. There is no other identifiable association in which zeta Puppis can have originated, unless its age is substantially greater than the 3 million years assumed.
Upton, E. K. L.↗
A proposed criterion for aircraft flight in turbulence
A proposed criterion for aircraft flight in turbulent conditions is presented. Subjects discussed are: (1) the problem of flight safety in turbulence, (2) new criterion for turbulence flight where existing ones seem adequate, and (3) computational problems associated with new criterion. Primary emphasis is placed on catastrophic occurrences in subsonic cruise with the aircraft under automatic control. A Monte Carlo simulation is used in the formulation and evaluation of probabilities of survival of an encounter with turbulence.
Porter, R. F.↗
Proposed preliminary criteria for space shuttle access equipment at the operational site
A comparison was made between the methods of access utilized, or proposed, by the military, commercial airlines, and the space shuttle Phase B contractors. The methodology was subjected to consideration for space shuttle use and similarity to current space shuttle access concepts. The Phase B contractor concepts were in turn examined for degree of use of the state-of-the-art and progressive extension of new cost-effective ideas. This comparison disclosed a need for better definition of the criteria/requirements for space shuttle access equipment. Preliminary criteria, needed prior to initiation of the detail design (Phase C/D effort) of ground hardware for the operational site, are presented.
Beck, P. E.↗
A proposed USAF fatigue evaluation program based upon recent systems experience
The United States Air Force has published a document entitled Aircraft Structural Integrity Program. One phase of the program is concerned with the fatigue life certification of all types of military aircraft. The document describes the criteria, analyses, and tests that are necessary in order to satisfy the USAF fatigue life requirement. Some recent and valid criticism has been directed toward the document, particularly the fatigue-life requirements contained in it. Some changes are proposed based on surveys conducted in the United States and abroad as well as some recent systems' experience. The surveys covered both military and civilian organizations. The fatigue certification case histories of selected military and commercial aircraft are presented. The design development element tests, preproduction design verification tests, and full-scale fatigue tests of each are described. A brief status report on the revisions to the MIL-A-008860 series specifications is included.
Haviland, G. P.↗
An analysis of proposed out-of-the-ecliptic-missions for the Helios spacecraft.
A mission analysis study has been performed to consider a proposed follow-on flight to Venus for the Helios spacecraft. The study basically considers a Venus swingby as the means of acquiring the desired extraecliptic trajectory. Several variations of a swingby-plus-propulsion mode have been examined to ascertain where these operational modes may lead to in terms of meeting the stated objectives. It has been found that the concept of a combined velocity boost-plus-swingby mode will produce an inclined trajectory plane satisfying the mission.-
Eades, J. B., Jr.↗
A proposed lunar orbiting gravity gradiometer experiment.
Analysis of the gravity gradiometer developed by Forward and Bell (1970) suggest that an accuracy, in the range 0.1 to 0.5 EU can be expected in a lunar orbiter application. This accuracy will allow gradient anomalies associated with mascons to be mapped with 1% accuracy and should reveal a great deal of new information about the lunar gravity field. The proposed experiment calls for putting such a gradiometer into a closely circular polar orbit at an average height of about 30 km above the lunar surface. This orbit allows the entire lunar surface to be covered in fourteen days, the gradiometer to be checked twice per revolution and results in successive passes above the lunar surface being spaced at about the resolution limit of about 30 km set both by the satellite altitude and instrumental integration time.
Debra, D. B.↗
Spectrophotometry /0.3 to 1.1 micron/ of visited and proposed Apollo lunar landing sites.
The study uses information gained by analysis of the spectral properties of lunar samples in the laboratory, and telescope spectra of over 100 lunar areas, to provide information regarding the composition and mineralogy of each proposed lunar landing site. Attention is given to (1) the presence of pyroxenes which cause an absorption band near 0.95 micron in the lunar reflection spectrum, (2) the proportion of crystalline to glassy material present in the soil which is derived from the slope of the reflectivity curve between 0.4 and 0.7 micron and the strength of the 0.95 micron absorption band, and (3) the presence of Ti(3+) ions in the glasses on the lunar surface, which affects the reflection spectrum at blue and ultraviolet wavelengths.
Mccord, T. B.↗
Absorption profile of a planetary atmosphere - A proposal for a scattering independent determination.
The use of scattering theory to infer atmospheric optical parameters requires the separation of absorption and scattering. It is demonstrated that a gradient flux relation exists that would provide the absorption (altitude) profile independently of scattering and irrespective of the state of polarization of the light field. The relation is derived for an atmosphere of plane-parallel or spherical geometry and for broad (continuum) and narrow (spectral line) frequency bands. The results are shown to hold, in particular, for the polarizations induced by both Rayleigh and Mie scattering in the field. Experimental setups are proposed for each of the cases considered of atmospheric geometry and frequency bandwidth.
Fymat, A. L.↗
Analytical and experimental evaluation of proposed ride comfort criteria
An exploratory study was conducted to evaluate the effectiveness of indices proposed by different investigators to relate vehicle vibrations to passenger comfort. The indices considered included criteria for sinusoidal vibrations, unweighted and weighted amplitude exceedance counts, the integral of the unweighted and weighted power spectral density and absorbed power. These functions were initially examined analytically to determine the manner in which they each weighed vibration amplitude and frequency. Similarities among them are noted. Index values were then computed from measured vibrations and compared with the associated comfort ratings. The data for these comparisons were obtained from ride comfort evaluations of passenger trains.
Vinje, E. W.↗
Change in Land Use in the Phoenix (1:250000) Quadrangle, Arizona Between 1970 and 1972: Successful Use of a Proposed Land Use Classification System
Change in land use in the Phoenix Quadrangle, Arizona between 1970 and 1972 - successful use of a proposed land use classification system
Place, J. L.↗
The staging dynamics of a proposed space shuttle configuration
A mathematical model was developed to simulate the staging dynamics of a proposed space shuttle configuration. Included in the mathematical model is the kinematics and dynamics of the staging mechanism, thrust forces and thrust vector control, rigid-body dynamics, and structural dynamics of both the booster and orbiter stages of the configuration. The mathematical model was incorporated into a computer program so that the staging maneuver could be simulated. Results of the simulations are presented.
Hamilton, D. A.↗
A proposed experimental method for interpreting Doppler effect measurements and determining their precision
The principal problem in the measurement of the Doppler reactivity effect is separating it from the thermal reactivity effects of the expansion of the heated sample. It is shown in this proposal that the thermal effects of sample expansion can be experimentally determined by making additional measurements with porous samples having the same mass and/or volume as the primary sample. By combining these results with independent measurements of the linear temperature coefficient and the computed temperature dependence of the Doppler coefficient the magnitude of the Doppler coefficient may be extracted from the data. These addiational measurements are also useful to experimentally determine the precision of the reactivity oscillator technique used to measure the reactivity effects of the heated sample.
Klann, P. G.↗