On the heat flux from the moon's interior o potoke tepla iz nedr luny
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Fluid controlled solid rocket motor using fully oxidized solid propellant grain configured with oversized nozzle throat area
Microbiological techniques for recovering trapped microorganisms from solids for use in spacecraft sterilization program
Size and weight evaluation of insulated cylindrical radiators used in SNAP-8 heat rejection system
Chemical composition of iron-rich spherules of meteoritic, volcanic, and unknown origin
Diopside, peridot and oligoclase optical constants found by measuring reflectance and transmittance spectra at high temperatures
Axisymmetric stationary type-D solution of Einstein field equation representing superposition of Kerr-NUT metric on rigidly rotating perfect fluid
Design and performance of seal test equipment
The development of very large size solid rocket engines cannot be accomplished, as in the case of small rocket engines, by empirical methods requiring a great number of full-scale firings. It is therefore necessary to predict rocket operation from data obtained on charges of different size and geometry. This paper presents a mathematical method for determining analytically the rocket engine thrust and chamber pressure development curves from the charge and engine geometry, the heat of explosion the kinetics characteristics and any other parameters affecting engine operation. It is shown that it is possible to compute empirical values for burning rate and erosion effects from experimental firings. Following a brief survey of the fundamentals of this method, the procedure is illustrated by four representative examples.
Autoionization lines effect on stellar structure by computing contributions to Rosseland mean opacity
Lunar surface magnetometer measurements for determining electrical conductivity and temperature of lunar core
Underwater research in ocean floor habitat for 60 day evaluation of supporting facilities at Virgin Islands for Tektite 1 project
Transfer functions for calculating coupled acoustic/elastic response of structure to sonic boom
Modulated beams of 0(+), Ar(+), and Kr(+) in the 100-300 eV range are directed into a copper box simulating the ante-chamber of an orbiting mass spectrometer. An RF quadrupole mass spectrometer and phase sensitive detection extract the component of the internal mass spectrum correlated with the beam. Intense Ar and Kr signals are observed; however, no O or O2 is detectable, indicating loss of the primary O(+) beam to surface interactions. All four primary ions stimulate sizeable signals at masses 26 and 28. The relevance of these experiments to the interpretation of mass spectra obtained by orbiting satellites is discussed.
There are no author-identified significant results in this report.
Published models for the moon's thermal history typically imply present day central temperatures far too high to be consistent with the recently proposed lunar temperature profile of Sonett et al. (1971). Furthermore, chemical data on Apollo samples show that the moon is depleted relative to chondrites in volatile elements, and possibly enriched relative to chondrites in refractory elements. Additional thermal models have therefore been investigated in order to set upper limits on lunar radioactivity consistent with the proposed temperature distribution. For an initially cold, uniform moon, devoid of potassium, a maximum uranium content of 23 parts per billion is inferred.
Discussion of the determination possibilities and requirements for certain crucial inertia-moment and radial-mass-distribution parameters of Mercury. It is shown that the high precision of 1 min of arc, which reasonable bounds on some of these parameters demand, cannot be obtained by either earth-based observations or the television imagery of the Mariner 73 flyby. Some methods are proposed for both landers and orbiters that could determine unambiguously most of these parameters.
The author has identified the following significant results. A reconstituted color infrared image covering the western Seward Peninsula was used for identifying vegetation types by simple visual examination. The image was taken by ERTS-1 approximately 1120 hours on August 1, 1972. Seven major colors were identified. Four of these were matched with four units on existing vegetation maps: bright red - shrub thicket; light gray-red - upland tundra; medium gray-red - coastal wet tundra; gray - alpine barrens. In the bright red color, two phases, violet and orange, were recognized and tentatively ascribed to differences in species composition in the shrub thicket type. The three colors which had no map unit equivalents were interpreted as follows: pink - grassland tundra; dark gray-red - burn scars; light orange-red - senescent vegetation. It was concluded that the image provides a considerable amount of information regarding the distribution of vegetation types, even at so simple a leval of analysis. It was also concluded that sequential imagery of this type could provide useful information on vegetation fires and phenologic events.