The analytical aerotriangulation of the Apollo 10 Hasselblad photography Final report
Analytical aerotriangulation of Apollo 10 Hasselblad photographs of moons far side
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Analytical aerotriangulation of Apollo 10 Hasselblad photographs of moons far side
Design considerations for development of operational super-pressure balloon system to carry 50 pounds to 10 millibar atmospheric pressure
Lunar geology, crater, and volcanic feature analysis from Apollo 10 visual observations and photointerpretations
Lunar photographs from Apollo 8, 10, and 11, flights
Tilt angle dependence of 10 MeV proton cutoff lattitudes in image dipole model magnetosphere
Interplanetary space He 3 differential energy spectrum in 10-30 MeV range from IMP 4 satellite observations, noting solar contributions
Solar flare electrons at 10-200 MeV region, discussing energy spectra and time history
Twilight helium 10,830 A emission observations and calculations, using grille spectrometer
Stored arc heated air true temperature, flight and altitude simulation facility in Mach number 8 to 10 region for air breathing propulsion research
Nonthermal X rays and 10-100 KeV electron acceleration and emission from solar flares, using spacecraft observations
Gamma ray emission from individual interactions of hadrons in carbon at 10 TeV, using ionization spectrometer-emulsion chamber combination
SNAP 8 turbine-alternator as nuclear-electric space power converter, discussing rotating machinery components design and 10,000 hr endurance testing results
Cosmic ray nuclear interactions in 10-300 GeV energy range, using balloon-borne emulsion target, spark chambers and ionization spectrometer
Microprobe measurements of rare gas composition for lunar rock 12013,10,31 mineral separates, noting cosmic ray bombardment role in K and Ar production
An ionization spectrometer consisting of 10.8 radiation lengths of tungsten and 35 radiation lengths of iron has been used to determine the energy spectrum of cosmic ray electrons above 10 GeV. The spectrometer was calibrated with electrons from 5.4 to 18 GeV and then flown at an altitude of 6 gm-cm/2 for 16 hours. Separation of electron initiated events from proton events was achieved by utilizing starting point distributions, the shower development in tungsten, and the energy deposited in the large thickness of iron absorber. The exponent of the differential energy spectrum of the electrons is -3.1 + or - 0.2 while the exponent of the background is consistent with the proton exponent of -2.7 + or -0.2.
A study of the motor starting of a Brayton cycle power system was conducted to provide estimates of system sensitivity to several controllable parameters. These sensitivity estimates were used as a basis for selection of an optimum motor-start scheme to be implemented on the 2- to 10-kilowatt Brayton power system designed and presently under test. The studies were conducted with an analog simulation of the Brayton power system and covered a range of frequencies from 400 Hz (33 percent design) to 1200 Hz (design), voltage-to-frequency ratios of 0.050 (50 percent design) to 0.100 (design), turbine-inlet temperatures of 800 K (1440 R, 70 percent design) to 1140 K (2060 deg R, design), and prestart pressure levels of 14.5 psia to 29.0 psia. These studies have shown the effect of selected system variables on motor starting. The final selection of motor-start variables can therefore be made on the basis of motor-start inverter complexity, battery size and weight, desired steady-state pressure level after startup, and other operational limitations. In general, the study showed the time required for motor starting to be inversely proportional to motor frequency, voltage, turbine-inlet temperature, and pressure level. An increase in any of these parameters decreases startup time.
Both the anisotropic and isotropic diffusion theories can be used to extrapolate proton fluxes for E greater than or equal to 10 meV for over 50% of the particle events. The isotropic diffusion theory uses a diffusion coefficient: D = Mr sup beta. It was found that M and beta tended to be functions of flare position on the solar disk. A measurement of the interplanetary flux in near earth space gives a good indication of the polar cap fluxes. It was found that the 30 MHz absorption over the poles during a PCA is proportional to the square root of the integral proton flux E greater than or equal to 11 meV in interplanetary space, J = KA squared, with K = 8 plus or minus 2 and J in protons/sq cm-sec-ster.
The conceptual design of a highly reliable 10 to the 8th power-bit bubble domain memory for the space program is described. The memory has random access to blocks of closed-loop shift registers, and utilizes self-contained bubble domain chips with on-chip decoding. Trade-off studies show that the highest reliability and lowest power dissipation is obtained when the memory is organized on a bit-per-chip basis. The final design has 800 bits/register, 128 registers/chip, 16 chips/plane, and 112 planes, of which only seven are activated at a time. A word has 64 data bits +32 checkbits, used in a 16-adjacent code to provide correction of any combination of errors in one plane. 100 KHz maximum rotational frequency keeps power low (equal to or less than, 25 watts) and also allows asynchronous operation. Data rate is 6.4 megabits/sec, access time is 200 msec to an 800-word block and an additional 4 msec (average) to a word. The fabrication and operation are also described for a 64-bit bubble domain memory chip designed to test the concept of on-chip magnetic decoding. Access to one of the chip's four shift registers for the read, write, and clear functions is by means of bubble domain decoders utilizing the interaction between a conductor line and a bubble.