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Results of a search for primary cosmic-ray antinuclei with charges 2 less than or equal to Z less than or equal to 26 with rigidities above 5 GV/c using a second-generation superconducting magnetic spectrometer with an average bending power of 5.1 kG-m. The addition of new data doubles the sample of cosmic-ray nuclei previously reported and greatly increases the percentage of the more highly charged nuclei.
Large areas of nuclear emulsions and plastic detectors were exposed to the primary cosmic radiation during high-altitude balloon flights. From an analysis of 141 particle tracks recorded during a total exposure of 13,000,000 sq m-ster-sec, a charge spectrum of the VVH particles has been derived.
A magnetic spectrometer and lead-plate spark chamber have been used to measure separate primary cosmic-ray electrons and positrons up to 50 GeV. Separation of these particles from the background was accomplished with a new technique combining both selective trigger and observation, in the lead-plate chamber, of bremsstrahlung photons that were created in a thin radiator placed above the spectrometer. The results of efficiency and rejection calibrations with accelerator tests and Monte Carlo calculations are presented, as well as preliminary data from a balloon-flight exposure of the apparatus.
We have performed a comparative study of the absolute solar modulation of cosmic-ray positrons and electrons. We find that the interstellar electron spectrum, which is described by a power-law slope at higher energies, must flatten below about 100 MeV, that a significant fraction of interstellar cosmic-ray electrons must originate in primary sources, and that the rigidity dependence of the interplanetary cosmic-ray diffusion coefficient, R raised to the power of alpha, changes from alpha greater than zero at higher rigidities to alpha -1 below about 60 MV.
Data on the primary electron spectrum from 5 MeV to 30 GeV are presented for a large number of balloon flights in the years 1965-1972. A new much larger area electron telescope was introduced to these studies in 1971 and the results from this new telescope are given and compared with earlier results. Detailed electron spectra are presented and the effects of solar modulation are examined over a wide energy range. The phase lag or hysteresis in the electron intensity observed after 1969 is also examined between 40 MeV and 1 GeV.
A somewhat phenomological overview of the hydrogen embrittlement process, both internal as well as external, is presented in a effort to make more clear the type of parameters which must be considered in the selection of a test method and test procedure so that the resulting data may be meaningfully applied to real engineering structures. What are believed to be the three primary influences on the embrittlement process are considered - the original location and form of the hydrogen, the transport reactions involved in the transport of hydrogen from its origin to some point it can interact with the metal to cause embrittlement, and the embrittlement interaction itself. Additionally, a few of the large number of secondary influences on the embrittlement process are discussed, for example, the influence of impurity species in the environment, surface hydride films, and surface oxide films.
The fabrication of prototype titanium alloy primary and secondary mirror support structures for a proposed experimental three-meter space telescope is discussed. The structure was fabricated entirely of Ti-6Al-4V tubing and plate. Fabrication included the development of procedures including welding, forming, and machining. Most of the structures was fabricated by gas-shielding tungsten-arc (GTA) welding with several major components fabricated by high frequency resistance (HFR) welding.
In previous studies it has been shown that a good case can be made for supposing that a large fraction of the primary cosmic rays is of extra-galactic origin. These ideas are reviewed here, and the most recent observations and theoretical suggestions bearing on the problem are described.
A review is presented of the current status of primary propulsion thrust subsystem (TSS) performance, packaging considerations, and certain operational characteristics. Thrust subsystem related work from recent studies by Jet Propulsion Laboratories (JPL), Rockwell and Boeing is discussed. Existing performance for 30-cm thrusters, power processors and TSS is present along with projections for future improvements. Results of analyses to determine (1) magnetic field distributions resulting from an array of thrusters, (2) thruster emitted particle flux distributions from an array of thrusters, and (3) TSS element failure rates are described to indicate the availability of analytical tools for evaluation of TSS designs.
An electric thrust subsystem technology development program to demonstrate the readiness of primary electric propulsion for flight applications is described. The development program is based on a subsystem design sufficiently flexible to be applicable to a broad range of mission requirements with minimum impact on the subsystem elements or interface designs. The effort includes development and qualification testing of new subsystem elements, the assembly and test of subsystem models to verify the physical and functional interfaces of the subsystem with other spacecraft subsystems, and the investigation of the effects of thrust subsystem operation on all aspects of spacecraft performance. The present status of this effort and some of the results so far obtained are presented.
An experimental Auger microprobe system is described which incorporates a field-emission electron gun and total beam currents in the nanoampere range. The distinguishing characteristics of this system include a large multistation UHV specimen chamber, pulse counting and fully digital Auger signal-processing techniques, and digital referencing methods to eliminate the effects of beam instabilities. Some preliminary results obtained with this system are described, and it is concluded that field-emission electron sources can be used for high-resolution Auger electron spectroscopy with primary-beam spots of less than 100 nm and beam currents of the order of 1 nA.
We have used a bremsstrahlung-identification technique to measure electron and positron spectra in the primary cosmic rays from 4 to 50 GeV. Above our average geomagnetic cutoff of 4.0 GV/c, we find fluxes of 4.4 (plus or minus 0.3) electrons and 0.37 (plus or minus 0.09 positrons) per sq m/sr/sec. The electron events follow a differential power law whose spectral index is 2.8 (plus or minus 0.1). Our ratio electrons/(electrons + positrons) = 0.08 (plus or minus 0.02) implies traversal of an equivalent slab thickness of 4.3 (plus or minus 1.5) g/sq cm of interstellar and source material.
The feasibility of an emergency aspirator once-through lubrication system was demonstrated as a viable survivability concept for Army helicopter mainshaft engine bearings for periods as long as 30 minutes. It was also shown in an experimental study using a 46-mm bore bearing test machine that an oil-air mist once-through system with auxiliary air cooling is an effective primary lubrication system at speeds up to 2,500,000 DN for extended operating periods of at least 50 hours.
Primary heat input systems and heat exchangers were evaluated for advanced energy conversion systems. Results are presented and discussed.
The prediction of the cooled aerodynamic performance, for both stators and turbines, at actual primary to coolant inlet total temperature ratios from the results obtained at a reduced total temperature ratio is described. Theoretical and available experimental results were compared for convection film and transpiration cooled stator vanes and for a film cooled, single stage core turbine. For these tests the total temperature ratio varied from near 1.0 to about 2.7. The agreement between the theoretical and the experimental results was, in general, reasonable.
Experiments were conducted to determine the performance of a premixing prevaporizing gas turbine primary zone combustor design over a range of combustor inlet temperatures from 700 to 1000 K and a range of inlet pressures from 40 to 240 N/sq cm. The 1 meter long combustor could be operated at pressures up to and including 120 N/sq cm without autoignition in the premixing duct or flashback from the stabilized combustion zone. Autoignition occurred in the mixer tube at the 240 N/sq cm pressure level with an entrance temperature of 830 K and a mixer residence time of 4 msec. Measured NOx level, combustion inefficiency, and hydrocarbon emission index correlated well with adiabatic flame temperature. The NOx levels varied from approximately 0.2 to 2.0 g NO2/kg fuel at combustion inefficiencies from 4 to 0.04 percent, depending upon adiabatic flame temperature and pressure. Measured NOx levels were sensitive to pressure. Tests were made at equivalence ratios ranging from 0.35 to 0.65. The overall total pressure drop for the configuration varied slightly with reference velocity and equivalence ratio, but never exceeded 3 percent.
An overview of Viking Orbiter (VO) system and subsystem performances during the primary mission (the time period from VO-1 launch on August 20, 1975, through November 15, 1976) is presented. Brief descriptions, key design requirements, pertinent historical information, unique applications or situations, and predicted versus actual performances are included for all VO-1 and VO-2 subsystems, both individually and as an integrated system.
Young lunar impact structures were investigated by using lunar orbiter, Apollo Metric and panorama photographs. Measurements on particularly homogeneous areas low in secondary craters made possible an expansion of primary crater distribution to small diameters. This is now sure for a range between 20m or = D or = 20km and this indicates that the size and velocity distribution of the impacting bodies in the last 3 billion years has been constant. A numerical approximation in the form of a 7th degree polynomial was obtained for the distribution.