Mechanical Impact System Design for Advanced Spacecraft /MISDAS/. Phase I - Design Concept Selection
Mechanical impact system for earth landing of Apollo command module
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Mechanical impact system for earth landing of Apollo command module
Gaseous coolant to transport waste heat from fission-electric cell reactor to space power plant radiator
Comparative efficiencies of thin wall aerospace pressure vessels, emphasizing primary structural weight
Connector plug automatically minimizes arcing during mating and demating. This plug uses a high-resistivity outer sheath as an extension to the regular pin contact. It is used in atmospheres containing explosive gases, and reduces erosion at the contact surfaces where mating and demating are performed frequently.
Design, construction, and performance of manned space center acoustic laboratory for ground tests of Apollo spacecraft
Low profile bulkheads for launch vehicles and spacecraft compartments to obtain structural weight reduction
Mathematical model for subdividing and transforming polyhedron into structural sphere
Pump provides independent liquid-metal streams at a uniform flow rate. The toroidal magnet structure can accomodate any reasonable number of pump circuits. The power requirement is suited to the output voltage of the basic thermionic diode output.
Application of cross beam remote sensing technique to atmospheric research problems
Turbine blade designs considered for increasing load capacity covering tandem, jet-blade and base plain blade configurations and test results
Fiber-metal matrix composites for gas turbine blades, discussing stress rupture strength, modulus of elasticity, fabrication, etc
Seal operating temperatures, leakage (pressurizing gas flow), torque, and wear of a conventional circumferential shaft seal were measured and compared to those of a conventional seal modified to have self-acting lift geometries. Both seal types had a 2.625-in diameter bore and were operated at a sliding velocity of 150 ft/sec with differential pressures ranging from 0 to 100 psi. Results of this investigation show that the self-acting seal operated at lower bulk carbon temperatures with half the torque and approximately one-tenth the wear of the conventional seal. Seal leakage of the self-acting seal was of order of 0.04 scfm for pressures above 60 psi which is well within the accepted range for gas turbine engine applications.
Passive device contains both solid and liquid animal waste matter for extended period without being cleaned and without contaminating animal. Constant airflow dries solid waste and evaporates liquid matter. Technique will maintain controlled atmospheric conditions and cage cleanliness during periods of 6 months to 1 year.
Five reactor cooling concepts which allow continued reactor operation following a single rupture of the coolant system are presented for application with the APR. These concepts incorporate convective cooling, double containment, or heat pipes to ensure operation after a coolant line rupture. Based on an evaluation of several control system concepts, a molybdenum clad, beryllium oxide sliding reflector located outside the pressure vessel is recommended.
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The efforts of a one year program of Requirements Analysis and Conceptual Design for the Large Earth Survey Telescope for the Synchronous Earth Observatory Satellite is summarized. A 1.4 meter aperture Cassegrain telescope with 0.6 deg field of view is shown to do an excellent job in satisfying the observational requirements for a wide range of earth resources and meteorological applications. The telescope provides imagery or thermal mapping in ten spectral bands at one time in a field sharing grouping of linear detector arrays. Pushbroom scanning is accomplished by spacecraft slew.
Digital computer components which perform two dimensional array logic operations (Tse logic) on binary data arrays are described. The properties of Golay transforms which make them useful in image processing are reviewed, and several architectures for Golay transform processors are presented with emphasis on the skeletonizing algorithm. Conventional logic control units developed for the Golay transform processors are described. One is a unique microprogrammable control unit that uses a microprocessor to control the Tse computer. The remaining control units are based on programmable logic arrays. Performance criteria are established and utilized to compare the various Golay transform machines developed. A critique of Tse logic is presented, and recommendations for additional research are included.