Reinforced oxide throat insert development
Wire reinforced zirconium oxide rocket nozzle inserts
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Wire reinforced zirconium oxide rocket nozzle inserts
Neutron and gamma measurements for NASA Plum Brook Reactor HB-6 beam hole insertion facility
Effect of helical flow inserts on boiling pressure drop
Enhanced heat transfer in tubes by using helical vane inserts
Impulsive velocity requirements for insertion into orbits about Venus, Mars, and Jupiter
Water and alkali metal boilers, predicting helical-flow-promoting inserts effect on pressure drop penalties by constant slip model
Tube heat transfer augmentation by helical vane inserts, noting Reynolds number and mass flow rate effects
Technique for sterile insertion of liquids into previously sterilized spacecraft
High impedance alternating current sensing transformer device between two bolometers for measuring insertion loss of test component
Initial data for space shuttle orbiter guidance, navigation, and control equations for preflight, boost, separation, orbit insertion, and ascent abort phases
Catheter inserted wire basket device for creation of reversible aortic insufficiency in animal
Monkey physiological responses from lift-off to orbital insertion, showing EEG and EMG arousal reactions, motion sickness development, cardiovascular and respiratory changes
Local forced convection heat transfer data and empirical correlations for boiling Hg in single wetted Ta tube with composite helical inserts
Actual navigation dispersions, estimation uncertainties and resultant Mars orbit insertion statistical delta V requirements for six Mars approach angles in 1977 Mars window
On 14 November 1971 the Mariner 9 1334-N-(300-lbf)-thrust rocket engine was fired for just over 15 min to place the first man-made satellite into orbit about Mars. Propulsion subsystem data gathered during the 5-month interplanetary cruise and orbit insertion are of significance to future missions of this type. Specific results related to performance predictability, zero g heat transfer, and nitrogen permeation, diffusion, and solubility values are presented.
The concept of a space shuttle orbit/tug orbital insertion surface is developed. Practical applications in the area of ascent targeting, on-orbit rendezvous targeting, payloads/OMS propellant off-loading, and mission analysis are identified.
The technology of impregnated materials is described and some inherently advantageous characteristics of impregnated cathodes are discussed. Thermionic emission measurements are presented for oxide coated and impregnated cathodes. Five cathode configurations with barium oxide impregnated porous tungsten inserts and/or tips have been fabricated and tested. Reliability, durability, and stability of operation are characterized. One of the cathodes has accumulated over 9000 operational hours, another has been cycled on and off more than 800 times.
A manually actuated tool for facing the exposed end of an insert installed in a honeycomb panel is described. Several cutting bits are held in a round body portion that is rotated around the end of a stud to provide the cutting action. Pressure is adjusted through a spring against the body portion and the surface of the stud by a pressure nut threaded on the stud. A diagram of the components of the device is provided.