Classical dynamical investigations of reaction mechanism in three-body hydrogen-halogen systems.
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Engineering topics
Publications and source records attributed to Porter, R. N..
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The molecular and atomic mechanisms for the hydrogen-iodine exchange reaction are treated theoretically by means of extensive classical trajectories calculated on a reasonable potential energy surface on which the single adjustable parameter is the iodine-core effective charge. The analysis shows the molecular mechanism to be dynamically forbidden, but gives an over-all rate constant for the atomic mechanism that is in agreement with the experimental values. It is indicated that the formation of a weak H2I complex plays an important dynamical role if the atomic mechanism is limited to reactions with collision complexes involving no more than two hydrogen atoms and two iodine atoms. Excellent agreement with experiment is obtained for the rate constant for the recombination I+I+H2 yields I2+H2 and its negative temperature coefficient.
Prototype liquid-fuel valve performs on-off and throttling functions in vacuum without component cold-welding or excessive leakage. Valve design enables simple and rapid disassembly and parts replacement and operates with short working stroke, providing maximum throttling sensitivity commensurate with good control.
Space storable oxygen fluoride/boron hydride tank module thermal control design for Jupiter mission
Space storable fluorine/hydrazine tank module thermal control design for Jupiter mission
Force balanced throttle valve for fuel control in rocket engines
Design of thermal control system for cryogenic fluid storage tanks
Test program for engineering model of thermal control system of space storable propellant module in simulated environments
Thermal control concepts for space storable fluorine hydrazine propulsion module
Thermal control system for space storable propellant module
Collapsible auxiliary tank for restarting liquid propellant rocket motors under zero gravity
Nitrogen tetroxide and hydrazine compatibility with aluminum alloy storage tanks
Test firing of 100-lb thrust ablatively cooled rocket chambers
Mechanical positive expulsion devices for earth- storable liquid rocket propellants in unmanned spacecraft
Fabrication of seamless Teflon propellant expulsion bladders
Use of earth-storable propellants in unmanned spacecraft propulsion systems for flights to near planets and moon
Advanced liquid propellants for spacecraft propulsion - nitrogen tetroxide and hydrazine
Advanced propulsion systems for unmanned spacecraft making simple pressure-fed systems, using storable propellants, thrust chambers and flexible propellant barriers