Precision flow measurement techniques for low thrust auxiliary propulsion liquid rockets.
Fuel consumption precision measurements for low thrust auxiliary rockets using impeller wheel and photometric devices
FLOW MEASUREMENT↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Preignition phenomena in small A-50/NTO pulsed rocket engines.
Preignition phenomena in small Aerozine- 50/nitrogen tetroxide pulsed rocket engines shown partly due to hydrazine nitrate accumulation
PROPELLANT COMBUSTION↗
Pneumatic logic rocket engine sequence control.
Fluidic breadboard version of rocket engine sequence control, describing pneumatic logic package and general limitations
FLUIDICS↗
Study of the ionosphere by means of rocket measurements of the VLF field radiated from a ground source. III
Ionosphere collision frequencies and densities studied by rocket measurements of magnetic field of VLF wave radiated from ground
ROCKET MEASUREMENT↗
Rocket observations of electron temperature in the E region.
Electron temperature observation in E region with Langmuir probes on Nike Apache rockets, discussing solar radiation effect
ELECTRON TEMPERATURE↗
Rocket sampling of noctilucent cloud particles during 1964 and 1965.
Rocket sampling of noctilucent cloud particles in mesopause
NOCTILUCENT CLOUD↗
Spectral radiances of model rocket exhaust gases at simulated altitude measured with a rapid-scanning spectrometer.
Spectral radiance of model rocket exhaust gases measured by rapid scanning spectrometer at simulated altitude
EXHAUST GAS↗
Southern Hemisphere stratospheric circulation as indicated by shipboard meteorological rocket observations.
Early autumn stratospheric circulation of Southern Hemisphere investigated by meteorological rocket observations
ROCKET SOUNDING↗
Determination of the attitude of a spinning rocket under thrust with statistically varied inputs.
Motion equations of spin-stabilized rocket under thrust with jet damping, variable mass and momentum effects and all angular disturbances
ANGULAR MOTION↗
Rapid determination of near-optimum linear pitch programs for rocket boosters.
Linear segment pitch rate program for near optimum trajectory for rocket boosters
COMPUTER PROGRAM↗
Liquid propellant space rockets
Liquid rocket propellants use in U.S. space program, particularly Apollo project, discussing future trends
APOLLO PROJECT↗
Micrometeorite flux determined from the 1965 Luster sounding rocket collection.
Micrometeorite flux rate for Leonid shower measured with Luster sounding rocket collecting surface
EXTRATERRESTRIAL MATTER↗
External and Internal Air Loads on Sounding Rockets
Air loads on sounding rocket from distributed aerodynamics and pressure differential
AERODYNAMIC LOAD↗
Theory and experimental results of a detonation tube technique for simulating rocket plumes in a space environment.
Shock tube simulation of rocket exhaust plumes and effects on vehicles in space environment
PLUME↗
Experimental verification of a double-dead-time model describing chugging in liquid- bipropellant rocket engines.
Stability boundaries of double-dead-time model describing chugging in liquid bipropellant rocket engine
ANALOG COMPUTER↗
Sources, mechanisms, and control of roll resonance phenomena for sounding rockets.
Dynamic flight characteristics of spin-stabilized sounding rockets during passage through atmosphere, emphasizing roll resonance and motions leading to roll lock-in and angle of attack
ANGLE OF ATTACK↗
Bleed Cycle Propellant Pumping in a Gas-Core Nuclear Rocket Engine System
The performance of ideal and real staged primary propellant pumps and bleed-powered turbines was calculated for gas-core nuclear rocket engines over a range of operating pressures from 500 to 5000 atm. This study showed that for a required engine operating pressure of 1000 atm the pump work was about 0.8 hp/(lb/sec), the specific impulse penalty resulting from the turbine propellant bleed flow as about 10 percent; and the heat required to preheat the propellant was about 7.8 MW/(lb/sec). For a specific impulse above 2400 sec, there is an excess of energy available in the moderator due to the gamma and neutron heating that occurs there. Possible alternative pumping cycles are the Rankine or Brayton cycles.
Gas-core↗
Internal-Film Cooling of Rocket Nozzles
Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous ring of 3.5 percent of propellant flow stabilized wall temperature in convergent section but did not adequately cool throat or divergent sections.
HEAT TRANSFER↗