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Results for “ROCKET THRUST”

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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At least 109 records · Page 6
All sourcesNASA NTRSDOE OSTI
NASA NTRS1992

Demonstrated survivability of a high temperature optical fiber cable on a 1500 pound thrust rocket chamber

A demonstration of the ability of an existing optical fiber cable to survive the harsh environment of a rocket engine was performed at the NASA Lewis Research Center. The intent of this demonstration was to prove the feasibility of applying fiber optic technology to rocket engine instrumentation systems. Extreme thermal transient tests were achieved by wrapping a high temperature optical fiber, which was cablized for mechanical robustness, around the combustion chamber outside wall of a 1500 lb Hydrogen-Oxygen rocket engine. Additionally, the fiber was wrapped around coolant inlet pipes which were subject to near liquid hydrogen temperatures. Light from an LED was sent through the multimode fiber, and output power was monitored as a function of time while the engine was fired. The fiber showed no mechanical damage after 419 firings during which it was subject to transients from 30 K to 350 K, and total exposure time to near liquid hydrogen temperatures in excess of 990 seconds. These extreme temperatures did cause attenuation greater than 3 dB, but the signal was fully recovered at room temperature. This experiment demonstrates that commercially available optical fiber cables can survive the environment seen by a typical rocket engine instrumentation system, and disclose a temperature-dependent attenuation observed during exposure to near liquid hydrogen temperatures.

Sovie, Amy L.↗
NASA NTRS1956

Effects of Variations in Combustion-chamber Configuration on Ignition Delay in a 50-pound-thrust Rocket

Ignition delays of a diallylaniline-triethylamine mixture and of triethyl trithioposphite with red fuming nitric acid were measured as a function of combustor dimensions, initial propellant temperature, and initial ambient pressure. Ignition delay increased with exhaust-nozzle diameter. Ignition delay also increased as propellant temperature decreased, but did not vary with initial ambient pressure except with the largest nozzle diameter. A correlation among ignition delay, combustor dimensions, and propellant temperature is presented, and the extension of the correlation to other systems is discussed.

Ladanyi, Dezso J↗
NASA NTRS1957

A Study of Injection Processes for Liquid Oxygen and Gaseous Hydrogen in a 200-pound-thrust Rocket Engine

Characteristic velocities of six single-element injectors that separately varied propellant spreading and mixing were measured over a range of oxidant-fuel weight ratios of 2 to 7. Hydrogen inlet temperature was -320 degrees F. Injectors that both mixed and spread the propellants had the highest characteristic-velocity efficiency. Spreading of either propellant produced about the same increment efficiency. The increase in efficiency due to mixing was relatively small. With similar injectors, oxygen-hydrogen required about 0.2 to 0.5 of the combustor volume of oxygen-heptane for the same efficiency.

Auble, Carmon M↗
NASA NTRS1957

A study of injection processes for 15-percent fluorine - 85-percent oxygen and heptane in a 200-pound-thrust rocket engine

Characteristic exhaust velocity over a range of mixture ratios and variations in gas velocity with distance from the injector were measured for six injectors. Comparisons of injector performance showed the gains obtained from oxidant atomization, fuel atomization, and propellant mixing. The results are compared with oxygen and heptane performance and show the effect, which is qualitatively small, of spontaneous propellant ignition on the relation between injection processes and engine performance.

Heidmann, M F↗