Performance study of a repetitively pulsed two-stage plasma propulsion engine Final report
Performance characteristics of repetitively pulsed two-stage plasma propulsion engine
PROPULSION SYSTEM PERFORMANCE↗
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Study of parametric performance of a two-stage repetitively pulsed plasma engine /REPPAC/
Parametric performance of two-stage repetitively pulsed plasma engine
ENGINE TESTING↗
Performance of a two-stage repetitively pulsed coaxial plasma engine.
Efficiency of two-stage repetitively pulsed coaxial plasma engine calculated from engine thrust and total mass flow
THRUST POWER↗
Steady state operation of a two-stage pulsed coaxial plasma engine.
Performance characteristics of two-stage pulsed coaxial plasma engine
ELECTRIC PROPULSION↗
Performance of an electrically triggered repetitively pulsed coaxial plasma engine.
Efficiency of two-stage repetitively pulsed coaxial plasma engine calculated from engine thrust and total mass flow
MASS FLOW↗
Energy efficiency trends in a coaxial gun plasma engine system.
Energy efficiency trends in two-stage repetitively pulsed coaxial plasma accelerator
ENERGY CONVERSION EFFICIENCY↗
Some characteristics of a two-stage repetitively fired coaxial gun.
Two-stage repetitively pulsed coaxial plasma engine performance, examining luminous species and their velocities
COAXIAL ACCELERATOR↗
Igniter Testing and Development for Liquid Oxygen/Liquid Methane (LOX/LCH4) and Liquid Oxygen/Gaseous Hydrogen (LOX/GH2) Injectors
In support of NASA's efforts to advance methane technology for future exploration missions, two different igniter concepts were developed and tested at NASA's Marshall Space Flight Center for ignition of oxygen/methane propellants. The first type of igniter, an impinging injection, spark-initiated torch igniter (impinging igniter), used traditional spark plug technology to produce a small, but very intense, pulsed plasma as the ignition source. The second type of igniter, a microwave-generated plasma igniter (microwave igniter), used a microwave magnetron to produce a continuous, larger-volume plasma as the ignition source. Two new designs for both types of igniters were leveraged off past oxygen/methane igniter designs that were tested at MSFC and documented in a 2008 JANNAF paper. In this most recent work, the two new igniters were to be tested at the component level as well as inside a liquid oxygen/liquid methane (LOX/LCH4) 40-element swirl coaxial injector. Although the microwave igniter achieved ignition in every test, it encountered technical difficulties that prevented it from being tested with the injector. The impinging igniter required several design iterations as well as testing at different mixture ratios and mass flow rates before reliable operation with minimal ignition delay was achieved. The final design of the impinging igniter was successfully tested in the LOX/LCH4 injector. The same igniter was later re-configured and component-tested to demonstrate reliable ignition of oxygen/hydrogen propellants. Future tests of the impinging igniter will include ignition of a LOX/hydrogen two-stage swirl injector, which is one of several injector concepts being tested in the Lunar Lander Descent Engine Test Bed at MSFC. All igniter and injector tests have been funded by the Propulsion & Cryogenics Advanced Development project managed by Glenn Research Center and sponsored by NASA s Exploration Technology Development Program.
Osborne, Robin J.↗