NASA required a rocket thruster able to produce a number of pulses at high specific impulse at a relatively low voltage (~300 to 400V). The key problem was that existing propellants for liquid-fueled pulsed plasma thrusters (LPPTs) required high voltages to ablate and accelerate...

NASA Johnson Space Center developed reprogrammable and interchangeable electronic controllers that can attach to a system or subsystem wirelessly or through plug-and-play capability. Originally designed to work with rocket engines, this technology can control...

Anon-catalytic pyrotechnic ignition system was developed for advanced green monopropellant systems operating with hydroxylammonium nitrate (HAN)-based monopropellant AF-M315E. This technology will provide increased performance and new operating regimes for...

NASA’s Marshall Space Flight Center has developed a unique prototype for measuring the liquid level in a tank, employing a novel process. The technology can operate in a wide range of environments, including high and low temperatures and pressures, and is simpler and less expensive than other...

Many pump vaned diffuser designs are based on existing airfoil designs, with little attention given to the vane leading edge. There is a need for a vaned diffuser leading edge that helps resist flow separation and the resultant poor diffuser pressure recovery....

The modeling of turbulent reactive flows is a subject of contemporary research. Current turbulent-reaction models cannot account for realistic complexities such as distinct species...

Innovators at NASA’s Marshall Space Flight Center have developed a suite of prototype fluid plug technologies with an array of capabilities for fluid flow metering, mixing, and conditioning. Each innovation within this suite is based upon a core technology that...

Low-cost access to space demands durable, cost-effective, efficient, and low-weight propulsion systems. Key components include boost and upper stage rocket engine nozzles and extensions. Nozzle material options include ablatives,...

Specific impulse (ISP), or simply impulse (change in momentum) per unit amount of propellant consumed, is a measure of rocket and jet engine efficiency. The amount of propellant, or in the case of engine testing at the Stennis Space Center (SSC), cryogen consumed during...