HIGH ENERGY REPLACEMENT FOR TEFLON PROPELLANT IN PULSED PLASMA THRUSTERS, Phase I

This program will utilize a well-characterized Pulsed Plasma Thruster (PPT) to test experimental high-energy extinguishable solid propellants (HE), instead of standard Teflon propellant. ET Materials LLC originally formulated this material as an environmentally friendly automotive airbag inflator propellant. In preliminary testing, the material was found suitable for use in PPTs. Electric arc discharges of the PPT apparently causes only thin surface layers of the energetic propellant to be ignited, without uncontrolled propagation to underlying propellant. The current Isp of these propellants is ~225 sec. but newer formulations appear to be reaching an Isp of 245 sec., essentially that of ammonium perchlorate propellants. The relative thrust contribution from plasma ionization and thermal expansion of non-ionized combustion gases will determine how much the energetic fuel enhances PPT performance. All testing and evaluation of the HE propellant will be conducted using the Aerojet Modular Test Unit Pulsed Plasma Thruster. This modular test unit was specifically designed to evaluate new flight configurations of the EO-1 PPT design. Using the high-energy propellant in the EO-1 PPT, should increase dramatically increase. This program will provide NASA with directly applicable results for a high-energy drop-in alternative propellant for the EO-1 PPT, providing new mission capabilities.

Miniaturized PPT?s for onboard propulsion are one of the few viable options for small satellites in the 10 kg and lower total mass region. Such satellites are of military interests in programs being developed by the Air Force, DARPA and MDA. In addition there is a growing commercial interest in small satellites that are being developed and built by University and Private companies. The high energetic propellants being developed in this program also could be used commercially for gas generation systems, such as automobile air bags, turbine starters or valve actuators. The use of energetic Pulsed Plasma Thrusters demonstrated in this program has specific application for primary propulsion of small spacecraft for orbit raising and life extension of low earth missions. Several studies have shown that an all PPT attitude control system has a significant mass benefit over wheel, torque rods and thrusters used for attitude control. Such NASA missions as the Space Technology 5,6 and 7 and THEMIS that require both attitude and translational positioning could benefit from this technology. Successful demonstration in these missions would provide enabling technology for later Origins missions, such as the Terrestrial Planet Finder

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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