Electronegative Gas Thruster - Direct Thrust Measurement Project

This effort is an international collaboration and academic partnership to mature an innovative electric propulsion (EP) thruster concept to TRL 3 through direct thrust measurement. The initial target application is for Small Satellites, but can be extended to higher power. The Plasma propulsion with Electronegative GASES (PEGASES) concept simplifies ion thruster operation, eliminates a neutralizer requirement and should yield longer life capabilities and lower cost implementation over conventional gridded ion engines. The basic proof-of concept has been demonstrated and matured to TRL 2 over the past several years by researchers at the Laboratoire de Physique des Plasma in France. Due to the low maturity of the innovation, there are currently no domestic investments in electronegative gas thrusters anywhere within NASA, industry or academia. The end product of this Center Innovation Fund (CIF) project will be a validation of the proof-of-concept, maturation to TRL 3 and technology assessment report to summarize the potential for the PEGASES concept to supplant the incumbent technology. Information exchange with the foreign national will be one-way with the exception of the test results. Those test results will first go through a standard public release ITAR/export control review, and the results will be presented in a public technical forum, and the results will be presented in a public technical forum

Development and In-Flight Testing of an Iodine Ion Thruster

The increase in the number of small satellite missions is enabling the development of new mission scenarios, requiring in turn further miniaturization of the systems onboard. An example is the deployment of small satellite constellations, which typically require onboard propulsion to perform phasing, collision avoidance and deorbit maneuvers. In this work we describe the development, testing and first in-space demonstration of a one Cubesat unit standalone iodine-fueled electric propulsion system based on a gridded ion thruster. The propulsion system, called NPT30-I2-1U, has all the subsystems necessary to its operation integrated inside the 1U volume, such as power processing unit, operation controller and iodine propellant storage and management. An inductively coupled RF plasma source is used for propellant ionization and a two-grid assembly for ion acceleration, while the beam neutralization is achieved with a cathode-neutralizer based on thermionic hot filament cathode. The propellant is solid iodine, stored in the internal unpressurized tank and sublimated during the operation. The system can provide up to 5500 Ns of total impulse at a specific impulse up to 2450 s and thrust levels of up to 1.1 mN in the range of input power of 35-65 W. Extreme miniaturization of the system is achieved through several innovations, including pipe-less propellant delivery, custom RF generation technology, a dedicated plasma ignition system and integrated thermal management. The necessary level of robustness and safety is achieved through implementation of reliability engineering approaches: system has built-in self-test and self-tuning algorithms and several layers of security loops. It should be mentioned, that the NPT30-I2-1U is the first iodine-fueled electric propulsion system launched to space and therefore many iodine-related aspects such as a propellant storage configuration, corrosion and sublimation control, iodine plume neutralization etc., have been tested in space for a first time

Phase-resolved optical emission spectroscopy of a neutralizer-free gridded ion thruster

International audienc

Transient propagation dynamics of flowing plasmas accelerated by radio-frequency electric fields

International audienceFlowing plasmas are of significant interest due to their role in astrophysical phenomena and potential applications in magnetic-confined fusion and spacecraft propulsion. The acceleration of a charge-neutral plasma beam using the radio-frequency self-bias concept could be particularly useful for the development of neutralizer-free propulsion sources. However, the mechanisms that lead to space-charge compensation of the exhaust beam are unclear. Here, we spatially and temporally resolve the propagation of electrons in an accelerated plasma beam that is generated using the self-bias concept with phase-resolved optical emission spectroscopy. When combined with measurements of the extraction-grid voltage, ion and electron currents, and plasma potential, the pulsed-periodic propagation of electrons during the interval of sheath collapse at the grids is found to enable the compensation of space charge

Grounded radio-frequency electrodes in contact with high density plasmas

An analytical model is developed of an asymmetric electrode system immersed in a plasma, consisting of two dc-grounded electrodes, where the smaller one is biased at 13.56MHz. The model is compared with a set of experiments performed in a high density low pressure plasma source (an electron cyclotron resonance source) where a second electrode is immersed into the plasma and powered by radio frequency. Excellent agreement is obtained between the analytical model and the experimental results. It is found that the time average plasma potential and the direct current(dc) flowing in the system during steady state are strongly dependent on both the rf voltage (or power) and the area ratio between the larger and smaller electrodes. For area ratios larger than 80, the dc current is large and the plasma potential is constant with respect to the applied rf voltage. For area ratios smaller than 80 but larger than unity, the plasma potential increases linearly with the applied rf voltage, and the dc current is reduced compared to the large area ratio case

Experiments and theory of an upstream ionization instability excited by an accelerated electron beam through a current-free double layer

A low-frequency instability varying from 10 to 20kHz has been discovered in the presence of a current-free double layer (DL) in a low-pressure expanding helicon plasma. The instability is observed using various electrostatic probes, such as Langmuir probes floating or biased to ion saturation and emissive probes measuring the plasma potential. A retarding field energy analyzer measuring the ion energy distribution function downstream of the double layer is used together with the LP to simultaneously observe the DL and the instability, confirming their coexistence. The frequency of the instability decreases with increasing neutral pressure, increases with increasing magnetic field in the source and increases with increasing rf power. A theory for an upstream ionizationinstability has been developed, in which electrons accelerated through the DL increase the ionization upstream and are responsible for the observed instability. The theory is in good agreement with the experimental results and shows that the frequency increases with the potential drop of the double layer and with decreasing chamber radius

An Off-Axis Iodine Propulsion System for the Robusta-3A Mission

The decrease of the force of the magnetic field in altitudes above Low Earth Orbits (LEO) drives the need for miniaturized propulsion systems that can provide attitude control. In addition, these systems are already needed for orbit maintenance, phasing and lifetime extension of small satellite missions, and could also help with end-of-life decommissioning and debris mitigation. The I2T5 cold gas thruster, an iodine-based propulsion system, will be integrated on the Robusta-3A mission, developed by the CSUM, along with several educational and scientific payloads, related to meteorology and technology demonstration. The insights given on the development process of this mission are intended to provide enriching knowledge to the space community, mainly in three areas: small satellite missions design, when both scientific payloads and propulsion systems are used; off-axis primary propulsion systems, focusing on how to eventually overcome the problems related to attitude control and mission analysis of small satellite missions; the use of iodine as a propellant for scientific space missions, focusing on how to overcome the issues related to the use of this propellant, such as propellant bouncing, deposition on external surfaces and following corrosion risks

Flow dynamics and magnetic induction in the von-Karman plasma experiment

The von-Karman plasma experiment is a novel versatile experimental device designed to explore the dynamics of basic magnetic induction processes and the dynamics of flows driven in weakly magnetized plasmas. A high-density plasma column (10^16 - 10^19 particles.m^-3) is created by two radio-frequency plasma sources located at each end of a 1 m long linear device. Flows are driven through JxB azimuthal torques created from independently controlled emissive cathodes. The device has been designed such that magnetic induction processes and turbulent plasma dynamics can be studied from a variety of time-averaged axisymmetric flows in a cylinder. MHD simulations implementing volume-penalization support the experimental development to design the most efficient flow-driving schemes and understand the flow dynamics. Preliminary experimental results show that a rotating motion of up to nearly 1 km/s is controlled by the JxB azimuthal torque

Design and Preliminary Performance Testing of Electronegative Gas Plasma Thruster

In classical gridded electrostatic ion thrusters, positively charged ions are generated from a plasma discharge of noble gas propellant and accelerated to provide thrust. To maintain overall charge balance on the propulsion system, a separate electron source is required to neutralize the ion beam as it exits the thruster. However, if high-electronegativity propellant gases (e.g., sulfur hexafluoride) are instead used, a plasma discharge can result consisting of both positively and negatively charged ions. Extracting such electronegative plasma species for thrust generation (e.g., with time-varying, bipolar ion optics) would eliminate the need for a separate neutralizer cathode subsystem. In addition for thrusters utilizing a RF plasma discharge, further simplification of the ion thruster power system may be possible by also using the RF power supply to bias the ion optics. Recently, the PEGASES (Plasma propulsion with Electronegative gases) thruster prototype successfully demonstrated proof-of-concept operations in alternatively accelerating positively and negatively charged ions from a RF discharge of a mixture of argon and sulfur hexafluoride.i In collaboration with NASA Marshall Space Flight Center (MSFC), the Georgia Institute of Technology High-Power Electric Propulsion Laboratory (HPEPL) is applying the lessons learned from PEGASES design and testing to develop a new thruster prototype. This prototype will incorporate design improvements and undergo gridless operational testing and diagnostics checkout at HPEPL in April 2014. Performance mapping with ion optics will be conducted at NASA MSFC starting in May 2014. The proposed paper discusses the design and preliminary performance testing of this electronegative gas plasma thruster prototype

High brightness inductively coupled plasma source for high current focused ion beam applications

A high brightnessplasmaion source has been developed to address focused ion beam(FIB) applications not satisfied by the liquid metal ion source (LMIS) based FIB. The plasmaFIB described here is capable of satisfying applications requiring high mill rates (>100μm³/s) with non-gallium ions and has demonstrated imaging capabilities with sub- 100-nm resolution. The virtual source size, angular intensity, mass spectra, and energy spread of the source have been determined with argon and xenon. This magnetically enhanced, inductively coupled plasmasource has exhibited a reduced brightness(βr) of 5.4×10³Am⁻²sr⁻¹V⁻¹, with a full width half maximum axial energy spread (ΔE) of 10eV when operated with argon. With xenon, βr=9.1×10³Am⁻²sr⁻¹V⁻¹ and ΔE=7eV. With these source parameters, an optical column with sufficient demagnification is capable of forming a sub-25-nm spot size at 30keV and 1pA. The angular intensity of this source is nominally three orders of magnitude greater than a LMIS making the source more amenable to creating high current focused beams, in the regime where spherical aberration dominates the LMIS-FIB. The source has been operated on a two lens ion column and has demonstrated a current density that exceeds that of the LMIS-FIB for current greater than 50nA. Source lifetime and current stability are excellent with inert and reactive gases. Additionally, it should be possible to improve both the brightness and energy spread of this source, such that the (βr/ΔE₂) figure-of-merit could be within an order of magnitude of a LMIS