Current projects in the Isp Lab:
- Re-generable Field Emission Cathodes for Low-Power Electric Propulsion
- Bismuth Hall thruster
- Powder Metallurgy
- Bismuth Cathode
- Hall thruster thermal modeling
- Magnetic field topology of hall thrusters
- Electron dynamics in a Hall-effect accelerator
- Xenon Hall thrusters
- Field-Reversed Configuration (FRC) Plasma
- Coulomb Propulsion
- Carbon nanotubes for sputter erosion resistance
- Zero Gravity Student Research
- Oculus: a nanosat for Space Situational Awareness
Field-emission cathodes have recently received much interest for use as zero-flow “cold” electron emitters for sub-100-W Electric Propulsion (EP) thrusters. Field emission cathodes rely on Fowler Nordheim emission from very sharp (10-nm-radius) electrode tips. The lifetime of microfabricated field emitters is, so far, incompatible with EP applications. Because of the fragility of the nanometer-sized tips, the structures are susceptible to damage that blunts the tip and destroys the device functionality.
This research investigates the discharge characteristics of a field-emission cathode for use in EP that has the ability to be re-generated when the emitter tip becomes damaged. Emitter tip re-generation is possible by using Taylor cone formation from an operating liquid-metal-ion-source (LMIS) in an effort to solidify, or quench, the ion emitting cone to preserve the sharp tip. The tip can then be used for electron emission.
Hall thrusters operating at power levels greater
than 30 kW would have significant benefits for space missions of interest
to the Air Force. Although scaling state-of-the-art Hall thrusters to
larger powers is straightforward from a physical standpoint, development
of such devices has been impeded by financial considerations. Currently,
Hall thrusters operating at the power levels of interest require multi-million
dollar ground-testing facilities and consume tens of thousands of dollars
of xenon propellant in a single day of testing.
This project is developing critical technology for high-power Bismuth Hall thrusters potentially having superior performance over state-of-the-art devices at a fraction of the cost of existing technology. Bismuth is significantly cheaper than Xenon and since it is solid at room temperature, does not require the pumping capacity needed for Xenon powered thrusters. Also when compared with xenon, bismuth has a higher atomic weight and lower ionization potentials, implying superior physical efficiency in the plasma discharge. (Hall thruster operating on bismuth propellant is shown to the left.)
The work centers on an MTU-patented concept for supplying metal vapor propellant to a Hall thruster using a temperature-controlled segmented anode. The metal propellant is maintained in a liquid state within the primary anode using waste heat dissipation within the thruster. The propellant supply rate is controlled through power-sharing shim electrodes, which intercept a fraction of the plasma discharge current, thereby regulating the liquid metal temperature within the primary anode and hence the evaporation rate.
This work is also supported by industry partners Aerojet and Aerophysics, Inc.
Refractory metals have various thermal and material properties that are desirable for use in plasma thrusters. The 
Isp Lab has the ability to sinter refractory materials in a high vacuum or inert environment to create parts with controlled densities while retaining open porosities. This process has been used to make large molybdenum discs with ~2 micron pores at 60 percent density which are used in bismuth Hall thrusters.
Using
bismuth in place of gases such as xenon for Hall thruster propellant could
potentially offer both physical and economical gains. As research continues
to develop Hall thrusters that are fueled with bismuth, it will become
advantageous to maintain one propellant supply rather than multiple supplies
for the anode and cathode. The recent development of a bismuth Hall thruster
at Michigan Tech, operated using a xenon LaB6 cathode, provided a motive
to explore the feasibility of developing an entire bismuth system.
Hall Thruster Thermal Modeling
Control
and Management of condensable metal propellants in Hall thrusters requires
detailed knowledge of the Hall thruster temperature field and heat transfer
during operation. Computational codes such as MuSES, IDEAS, and TRASYS are
used to predict temperature fields. Numerical results are calibrated against
test data. The Isp lab also maintains a Mikroscan 5104 IR thermal imaging camera for experimentally examining the thermal properties of condensable metal laboratory cathodes and Hall thrusters in operation.
Electron Dynamics in Hall Thruster Fields
Hall thrusters employ a magnetic field applied transverse to an accelerating electric field to emulate virtual accelerating electrodes. Historically, the cross-field electron mobility in HEA's has been shown to be 1,000 times greater than predicted by classical plasma theory, yet an explanation for this discrepancy is absent.
In
this project, the defining characteristics of the accelerating region in a Hall thruster are reproduced in the construction of an electron trapping apparatus.
The trap will be used to confine a one-component-plasma to study the mobility
of electrons across the magnetic field. The trap utilizes radial magnetic
mirror forces and an induced circular ExB drift to confine the plasma. Mobility
is measured in response to field strength, collision frequency, and time-varying
electrostatic perturbations representative of traveling plasma waves.
Many scientific devices rely on trapping hot, electrically charged particles in electromagnetic "bottles" to prevent collisions between the particles and solid walls. While many excellent techniques exist to confine either positively charged or negatively charged particles in such bottles, trying to simultaneously trap charges of both signs has been problematic. Magnetic fields are typically used as virtual walls for trapping charged particles, since such particles have difficulty crossing magnetic field lines. Theoretical calculations show that magnetic fields should be very effective for simultaneously confining both positive and negative charges. However, when used in the laboratory the rate at which particles escape magnetic devices can be more than 1,000 times greater than predicted by theory.
The poor effective trapping has been a problem in many disciplines. Most visibly, the inability to effectively trap particles has been a frustration for scientists trying to design fusion energy devices that have the potential to eliminate our reliance on fossil fuels. This project will study the problem of confining charged particles in magnetic fields in an attempt to understand the most basic discrepancy between theory and experiment. The results of this study could be used to improve charged particle confinement with benefits for fusion energy, space propulsion, and materials science applications.
Plasma thrusters are famous for their fuel efficiency: when compared with a chemical rocket, a typical plasma thruster may only require 1/10th the amount of propellant to accomplish a given mission. However, because the electric power available on a spacecraft is limited to a few 10's of kW, plasma thrusters are limited in the amount of instantaneous thrust they can provide. The result is that, while a plasma thruster requires less fuel, it will take longer to accomplish a given mission than a high-thrust chemical system. For certain missions, it is more important to get the spacecraft to its destination in a short time than it is to conserve propellant. These types of missions require more thrust than is currently available using state-of-the-art Hall thrusters.
Work at the Isp Lab is focusing on increasing the amount of thrust available from a Hall thruster for a given input electric power. These so-called High Thrust-to-Power ratio devices would be an enabling technology for many missions, civilian as well as military, requiring rapid re-positioning of space assets. Researchers are examining the various thrust and power loss mechanisms of current Hall thrusters with the intention of identifying means of improvement. A subtle, but critical, related area of research involves understanding the coupling voltage between the thermionic hollow-cathode/neutralizer and the thruster plasma.
Field Reversed Configuration 
Plasma
The ISP Lab is developing an experiment to study the formation and translation dynamics of annular field reversed configuration (AFRC) plasmas. The primary goal of this project is to explore AFRC's as a candidate for high power electric propulsion. An AFRC is a derivative of the traditional FRC, studied by the fusion community since 1958.
Traditional FRC's are characterized by an elongated, prolate compact toroid with a pure toroidal field and polidal current formed from a magnetic field reversal. The formation process yields a hot, dense plasma with a closed, self-contained structure which can be translated along it's axis. This self-contained structure requires very high voltages (~200 kV) and short pulse widths (~1 us) for formation.
Lower discharge voltages (~1 kV) are obtainable by using a coaxial coil geometry (referred to as an AFRC) and wrapping the field lines around the plasma, as opposed to reversing the magnetic field. The formation
sequence for an AFRC is shown in illustration on the right. Plasma densities (ne ~ 10^21 m^-3) and temperatures (Te ~ 20 eV) of AFRCs are not sufficient for fusion, but the lower discharge voltages make it amenable to spacecraft.
The ISP Lab's AFRC experiment is a next-generation device of University of Michigan/U.S. Air Force Research Laboratory's AFRC experiment. Other co-axial geometry studies (the Coaxial Slow Source) have been completed by the University of Washington.
Spacecraft clusters, or formations, are an emerging trend in space
mission design. Proposed concepts utilize swarms of small micro- or
nanosatellites acting in collaboration. For many applications, the
vehicles within the swarm must maintain accurate position with
respect to others in the group. To achieve relative position
control, some type of formation-keeping propulsion is required on
each vehicle. While the propulsive forces necessary are small (10's
to 100's of microNewtons), precise application and control of these
forces is difficult in practice. Also, continuous application of
formation-keeping forces would quickly exhaust the propellant supply
of traditional micro-rocket engines. In 2001, the Isp Lab was the
first to propose the use of inter-vehicle Coulomb forces for use in
spacecraft formation control. This concept relies on electrically
charging spacecraft by expelling charged beams. The vehicles then
experience electrostatic attraction or repulsion from the other
vehicles in the swarm. The entire formation exhibits coupled,
collective motion that can be exploited to maintain relative
position. Since Coulomb propulsion requires no fuel, the concept can
essentially maintain a formation for an indefinite period of time.
The power required to affect Coulomb propulsion has been shown to be
on the order of milli-Watts up to a few Watts. The required on-board
mass of the system has been shown to be very small. Research
continues on charging mechanisms, charge sensing/serving techniques,
spacecraft/plasma interaction, and distributed control.
Carbon Nanotubes for Sputter Erosion Resistance
Electric
propulsion devices make deep space missions feasible because of their superior
efficiency over traditional chemical rockets. However, sputter erosion of
critical surfaces in these thrusters is a life-limiting factor. To extend
the lifetime of EP devices, sputter resistant materials such as molybdenum
(Mo) are generally used for these surfaces. However, unique mechanical properties
of carbon nanotubes (CNTs) have triggered tremendous curiosities in their
applications, particularly for EP thrusters. Vertically aligned multi-walled
carbon nanotubes (VA-MWNTs) are evaluated as protective coatings against ion
erosion in hopes of finding a superior material for EP applications. More
information is available at http://www.phy.mtu.edu/yap/
Michigan Tech students regularly perform experiments on-board NASA's zero-gravity simulation aircraft through the NASA Reduced Gravity Student Flight Opportunity Program http://microgravityuniversity.jsc.nasa.gov/. The C9 aircraft, which flies 
a parabolic path consisting of a steep climb followed by a steep dive, can provide 30-second periods of simulated zero gravity for participants. MTU student research teams conducted experiments on the C9 in 2004, 2005, and 2007. In the most recent set of tests, researchers evaluated a proposed scheme for removing accumulated lunar dust from solar panels in conditions that simulated a lunar outpost (1/6th Earth gravity). In these tests a clear glass substrate was patterned with transparent electrodes and placed over a solar cell. By applying high-voltage radio-frequency signals to the electrodes, accumulated dust was repelled from the surface due to electrostatic forces. For more information on the Aerospace Enterprise view their web page at http://www.enterprise.mtu.edu/aerospace/
Oculus: a nanosat for Space Situational Awareness
Satellites, having very predictable orbits, are increasingly vulnerable to attack by both enemy countries and terrorists. Many nations and groups either have, or will have soon, access to space that they can exploit to gain an advantage during conflict. For the future of the US space force it is imperative to (1) protect US-flagged spacecraft from hostile disruption as well as (2) have an accurate knowledge of our adversaries' space capabilities. Currently, the US spacecraft tracking system relies on ground-based radar to detect satellites as they pass over monitoring stations. This system is slow to detect and respond to spacecraft which may have c
hanged their orbits between passes over the ground stations. Also, the ground-based radar is sufficient to determine the relative size of an object, however it is unable to provide information on vehicle configuration, capability, or intent. The Air Force Space Command's Strategic Master Plan has identified the need for space-based surveillance systems, including inspector satellites, that are capable of providing details of space objects unattainable by ground-based systems.
The MTU nanosatellite Oculus will serve as a test-bed for space-based surveillance technologies used to characterize resident space objects. The vehicle, weighing less than 30 kg, will carry a sophisticated imaging system developed by Raytheon Missile Systems of Tucson, AZ. Oculus will be capable of highly accurate three-axis control, allowing it to provide exquisite optical characterization of other spacecraft. For more information on the Aerospace Enterprise view their web page at http://www.aerospace.mtu.edu/aeroweb/
