The Space Systems research group is involved in aerospace engineering, ion space propulsion, planetary exploration, control systems, and ultra-strong composites.
The Michigan Tech Aerospace Engineering Research Center (MARC) is a focal point for activities related to aerospace engineering.
The Aerospace Enterprise team places an emphasis on space mission design and analysis, vehicle integration,systems engineering, and comprehensive ground testing and qualification.
The Institute for Ultra-Strong Composites by Computational Design (US-COMP) is a NASA Space Technology Research Institute awarded in 2017. Its mission is computational development of materials for space applications.
The Ion Space Propulsion Lab (ISP Lab) involves next-generation plasma thrusters for spacecraft.
The Multiplanetary INnovation Enterprise (MINE) seeks to design, test, and implement robotic technologies for extracting and using local resources, construction, and characterization in extreme environments.
The Planetary Surface Technology Development Lab (PSTDL) develops technology solutions for planetary surface exploration of the Moon, Mars, and beyond while training the next generation of engineers.
Faculty + Research = Discovery
Our department boasts world-class faculty who have access to numerous innovative research labs and are committed to discovery and learning.
This encompasses a range of research areas, experiences, and expertise related to space systems. Learn more about our faculty and their research interests:
Our faculty engage in a number of research projects, many of which are publicly funded.
A sample listing of recent research projects appears below. You can also view a broader list of research projects taking place across the mechanical engineering-engineering mechanics department.
In-SiTU Resource Utilization (ISRU) on Mars
- Where gypsum deposits ARE found on earth (blocks (not grains) of gypsum)
- What mining methods are employed typically on Earth
- What techniques are used for processing gypsum on Earth
- What characteristic particle size distributions do they result in
- Do empirical or analytical methods exist (and what are they) to estimate how much energy would be required to "crush" gypsum from a state with a larger characteristic dimension to a smaller one (by unit mass or by unit volume)?
- Visit a gypsum quarry/mine and factory to discuss processes in person and study applicability for Mars use based on Earth experience not typically documented.
- Discuss if any of the Earth methods for mining and processing are suitable for adaptation for Mars
- Discuss the most important trade-off factors for achieving the highest mass/power efficiency mining and processing of Mars gypsum for extracting water. Try to setup a relationship between the trade-off factors (e.g. size of feedstock particles/chunks and excavation energy vs. heating time and extraction percentage.
- Based on the identified trade-off factors, recommend the most mass/power effective method/process to extract gypsum on Mars and extract water from the gypsum deposit.
Stratus Meteorological CubeSat: Payload Integration and Mission Level Design:
Oculus-ASR Nanosatellite Flight Integration
Auris: A CubeSat to Characterize and Locate Geostationary Communication Emitters
Characterization Test-Bed for Nanostructured Propellants
At present there exists no single propulsion technology capable of meeting both orbit-raising and stationkeeping requirements for communications satellites. Contemporary satellites thus carry two completely separate propulsion systems and incur the mass penalty associated with each. It is conceivable that a single propellant could be used for both a high-thrust chemical thruster that performs orbit raising as well as a high-specific-impulse electric thruster to perform stationkeeping. In this case the mass burden on the spacecraft bus would be significantly reduced simply by eliminating one of the large propellant storage vessels. Although no single propellant has been identified yet, recent developments suggest that it is possible to synthesize custom nanostructured propellants that could be used in both chemical combustion-based thrusters as well as electrostatic thrusters.
The goal of work proposed here is to fabricate and implement an experimental test bed that is capable of fully characterizing the electrostatic acceleration and chemical combustion of nanostructured propellants for spacecraft propulsion. The instruments will be developed through collaboration between Michigan Technological University and the University of Maryland. The proposed test-bed represents the first-ever facility devoted to combustion and electrospray research on nanostructured colloidal propellants.
The investigators on this project together are presently engaged in DoD research with total funding exceeding $4M. Agencies supporting this research include Office of Naval Research, Air Force Office of Scientific Research, and the Defense Threat Reduction Agency. All of this work is devoted to studies, in one form or another, of the behavior of nano-structured propellants for either chemical or electric propulsion. The test equipment proposed here will be directly relevant to these on-going activities.
Trajectory Optimization for Solar Electric Propulsion Satellites
The investigation of a low cost SEP microsatellite capable of launching within an ESP A class rideshare opportunity. The research is focused is on optimizing the low-thrust trajectory to minimize satellite hardware and operation costs while maintaining the ESPA class requirements. In particular, the solar array and mission operation costs as a function of array power and inclination of the spacecraft orbit as it transits the radiation belts. As power increases, trip time and thus radiation exposure and operation costs decrease. However, large solar arrays increase cost and the mass reduces payload capability. Also, varying inclinations follow different trajectories through the radiation belts as they reach their final orbits. Trajectories that start at a higher inclination have a longer path, but pass through lower intensity radiation bands. This can decrease the size and costs of the solar arrays, but requires larger Δ Vs and reduces payload capabilities
Tasks and Deliverables:
1. Provide a trajectory optimization of the SolRider vehicle to minimize cost of the following orbit transfers:
2. Analysis should consider the following variables/factors. Values are provided in the Solar Rider specification.
a. Radiation degradation of solar arrays
b. Solar Array $/W
c. Solar Array kg/W
d. Propellant & Tank Mass
e. Mission operations cost: $/day
f. Thruster shut down and start up due to eclipse
g. Atmospheric Drag
a. For each transfer orbit:
i. Normalized Cost vs. Array Power
ii. Trip Time vs. A1Tay Power
iii. Payload Mass v. Array Power
iv. Radiation Degradation v. Array Power
b. For the LEO to GEO transfer orbit
i. Normalized Cost v. Initial Inclination
ii. Trip Time v. Initial Inclination
iii.. Payload Mass v. Initial Inclination
iv. Radiation Degradation v. Initial Inclination
c. Input files
d. Raw Output Data
Trajectory Analysis for NASA Asteroid Redirect Mission
Michigan AFRL Center of Excellence in Electric Propulsion (MACEEP)
This five year research program consists of research in three areas: electrospray propulsion, field-reversed configuration devices, and non-invasive plasma optical diagnostics.
1. Electrospray Propulsion
MTU has pioneered a unique micromachining technique for fabricating all-metal electrospray structures for space propulsion. Unlike devices built using silicon MEMS protocols, the all-metal emitters are suitable for use with reactive propellants such as AF315. The all-metal structures can also tolerate very high temperatures. The electrode needles in this array are solid tungsten, while the substrate is solid molybdenum. MTU will investigate the use of externally wetted emitters - as well as internally wetted capillaries for use as electrospray sources for space propulsion. Research will focus on the use of AF315 as a propellant. Investigations will address fabrication challenges, device performance, plume characterization, and spacecraft interaction.
2. Field-Reversed Configurations
The FRC presents a unique plasma geometry that is well suited for plasma propulsion.
Because the FRC plasmoid is not linked to the structural magnetic flux, the plasma is not attached to the open field lines and can be ejected from the formation region as a self-contained entity. Furthermore, FRCs result from inductive "electrodeless" formation, avoiding the failure mode imposed by electrode erosion that is common to contemporary plasma thrusters. Motivated by the surprising stability of FRCs and their ability to translate while remaining coherent, MTU and the Air Force Research Laboratory (AFRL) at Edwards AFB will collaborate on an investigation into the feasibility of FRC space propulsion. MTU has designed and built a unique co-axial FRC mounted to a large expansion chamber that will be used for MACEEP research.
The goal of MACEEP research will be to determine the optimal physical and electrical configuration of a coaxial FRC for space propulsion and to characterize the conversion of stored electrical energy into plasmoid kinetic energy during translation and ejection. MTU researchers will employ a number of diagnostic techniques - to include magnetic field probes, electrostatic probes, and optical diagnostics - to quantify the energy conversion process during FRC formation and ejection. Thrust will be estimated from exhaust plume properties.
3. Non-invasive Optical Diagnostics
MTU is currently developing an optical diagnostic technique that can, for the first time, obtain direct measurements of electron density and electron energy distribution function (EEDF) within the discharge chamber and near-field plume of a Hall thruster. The MTU technique uses a
1,000-mJ-per-pulse Nd-YAG laser to induce laser Thomson scattering (LTS) from the free electrons in a plasma. The scattered radiation is measured using a triple-grating spectrograph and electron-multiplied CCD camera with single-photon detection capability. The scattered spectra can directly provide density and EEDF without perturbing the plasma. Researchers will use MACEEP funding to demonstrate this technique and apply the measurement to Hall thrusters and FRC plasmas. It is anticipated that knowledge gained from LTS measurements will provide insight into Hall thruster cross-field mobility as well as FRC internal energy storage and conversion.
Electrospray from Magneto-Electrostatic Instabilities
The term "electrospray" refers to the charged droplets and molecular ions that are emitted from the meniscus of a conducting liquid due to a strong electric field. The applied electric field induces a layer of surface charge on the liquid resulting in an electrostatic stress on the surface; if the stress is strong enough to overcome liquid surface tension the result is an ejected beam of charged particles. In 2013 Meyer and King demonstrated a completely new mechanism of electrospray that is fundamentally different from anything observed to date. This new electrospray was enabled by a unique and exotic fluid that was synthesized for the first time by Jain and Hawkett in 2011. This new fluid is called an ionic liquid ferrofluid (ILFF), which is a superparamagnetic, electrically conductive, room-temperature molten salt. Because the ILFF is superparamagnetic it can be stressed by magnetic fields; because the ILFF is also electrically conductive it can be stressed by electric fields. Meyer and King induced a magnetostatic instability in the ILFF surface known as a Rosensweig instability, which caused a regular array of static fluid spikes in the free surface. An applied electric field then further stressed and deformed the magnetically formed peaks causing their amplitude to increase and tip radius to decrease. A sufficiently strong electric field was shown to cause electrospray emission from the tip of each spike in the array.
This combined magneto-electrostatic instability has never before been observed and hence no description is available. The phenomenon was observed in two different fluids and under various values of applied electric field, but systematic investigation of the effect has not yet been addressed. This document proposes an integrated experimental, theoretical, and numerical investigation of electrospray from Rosensweig-Taylor instabilities that is designed to uncover the governing processes in this new phenomenon. The goal of work proposed here is to quantify how the combination of electric and magnetic surface stress components affect electrospray behavior in a superparamagnetic liquid. A two year research effort is proposed to
• Design and fabricate an apparatus that isolates a single Rosensweig-Taylor tip and permits controlled variation of both electric and magnetic field
• Measure rheology, surface tension, magnetic nanoparticle concentration, and electric conductivity for each ionic liquid ferrofluid tested
• Measure the critical voltage required to induce electrospray from a magneto-electrostatic instability as a function of (I) fluid magnetization, (2) magnetic field strength, (3) and fluid conductivity
• Establish the relationship between applied voltage, spray current, and total spray mass flow as a function of magnetic field strength
• Measure the angular divergence of the emitted electrospray beam as a function of electric and magnetic field strength
• Numerically model the fluid emission site using molecular dynamics simulations
• Measure the mass-to-charge ratio of emitted products using mass spectrometry
• Attempt a theoretical description of the static instability as a function of fluid parameters and electric/magnetic field strength.