MIRO cSETR actively conducts fundamental and applied research and education in propulsion and in-situ resource utilization. By developing and advancing bodies of knowledge in ignition physics, combustor technology, fluid properties and the associative processes, the research is applicable to a wide range of aerospace, energy and academic beneficiaries. In-situ resource extraction is also a component and includes investigation of numerous methods, such as thermochemical, combustion-based, and biological means. Computational modeling and analysis compliments the experimental and application portions of the research.
Using advanced diagnostics in fundamental and applied experiments within a varied range of combustor and propellant types, MIRO cSETR has improved combustion, propulsion, and fluid flow systems. MIRO cSETR has progressed from a micropropulsion specialty to larger attitude and descent class thruster research and bodies of knowledge applicable to all areas of propulsion.
The work is accomplished through research grants with federal agencies, national laboratories, affiliate universities and industrial task orders. The propulsion area is complimented by parallel research in combustion, materials and thermal barrier coatings and aerospace structures.
- Thruster Development
- Bi-Propellant Micropropulsion (Milli-Newton/Micro-Newton Thrusters)
- LOX/Hydrocarbon, Hydrogen Peroxide Thrusters
- Heat Transfer and Thermo-Mechanical Characterization
- Alternative (Non-Toxic) Propellants
- LOX/Methane, Kerosene, Ethanol, Hydrogen, Hydrogen Peroxide
- Injectors & Igniters
- Micro-Swirl Injectors
- Multi-Propellant Injectors
- Thermal and Spark Igniters for LOX/Hydrocarbon
- Miniaturized Space Systems
- Next Generation Divert and Attitude Control Engines
- Propellant Pressurization
- Micro-Turbo Pumps, Micro-Nozzles and Flows
- In-Situ Resource Utilization
- Chemical Extraction