SBIR/STTR
Electron Kinetics in Hypersonic Plasmas, Phase I
Project Introduction
The goal of this SBIR project is to advance the state-of-the-art in computations of hypersonic plasmas by adding high-fidelity kinetic models for electrons. Electron kinetics affects plasma-chemical reactions and nonequilibrium radiation, which are important for designing hypersonic vehicles.
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Anticipated Benefits
This project will increase predictive capability of computational tools for simulations of the aerothermal environment around space vehicles at extreme Mach numbers. The new capabilities will find direct and immediate application in a multitude of NASA technology development programs related to access to space and planetary entry. Detailed treatment of electrons will reduce uncertainties and improve accuracy of collision-radiative models to predict radiation spectra and plasma signature. The accurate modeling of aerothermal environments is essential for predicting heat load and design of thermal protection systems (TPS) for space vehicles such as NASA's Orion spacecraft and the proposed Space Launch System. The modified UFS code will be used as a design tool for development of new generation vehicles for space exploration and components of future hypersonic spacecrafts. The new tool will help analyzing communication blackout problems and hypersonic flow control by electromagnetic field Technology applications beyond NASA include Ballistic Missile Defense and future hypersonic vehicles performing exo-atmospheric missile intercepts, nozzle expansion and thruster plume interaction. The new model will improve predictive capabilities for calculating the radiation signature of hypersonic plasmas. The tool will have an appeal to rocket engine manufacturers (e.g., ATK, Pratt & Whitney, and Aerojet) and to universities studying arc-jets, plasmatrons and other high enthalpy flow systems. The developed computational tool will be utilized for evaluation of plasma phenomena on advanced hypersonic vehicles such as the X-51 waverider, missile technologies such as the Next Generation Aegis Missile. Typical applications include communication blackout for hypersonic flights, plasma flow control for hypersonic vehicles, electric propulsion, and plasma plumes expanding through nozzles, and shock wave propagation through plasmas. The methodology and software will be extendable for analys
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Langley Research Center
(LaRC)
|
Lead Organization | NASA Center | Hampton, VA |
| CFD Research Corporation | Supporting Organization | Industry | Huntsville, AL |
Primary U.S. Work Locations
-
Virginia
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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Lead Center / Facility:
- Langley Research Center (LaRC)
Responsible Program:
- SBIR/STTR
Project Management
Program Director:
Program Manager:
Principal Investigator:
- Vladimir Kolobov
Project Duration
Start: Feb 2012
End: Aug 2012
Technology Maturity (TRL)
| Start: | 1 |
| Current: | 1 |
| Estimated End: | 3 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TA 9 Entry, Descent, and Landing Systems
- TA 9.1 Aeroassist and Atmospheric Entry
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This is a historic project that was completed before the creation of TechPort on October 1, 2012. Available data has been included. This record may contain less data than currently active projects.