{"project":{"acronym":"","projectId":93877,"title":"Plasma Based Energy Deposition for Mitigation of Sonic Boom: Experiment to demonstrate viability, Year 1","primaryTaxonomyNodes":[{"taxonomyNodeId":10954,"taxonomyRootId":8816,"parentNodeId":10946,"level":3,"code":"TX15.1.8","title":"Ground and Flight Test Technologies","definition":"This area covers advanced ground test capabilities, techniques, and strategies to enable development and validation of atmospheric flight vehicle concepts, validation of new CFD technology, and vehicle and flow research.","exampleTechnologies":"Technologies that incorporate advanced sensors, measurement techniques, and processes into ground testing in wind tunnels, ballistic ranges, water channels, arc jets and other ground test facilities as well as similar technologies for flight testing. These test technologies include advanced pressure and temperature measurement, qualitative and quantitative off-body measurement techniques, advanced static and dynamic pressure sensitive paint, advanced load balances, including flow-through balances for powered testing, and model deformation measurement systems for aeroelastic test. Flight testing leverages similar technology and extends into remote thermal imaging techniques for direct aerothermodynamic measurements of flight vehicles and technologies like background oriented Schlieren techniques for off-body flow measurement, visualization and interaction.","hasChildren":false,"hasInteriorContent":true}],"startTrl":3,"currentTrl":3,"endTrl":3,"benefits":"
There is currently a substantial amount of empirical data regarding the effect of plasma generated by electric discharge, focused lasers and or microwave energy on shockwaves generated by aerodynamic shapes in supersonic flow. However, all of this data is from small scale wind tunnel tests and the positive effect of the plasma on the models can only be observed near the model. The goal of this work is to acquire data further away from the model to see if the modified shockwaves remain modified as they propagate away from the model or if they reform to their original form prior to the introduction of the plasma. If we can show that the influence of the plasma on the shock waves do indeed continue as we move away from the model, this would support further research in the area of plasmadynamics applied to sonic boom reduction.
","description":"By the end of this year, we intend to have a two inch diameter, operational test article which continuously generates a symmetric plasma discharge. We intend to ensure this symmetry by adding a magnet to the original one inch diameter design which was used to demonstrate this shock wave attenuation effect in an earlier wind tunnel test. We will be testing a slightly larger model in order to better instrument the test article. This larger model will also add to our understanding of how the size of the model affects the amount of power needed to attenuate the shock waves. We also intend to demonstrate that the discharge from this new model significantly attenuates any shock waves generated at flight relevant conditions in a supersonic wind tunnel. The next step after this year is to mount this test article to the \"Big Red\" flight test fixture underneath a NASA F15, fly at Mach 1.6 at 31kft, 32kft and 33kft and possibly Mach 1.8 at 33kft. And use AirBOS to image the shockwaves coming off of the model with plasma on and plasma off.
","destinations":[{"lkuCodeId":1543,"code":"EARTH","description":"Earth","lkuCodeTypeId":526,"lkuCodeType":{"codeType":"DESTINATION_TYPE","description":"Destination Type"}}],"startYear":2017,"startMonth":10,"endYear":2018,"endMonth":9,"statusDescription":"Completed","principalInvestigators":[{"contactId":13533,"canUserEdit":false,"firstName":"Aliyah","lastName":"Ali","fullName":"Aliyah N Ali","fullNameInverted":"Ali, Aliyah N","middleInitial":"N","primaryEmail":"aliyah.n.ali@nasa.gov","publicEmail":true,"nacontact":false}],"programDirectors":[{"contactId":335305,"canUserEdit":false,"firstName":"Michael","lastName":"Lapointe","fullName":"Michael R Lapointe","fullNameInverted":"Lapointe, Michael R","middleInitial":"R","primaryEmail":"michael.r.lapointe@nasa.gov","publicEmail":true,"nacontact":false}],"programExecutives":[{"contactId":392233,"canUserEdit":false,"firstName":"Richard","lastName":"Howard","fullName":"Richard W Howard","fullNameInverted":"Howard, Richard W","middleInitial":"W","primaryEmail":"richard.w.howard@nasa.gov","publicEmail":true,"nacontact":false}],"programManagers":[{"contactId":112848,"canUserEdit":false,"firstName":"David","lastName":"Voracek","fullName":"David F Voracek","fullNameInverted":"Voracek, David F","middleInitial":"F","primaryEmail":"david.f.voracek@nasa.gov","publicEmail":true,"nacontact":false}],"website":"https://www.nasa.gov/directorates/spacetech/innovation_fund/index.html#.VQb6gUjJzyE","libraryItems":[],"transitions":[{"transitionId":53577,"projectId":93877,"partner":"Other","transitionDate":"2018-10-01","path":"Advanced To","relatedProjectId":146146,"relatedProject":{"acronym":"","projectId":146146,"title":"Plasma Based Energy Deposition for Mitigation of Sonic Boom Experiment to demonstrate viability - Wind Tunnel Test, Year 2","startTrl":4,"currentTrl":5,"endTrl":5,"benefits":"Acquire far field data to show that the positive effects of plasma based energy deposition via electric discharge extends beyond the near field. Show that this is a viable method of sonic boom mitigation worth further in-depth study to investigate full scale implementation. If successful, this project will revolutionize commercial supersonic transport as we know it. It has the potential to loosen the current design restrictions on commercial supersonic transport aircraft. Allowing for wider bodied aircraft with improved handling capability at lower speed. It also has the potential to allow for improved control authority during supersonic flight.
","description":"With regards to plasma generated by electric discharge, we plan to demonstrate the effect of plasma based energy deposition on the strength of the shock waves in the far field by conducting the experiment in flight. Wind tunnel test to confirm that electric discharge on the tip of a 2 diameter model with a magnet in the nose, in Mach 1.6 flow will produce significant shock attenuation
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The focus for the program is on validating, developing, and testing new and innovative technologies.
The current technology areas for the projects included:
AFRC is currently looking into following Technical Capability areas (not in any priority order and not all inclusive):
1. Small launch Space Systems
Develop small launch space systems such as horizontal rockets that could launch to orbit small free-flying space platforms (e.g., cuestas, nanosats, picosats).
2. Altitude Compensating Rocket Systems
Design, build, and test altitude compensating rocket systems or sub-systems designed to operate the rocket efficiently across a wide range of altitudes. Subsystems such as Altitude Compensating Nozzles are being considered.
3. Aero Gravity Assist Systems
Design, build, and test an Aerogravity assist system which uses a close approach to the planet, dipping into the atmosphere, so the spacecraft can also use aerodynamic lift to further curve the trajectory.
4. Launch Vehicle and Spacecraft Adaptive Controls
Develop and test adaptive controls architectures specifically tailored for application to launch vehicles. Adaptive Controls for launch vehicles would include unique features of the aerospace vehicle, such as control-structure interaction, propellant slosh, sensor performance, and actuator dynamics. In addition, the analysis, verification, and flight certification framework for the control system must be addressed.
5. Autonomous Systems
AFRC is exploring concepts for advanced autonomous systems and collaborative autonomous operations that could be applied across aerospace vehicles to enhance effectiveness, survivability, and affordability.
6. Autonomy in a Safety Critical Framework
Armstrong Flight Research Center is interested in the flight demonstration of high level autonomy in a safety critical framework with applicability to man-rated air and space vehicles. This high level of autonomy is enabled through the use of multiple sensor platforms and algorithms with high computational demands. Increased computational capability through embedded high performance computing and implementation of resource efficient algorithms is needed to support this integration. Research into embedded high performance computing using multi-core processors, FPGA, GPU, DSP and associated development of toolchains and algorithms targeted to these platforms is needed in order to reduce the Size, Weight, and Power (SWaP) of the flight vehicles..
7. Space Weather Systems
Design, develop, and test measurement systems to provide the capability for on-demand, validated, and archived radiation measurements related to human tissue and avionics silicon upset concerns.
8. Electromagnetically Boosted Rockets
One possible solution is to use an electromagnetic linear motor boost system to supplement the use of first stage booster rockets and rocket clusters. China Lake is currently advocating to NAVAIR to initiate a study of long term capital costs and recurring system operational costs of the use of an electromagnetic linear motor booster system for their rocket sled tracks as compared to the long term operational system costs of moving to a newer line of booster rocket production.
","parentProgram":{"acronym":"CIF","active":true,"description":"
Through the Center Innovation Fund, the Space Technology Mission Directorate allocates a small portion of the NASA workforce and procurement budget to internal research and development to feed early stage innovation in technology and exploration. Activities with in the Center Innovation Fund are proposed and led by NASA scientists and engineers. These activities and creative initiatives pursue emerging technologies that leverage talent and capabilities at the NASA Centers.
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The focus for the program is on validating, developing, and testing new and innovative technologies.
The current technology areas for the projects included:
AFRC is currently looking into following Technical Capability areas (not in any priority order and not all inclusive):
1. Small launch Space Systems
Develop small launch space systems such as horizontal rockets that could launch to orbit small free-flying space platforms (e.g., cuestas, nanosats, picosats).
2. Altitude Compensating Rocket Systems
Design, build, and test altitude compensating rocket systems or sub-systems designed to operate the rocket efficiently across a wide range of altitudes. Subsystems such as Altitude Compensating Nozzles are being considered.
3. Aero Gravity Assist Systems
Design, build, and test an Aerogravity assist system which uses a close approach to the planet, dipping into the atmosphere, so the spacecraft can also use aerodynamic lift to further curve the trajectory.
4. Launch Vehicle and Spacecraft Adaptive Controls
Develop and test adaptive controls architectures specifically tailored for application to launch vehicles. Adaptive Controls for launch vehicles would include unique features of the aerospace vehicle, such as control-structure interaction, propellant slosh, sensor performance, and actuator dynamics. In addition, the analysis, verification, and flight certification framework for the control system must be addressed.
5. Autonomous Systems
AFRC is exploring concepts for advanced autonomous systems and collaborative autonomous operations that could be applied across aerospace vehicles to enhance effectiveness, survivability, and affordability.
6. Autonomy in a Safety Critical Framework
Armstrong Flight Research Center is interested in the flight demonstration of high level autonomy in a safety critical framework with applicability to man-rated air and space vehicles. This high level of autonomy is enabled through the use of multiple sensor platforms and algorithms with high computational demands. Increased computational capability through embedded high performance computing and implementation of resource efficient algorithms is needed to support this integration. Research into embedded high performance computing using multi-core processors, FPGA, GPU, DSP and associated development of toolchains and algorithms targeted to these platforms is needed in order to reduce the Size, Weight, and Power (SWaP) of the flight vehicles..
7. Space Weather Systems
Design, develop, and test measurement systems to provide the capability for on-demand, validated, and archived radiation measurements related to human tissue and avionics silicon upset concerns.
8. Electromagnetically Boosted Rockets
One possible solution is to use an electromagnetic linear motor boost system to supplement the use of first stage booster rockets and rocket clusters. China Lake is currently advocating to NAVAIR to initiate a study of long term capital costs and recurring system operational costs of the use of an electromagnetic linear motor booster system for their rocket sled tracks as compared to the long term operational system costs of moving to a newer line of booster rocket production.
","parentProgram":{"acronym":"CIF","active":true,"description":"
Through the Center Innovation Fund, the Space Technology Mission Directorate allocates a small portion of the NASA workforce and procurement budget to internal research and development to feed early stage innovation in technology and exploration. Activities with in the Center Innovation Fund are proposed and led by NASA scientists and engineers. These activities and creative initiatives pursue emerging technologies that leverage talent and capabilities at the NASA Centers.
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