{"project":{"acronym":"","projectId":32954,"title":"Coreless Linear Induction Motor (LIM) for Space-borne Electro-magnetic Mass Driver Applications Element","startTrl":4,"currentTrl":5,"endTrl":5,"benefits":"A coreless LIM can enable an alternative solution to asteroid re-direct missions. The application of this technology offers distinct system life cycle cost advantages. A coreless LIM will enable high speed electromagnetic space-faring mass driver propulsion, which introduces a disruptive technology into conventional space mission system design, mission performance, and the advancement of space technology. A coreless LIM offers the potential of creating a self-sustaining, low life-cycle cost interplanetary space transportation and resource supply infrastructure that can be more efficient than space-faring all chemical propulsion which have high maintenance purification and refining processes. Although chemical propulsion systems can out-perform many other space propulsion system in the near-term, the mass driver system provides a low maintenance supply chain backbone.","description":"Large scale linear induction motors use ferromagnetic cores, but at high speed these cores choke the system's ability to transform electrical energy into mechanical energy. Use of composite materials can be used to replace structural support previously provided by ferromagnetic materials. However, coreless motors lack the structural support usually provided by the iron core in a traditional LIM. Designing a rigid coreless LIM will require material studies and detailed thermal/structural analysis.","startYear":2014,"startMonth":11,"endYear":2015,"endMonth":10,"statusDescription":"Completed","principalInvestigators":[{"contactId":104277,"canUserEdit":false,"firstName":"David","lastName":"Boyle","fullName":"David R Boyle","fullNameInverted":"Boyle, David R","middleInitial":"R","primaryEmail":"dave.boyle@honeywell.com","publicEmail":false,"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":"","libraryItems":[{"caption":"Mass Driver attached to asteroid ejects the crushed asteroid matter as propellant","file":{"fileExtension":"jpg","fileId":266872,"fileName":"image","fileSize":173214,"objectId":266603,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"169.2 KB"},"files":[{"fileExtension":"jpg","fileId":266872,"fileName":"image","fileSize":173214,"objectId":266603,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"169.2 KB"}],"id":266603,"title":"Mass Driver attached to asteroid ejects the crushed asteroid matter as propellant","description":"Mass Driver attached to asteroid ejects the crushed asteroid matter as propellant","libraryItemTypeId":1095,"projectId":32954,"primary":false,"publishedDateString":"","contentType":{"lkuCodeId":1095,"code":"IMAGE","description":"Image","lkuCodeTypeId":341,"lkuCodeType":{"codeType":"LIBRARY_ITEM_TYPE","description":"Library Item Type"}}},{"caption":"Rendering of a coreless LIM","file":{"fileExtension":"jpg","fileId":266599,"fileName":"image","fileSize":5813,"objectId":266252,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"5.7 KB"},"files":[{"fileExtension":"jpg","fileId":266599,"fileName":"image","fileSize":5813,"objectId":266252,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"5.7 KB"}],"id":266252,"title":"Rendering of a coreless LIM","description":"Rendering of a coreless LIM","libraryItemTypeId":1095,"projectId":32954,"primary":true,"publishedDateString":"","contentType":{"lkuCodeId":1095,"code":"IMAGE","description":"Image","lkuCodeTypeId":341,"lkuCodeType":{"codeType":"LIBRARY_ITEM_TYPE","description":"Library Item Type"}}},{"file":{"fileExtension":"pdf","fileId":267008,"fileName":"S3008508016022415030","fileSize":329935,"objectId":266773,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"322.2 KB"},"files":[{"fileExtension":"pdf","fileId":267008,"fileName":"S3008508016022415030","fileSize":329935,"objectId":266773,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"322.2 KB"}],"id":266773,"title":"TechPort STMD Data Upload Agreement","description":"STMD 2016","libraryItemTypeId":1222,"projectId":32954,"primary":false,"publishedDateString":"","contentType":{"lkuCodeId":1222,"code":"DOCUMENT","description":"Document","lkuCodeTypeId":341,"lkuCodeType":{"codeType":"LIBRARY_ITEM_TYPE","description":"Library Item Type"}}}],"transitions":[{"transitionId":53830,"projectId":32954,"partner":"Other","transitionDate":"2014-11-01","path":"Advanced From","relatedProjectId":32420,"relatedProject":{"acronym":"","projectId":32420,"title":"Bio-Mimetic Concepts for Next-Generation Turbomachinery","startTrl":5,"currentTrl":6,"endTrl":6,"benefits":"
The anticipated results will illustrate the potential benefits of looking to billions of years of evolution and natural selection to enhance man-made designs. Based on current results, the bio-inspired vortex shedding mitigation strategy will allow for lower fluid induced vibrations and noise. This is beneficial to the noise mitigation efforts in aero-propulsion technology. Further, the bio-inspired airfoil geometries have been shown to exhibit higher angles of attack before stall which, for example, may allow aero-propulsion technologies to extract more work per turbine stage. This may lead to lighter, quieter aero-propulsion technology.
","description":"Harbor Seal whisker samples were obtained from the San Diego Zoo for analysis using both microscopes and computed tomography (CT) to obtain an accurate 3D geometry. The geometry was then parameterized in a CAD model based on seven variables which accurately represent the whisker geometry. The new HPC hardware consists of four Intel Xeon 7120A Phi cards which provides access to 244 cores (4.8 teraflops) of computing resources in one office environment workstation. A novel CFD code (XFlow) is utilized which allows for very fast and accurate large eddy simulations (LES), based on the Lattice-Boltzmann method. The use of modern computing equipment coupled with innovative CFD tools allows for rapid design evaluations on the order of hundreds or even thousands of computed results. In order to automate the search for an optimal geometry, a software integration and optimization tool is used to iterate though many designs to find a set of optimal solutions. The first application of interest demonstrates that this synthetic evolution architecture does find the Harbor Seal whisker geometry to be an optimal solution based on the two objectives of minimizing the RMS vortex induced vibrations (VIV) and minimizing induced drag. The parameterized geometry initially begins as a perfect cylinder, which exhibits very poor RMS VIV and drag characteristics. After several hundred iterations driven by a global optimization routine, the optimized geometry converged to a shape very similar to the Harbor Seal whisker. This automated architecture will be implemented to drive the optimization of bio-inspired airfoils towards increased performance characteristics and lower noise signatures. The disrupted vortex shedding characteristics enhances trailing edge wake dissipation as well as shifting wake frequencies higher past the audible range.","startYear":2014,"startMonth":11,"endYear":2015,"endMonth":10,"statusDescription":"Completed","website":"https://www.nasa.gov/directorates/spacetech/home/index.html","program":{"acronym":"GRC CIF","active":true,"description":"Tthe goal of the Center Innovation Fund is to stimulate and encourage creativity and innovation in addressing the technology needs of NASA and the Nation. The GRC Center Innovation Fund is intended to provide GRC Civil Servants, potentially partnering with external organizations and other NASA Centers, with the opportunity to develop new ideas toward this goal, and to pursue their intellectual growth in areas that are deemed to be of strategic importance to the Center. The projects are high payback, highly innovative research proposals that could significantly impact future GRC programs.
","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.
","programId":64,"responsibleMd":{"acronym":"STMD","canUserEdit":false,"city":"","external":false,"linkCount":0,"organizationId":4875,"organizationName":"Space Technology Mission Directorate","organizationType":"NASA_Mission_Directorate","naorganization":false,"organizationTypePretty":"NASA Mission Directorate"},"responsibleMdId":4875,"stockImageFileId":36643,"title":"Center Innovation Fund"},"parentProgramId":64,"programId":162,"responsibleMd":{"acronym":"STMD","canUserEdit":false,"city":"","external":false,"linkCount":0,"organizationId":4875,"organizationName":"Space Technology Mission Directorate","organizationType":"NASA_Mission_Directorate","naorganization":false,"organizationTypePretty":"NASA Mission Directorate"},"responsibleMdId":4875,"stockImageFileId":36645,"title":"Center Innovation Fund: GRC CIF"},"lastUpdated":"2023-9-20","releaseStatusString":"Released","viewCount":30,"endDateString":"Oct 2015","startDateString":"Nov 2014"},"infoText":"Advanced from another project within the program","infoTextExtra":"Another project within the program (Bio-Mimetic Concepts for Next-Generation Turbomachinery)","dateText":"November 2014"}],"primaryImage":{"file":{"fileExtension":"jpg","fileId":266599,"fileSizeString":"0 Byte"},"id":266252,"description":"Rendering of a coreless LIM","projectId":32954,"publishedDateString":""},"responsibleMd":{"acronym":"STMD","canUserEdit":false,"city":"","external":false,"linkCount":0,"organizationId":4875,"organizationName":"Space Technology Mission Directorate","organizationType":"NASA_Mission_Directorate","naorganization":false,"organizationTypePretty":"NASA Mission Directorate"},"program":{"acronym":"AFRC CIF","active":true,"description":"
The Armstrong Flight Research Center is NASA’s primary center for atmospheric flight research and operations, with a vision “to fly what others only imagine.” We believe that flight validation and research is one of the crucial phases within the advancement of any NASA technology, and it is often the barrier to technology utilization by the private sector. We also believe that aerospace technology can be enhanced through flight early in the Technology Readiness Level (TRL) lifecycle. In fact, some research can be done only in flight. The CIF projects are examples of aerospace technologies that are theoretically advantageous but have had little TRL advancement or are at too early of a technology level for support through a NASA mission.
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":"
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