{"project":{"acronym":"","projectId":9903,"title":"Propellant Flow Actuated Piezoelectric Rocket Engine Igniter","primaryTaxonomyNodes":[{"taxonomyNodeId":10536,"taxonomyRootId":8816,"parentNodeId":10533,"level":3,"code":"TX01.1.3","title":"Cryogenic","definition":"Cryogenic propulsion systems or subsystems operate with propellants that are liquefied gases at low temperatures.","exampleTechnologies":"Liquid oxygen (LO2), methane (CH4) pressure-fed main engine LO2, CH4 pump-fed main engine LO2, liquid hydrogen (LH2) reaction and attitude control engine, LOX/RP, LH2/LOX based engine","hasChildren":false,"hasInteriorContent":true}],"startTrl":4,"currentTrl":7,"endTrl":7,"benefits":"Aside from the ULA and PWR applications mentioned above (both of which also provide non-NASA services to commercial satellite operations and military customers such as Air Force), other potential commercial aerospace and industrial applications include gas turbine igniters for aircraft or ground power applications, furnace combustor ignition, flare stack ignition systems for hydrogen or methane, etc.
Two specific commercial customers that regularly provide services for NASA have identified strong interest in this technology, with intent to implement the technology if Phase II development is successful. One application is a new gaseous H2/O2 attitude control and settling thruster currently under development by United Launch Alliance (ULA) for Atlas upper stage. The second application is a new ignition system for the Pratt and Whitney Rocketdyne (PWR) evolved RL-10 engine. Both ULA and PWR have stated their interest and intention to provide facility access and test opportunities concurrent with any Phase II effort. A third potential application is for ignition of any bi-propellant thrusters to be installed on the CRYOTE (Cryogenic Orbital Testbed) currently of interest to NASA and ULA. This testbed might use either the ULA thrusters mentioned above, or another engine identified by NASA. Numerous other NASA applications for very simple spark igniters are inevitable as small catalytic monopropellant (hydrazine) thrusters are replaced by cleaner bipropellant thrusters for satellite and upper stage attitude control purposes.","description":"Under a Phase 1 effort, IES successfully developed and demonstrated a spark ignition concept where propellant flow drives a very simple fluid mechanical oscillator to excite a piezoelectric crystal. The Phase 1 effort exceeded expectations, with the device demonstrating reliable ignition of both hydrogen and propane fuels, and achieving in excess of 1 million impact cycles (40,000 start cycles) during fatigue testing without measureable degradation. Several spin-off concepts were also identified that provide additional options for improving spark ignition system design. For Phase 2, IES proposes an accelerated, 18 month effort to refine design concepts and analysis tools, and then develop specific ignition system designs for two customer applications, with the intention of having these ignition systems demonstrated in engine ground testing during Phase 2 and ready to start flight qualification immediately following the Phase 2 effort. Both customers (United Launch Alliance and Pratt Whitney Rocketdyne) have expressed interest and commitment in participating in the Phase 2 activity, making engines and facilities available for development testing, and integrating any resulting viable products into their flight engines. The ULA application is a new gaseous bipropellant H2/O2 attitude control thruster, for which the piezoelectric igniter is ideal as a simple, direct ignition source. The PWR application is for an evolved RL-10 study currently underway, for which the piezoelectric system might be scaled up or used as a pilot igniter for a torch, or make use of another spin-off concept that was identified during the Phase 1 effort. The timing of this Phase 2 effort coincides perfectly with near term needs of both these customers, as well as for other small engine applications in work to replace catalytic hydrazine engines with bi-propellant engines that will require a simple and reliable ignition source.","startYear":2011,"startMonth":6,"endYear":2013,"endMonth":5,"statusDescription":"Completed","principalInvestigators":[{"contactId":314652,"canUserEdit":false,"firstName":"Mark","lastName":"Wollen","fullName":"Mark A Wollen","fullNameInverted":"Wollen, Mark A","middleInitial":"A","primaryEmail":"mwollen@iesnet.com","publicEmail":true,"nacontact":false}],"programDirectors":[{"contactId":206378,"canUserEdit":false,"firstName":"Jason","lastName":"Kessler","fullName":"Jason L Kessler","fullNameInverted":"Kessler, Jason L","middleInitial":"L","primaryEmail":"jason.l.kessler@nasa.gov","publicEmail":true,"nacontact":false}],"programExecutives":[{"contactId":215154,"canUserEdit":false,"firstName":"Jennifer","lastName":"Gustetic","fullName":"Jennifer L Gustetic","fullNameInverted":"Gustetic, Jennifer L","middleInitial":"L","primaryEmail":"jennifer.l.gustetic@nasa.gov","publicEmail":true,"nacontact":false}],"programManagers":[{"contactId":62051,"canUserEdit":false,"firstName":"Carlos","lastName":"Torrez","fullName":"Carlos Torrez","fullNameInverted":"Torrez, Carlos","primaryEmail":"carlos.torrez@nasa.gov","publicEmail":true,"nacontact":false}],"projectManagers":[{"contactId":3164438,"canUserEdit":false,"firstName":"Bill","lastName":"Studak","fullName":"Bill Studak","fullNameInverted":"Studak, Bill","primaryEmail":"joseph.w.studak@nasa.gov","publicEmail":true,"nacontact":false},{"contactId":461333,"canUserEdit":false,"firstName":"Theresa","lastName":"Stanley","fullName":"Theresa M Stanley","fullNameInverted":"Stanley, Theresa M","middleInitial":"M","primaryEmail":"theresa.m.stanley@nasa.gov","publicEmail":true,"nacontact":false}],"website":"","libraryItems":[],"transitions":[{"transitionId":66811,"projectId":9903,"partner":"Other","transitionDate":"2011-06-01","path":"Advanced From","relatedProjectId":9034,"relatedProject":{"acronym":"","projectId":9034,"title":"Propellant Flow Actuated Piezoelectric Rocket Engine Igniter","startTrl":3,"currentTrl":5,"endTrl":5,"benefits":"The igniter proposed is applicable to virtually any non-NASA rocket engine application, as well as having application as an ignition source for commercial or military gas turbine engines, or anywhere that an ignition source is required to coincide with the initiation of fuel flow (e.g. flame throwers, flare stacks, industrial gas heaters).
Reliable and simplified ignition sources are critical for virtually all bi-propellant rocket engines. The proposed innovation has the potential to provide a reliable, properly timed ignition source for new rocket engines, as well as being a potential retrofit option to replace costly or complex igniters on currently operational engines. The technology is applicable to virtually any size engine, from attitude control to main booster engine scale. For small RCS engines, it is particularly suitable due to its simplicity, potentially very small size, and ability to repetitively generate a reliable, well timed ignition source.","description":"Spark ignition of a bi-propellant rocket engine is a classic, proven, and generally reliable process. However, timing can be critical, and the control logic, additional electronic components and wiring adds complexity, cost and weight. These factors can be especially undesirable for small attitude or reaction control engines. The proposed innovation uses a novel method to excite a piezo-ceramic crystal using the initiation of propellant flow to the engine. When the propellant valves are opened, the precise timing of the spark relative to propellant flow, as well as the flow start transient, are governed by the geometry of the device. Hence, precise, repeatable start conditions should be achieved with no additional control logic or complexity. Furthermore, the piezo-ceramic crystal is integral to (and embedded in) the igniter body, thereby completely eliminating external wiring and associated complexity. A bench-top demonstration of one manifestation of the device (incorporating only one very simple moving part) has already demonstrated basic feasibility. Other manifestations with no moving parts what-so-ever (at the macroscopic scale) may also be viable, and will be investigated. Phase 1 TLR advancement goal is from 3 to 5, with Phase 2 goal of 7.","startYear":2010,"startMonth":1,"endYear":2010,"endMonth":7,"statusDescription":"Completed","website":"","program":{"acronym":"SBIR/STTR","active":true,"description":"
The NASA SBIR and STTR programs fund the research, development, and demonstration of innovative technologies that fulfill NASA needs as described in the annual Solicitations and have significant potential for successful commercialization. If you are a small business concern (SBC) with 500 or fewer employees or a non-profit RI such as a university or a research laboratory with ties to an SBC, then NASA encourages you to learn more about the SBIR and STTR programs as a potential source of seed funding for the development of your innovations.
The SBIR and STTR programs have 3 phases:
The SBIR and STTR Phase I contracts last for 6 months with a maximum funding of $125,000, and Phase II contracts last for 24 months with a maximum funding of $750,000 - $1.5 million.
Opportunity for Continued Technology Development Post-Phase II:
The NASA SBIR/STTR Program currently has in place two initiatives for supporting its small business partners past the basic Phase I and Phase II elements of the program that emphasize opportunities for commercialization. Specifically, the NASA SBIR/STTR Program has the Phase II Enhancement (Phase II-E) and Phase II eXpanded (Phase II-X) contract options.
Please review the links below to obtain more information on the SBIR/STTR programs.
Provides an overview of the SBIR and STTR programs as implemented by NASA
Provides access to the annual SBIR/STTR Solicitations containing detailed information on the program eligibility requirements, proposal instructions and research topics and subtopics
Schedule and links for the SBIR/STTR solicitations and selection announcements
Federal and non-Federal sources of assistance for small business
Search our complete archive of awarded project abstracts to learn about what NASA has funded
Still have questions? Visit the program FAQs
","programId":73,"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":36648,"title":"Small Business Innovation Research/Small Business Tech Transfer"},"lastUpdated":"2024-1-10","releaseStatusString":"Released","viewCount":560,"endDateString":"Jul 2010","startDateString":"Jan 2010"},"infoText":"Advanced from another project within the program","infoTextExtra":"Another project within the program (Propellant Flow Actuated Piezoelectric Rocket Engine Igniter)","dateText":"June 2011"},{"transitionId":66810,"projectId":9903,"transitionDate":"2013-05-01","path":"Closed Out","closeoutDocuments":[{"title":"Final Summary Chart","file":{"fileExtension":"pdf","fileId":306567,"fileName":"206553_05_31_2013_01_59_29","fileSize":178179,"objectId":66810,"objectType":{"lkuCodeId":1841,"code":"TRANSITION_FILES","description":"Transition Files","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"fileSizeString":"174.0 KB"},"transitionId":66810,"fileId":306567}],"infoText":"Closed out","infoTextExtra":"","dateText":"May 2013"}],"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":"SBIR/STTR","active":true,"description":"The NASA SBIR and STTR programs fund the research, development, and demonstration of innovative technologies that fulfill NASA needs as described in the annual Solicitations and have significant potential for successful commercialization. If you are a small business concern (SBC) with 500 or fewer employees or a non-profit RI such as a university or a research laboratory with ties to an SBC, then NASA encourages you to learn more about the SBIR and STTR programs as a potential source of seed funding for the development of your innovations.
The SBIR and STTR programs have 3 phases:
The SBIR and STTR Phase I contracts last for 6 months with a maximum funding of $125,000, and Phase II contracts last for 24 months with a maximum funding of $750,000 - $1.5 million.
Opportunity for Continued Technology Development Post-Phase II:
The NASA SBIR/STTR Program currently has in place two initiatives for supporting its small business partners past the basic Phase I and Phase II elements of the program that emphasize opportunities for commercialization. Specifically, the NASA SBIR/STTR Program has the Phase II Enhancement (Phase II-E) and Phase II eXpanded (Phase II-X) contract options.
Please review the links below to obtain more information on the SBIR/STTR programs.
Provides an overview of the SBIR and STTR programs as implemented by NASA
Provides access to the annual SBIR/STTR Solicitations containing detailed information on the program eligibility requirements, proposal instructions and research topics and subtopics
Schedule and links for the SBIR/STTR solicitations and selection announcements
Federal and non-Federal sources of assistance for small business
Search our complete archive of awarded project abstracts to learn about what NASA has funded
Still have questions? Visit the program FAQs
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