{"project":{"acronym":"","projectId":18314,"title":"A high performance, electric pump-fed LOX / RP propulsion system","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":3,"currentTrl":4,"endTrl":4,"benefits":"A high-performance, pump-fed LOX / RP propulsion system can be expected to have several NASA applications including nano-sat launch, lunar ascent / descent (precursors, rovers, cargo, man-rated vehicles, etc.), planetary missions (ascent vehicles for payload and sample placement into orbit, sample return, etc.), and Near-Earth-Object (NEO) missions (sample return). Three specific applications that Ventions has already received customer level support from are: 1. 1st stage booster for LSP's NEXT launch vehicle; 2. Outer planet orbit capture / insertion for missions such as Europa and Uranus orbiters; and 3. Planetary ascent applications in the Mars Ascent Vehicle.
Non-NASA applications for high-performance micro-rocket engines enabled by the proposed pump technology are likely to include commercial / military launch vehicles for low-cost and on-demand access to space for a variety of micro / small satellite payloads, upper stage propulsion for orbit insertion of commercial satellites, apogee kick motors for orbit circularization of commercial satellites, etc. Additionally, the pump itself is expected to have non-aerospace applications in industrial cryogenic pumping applications, and as a replacement for small-scale, high-pressure liquid pumps. Four specific applications that Ventions has already received customer level support from are: 1. Prototype upper stage for DARPA's XS-1 program; 2. DARPA's next generation rocket engine exploring feasibility of modular rocket approaches such as aero-spike engines; 3. DARPA's ALASA program; and 4. Lunar lander propulsion for a commercial customer.","description":"To-date, the realization of small-scale, high-performance liquid bipropellant rocket engines has largely been limited by the inability to operate at high chamber pressures in a regeneratively-cooled environment using on-board pumps for propellant pressurization. Ventions seeks to fulfill this critical need by using a novel fabrication scheme that builds on previously-demonstrated technologies (under DARPA and NASA sponsored efforts) to design, fabricate and hot-fire test a pump-fed, 3,000lbf LOX/RP propulsion system.","startYear":2014,"startMonth":4,"endYear":2016,"endMonth":3,"statusDescription":"Completed","principalInvestigators":[{"contactId":2911,"canUserEdit":false,"firstName":"Adam","lastName":"London","fullName":"Adam London","fullNameInverted":"London, Adam","primaryEmail":"adam.london@ventions.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":3164121,"canUserEdit":false,"firstName":"Robert","lastName":"Johnson","fullName":"Robert Johnson","fullNameInverted":"Johnson, Robert","primaryEmail":"Robert.G.Johnson@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":[{"file":{"fileExtension":"pdf","fileId":293281,"fileName":"SBIR_S_2012_2_BC_E1.02-9215","fileSize":813979,"objectId":289800,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"794.9 KB"},"files":[{"fileExtension":"pdf","fileId":293281,"fileName":"SBIR_S_2012_2_BC_E1.02-9215","fileSize":813979,"objectId":289800,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"794.9 KB"}],"id":289800,"title":"Briefing Chart","description":"A high performance, electric pump-fed LOX / RP propulsion system, Phase II","libraryItemTypeId":1222,"projectId":18314,"primary":false,"publishedDateString":"","contentType":{"lkuCodeId":1222,"code":"DOCUMENT","description":"Document","lkuCodeTypeId":341,"lkuCodeType":{"codeType":"LIBRARY_ITEM_TYPE","description":"Library Item Type"}}},{"caption":"A high performance, electric pump-fed LOX / RP propulsion system, Phase II","file":{"fileExtension":"png","fileId":293676,"fileName":"SBIR_S_2012_2_BC_E1.02-9215","fileSize":851384,"objectId":290195,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"831.4 KB"},"files":[{"fileExtension":"png","fileId":293676,"fileName":"SBIR_S_2012_2_BC_E1.02-9215","fileSize":851384,"objectId":290195,"objectType":{"lkuCodeId":889,"code":"LIBRARY_ITEMS","description":"Library Items","lkuCodeTypeId":182,"lkuCodeType":{"codeType":"OBJECT_TYPE","description":"Object Type"}},"objectTypeId":889,"fileSizeString":"831.4 KB"}],"id":290195,"title":"Briefing Chart Image","description":"A high performance, electric pump-fed LOX / RP propulsion system, Phase II","libraryItemTypeId":1095,"projectId":18314,"primary":true,"publishedDateString":"","contentType":{"lkuCodeId":1095,"code":"IMAGE","description":"Image","lkuCodeTypeId":341,"lkuCodeType":{"codeType":"LIBRARY_ITEM_TYPE","description":"Library Item Type"}}}],"transitions":[{"transitionId":64728,"projectId":18314,"partner":"Other","transitionDate":"2014-04-01","path":"Advanced From","relatedProjectId":16641,"relatedProject":{"acronym":"","projectId":16641,"title":"Regeneratively-Cooled, Pump-Fed Propulsion Technology for Nano / Micro Satellite Launch Vehicles","startTrl":4,"currentTrl":5,"endTrl":5,"benefits":"The proposed nano launch vehicle is aimed at providing low-cost and on-demand insertion of NASA cube- and nano-satellites into LEO as primary payloads. This will change the current model of launching such satellites as secondary payloads (which are often constrained by requirements of the primary payload), thereby extending this capability to a wider range of NASA experimental missions requiring on-demand and low-cost insertion of small sattelites into specific orbits.
Non-NASA applications for the same will include DoD and military missions requiring rapid on demand access to space from anywhere in the world (based on ground or air-launch), as well as university and research satellites. Additionally, the small-scale thrust chamber assemblies and turbomachinery technology components developed for the launch vehicle are also expected to have widespread applications in other in-space propulsion systems, upper stages, and orbital insertion / maneuvering thrusters, etc.","description":"Ventions proposes the development of a pump-fed, 2-stage nano launch vehicle for low-cost on demand placement of cube and nano-satellites into LEO. The proposed vehicle uses high T/W and Isp pump-fed engines that operate at chamber pressures >750psi without the weight penalty of high pressure tanks, thereby realizing payload fractions in the 1-2% range. Ventions has already completed several component-level demonstrations in the area, and is proposing additional optimization / testing of a 5,000lbf LOX / RP-1 turbopump-fed engine as part of this Phase I in-order to demonstrate a flight-ready 1st stage propulsion system.","startYear":2013,"startMonth":5,"endYear":2013,"endMonth":11,"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
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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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