{"project":{"acronym":"","projectId":94532,"title":"Compact High Performance Plasma Propulsion System","primaryTaxonomyNodes":[{"taxonomyNodeId":10544,"taxonomyRootId":8816,"parentNodeId":10542,"level":3,"code":"TX01.2.2","title":"Electrostatic","definition":"This area covers electric propulsion systems that use electrostatic fields to ionize and accelerate a propellant.","exampleTechnologies":"Ion engines, hall thrusters, electrospray propulsion","hasChildren":false,"hasInteriorContent":true}],"startTrl":2,"currentTrl":3,"endTrl":3,"benefits":"The proposed system would propel a small earth orbiting or interplanetary spacecraft, targeting 12U and 27U CubeSats and small satellites. Applications include orbit raising and lowering, compensating for drag at low altitude, de-orbiting a spacecraft at EOL, changing orbit inclination and phase, NS and EW station-keeping in GEO, and constellation deployment and maintenance. The system also enables a low cost demonstration of HET magnetic shielding with iodine propellant.
The integrated system will be actively marketed spacecraft platform providers, targeting CubeSats and small commercial buses. Commercial and DoD applications include orbit raising and lowering, compensating for drag at low altitude, de-orbiting a spacecraft at EOL, changing orbit inclination and phase, NS and EW station-keeping in GEO, and constellation deployment and maintenance.","description":"The Compact High Performance Plasma Propulsion System (CHPPPS) is an electric propulsion system for 12U – 27U CubeSats. CHPPS is designed for high-value science missions which require high specific impulse, high reliability, and radiation tolerance. CHPPPS includes a low power Hall Effect Thruster (HET), a hollow cathode for neutralizing the ion beam, a propellant management system, and a power processing unit (PPU). The system is highly modular and appropriate for 12U – 27 U CubeSats in terms of size, mass, and power. CHPPPS may be as small as 4U, depending upon the fuel load and specific component selection. Thrust will be 3-8 mN, depending on the power supplied (60 – 135 W) and peak specific impulse will be >1100 s. The thruster will be fueled with xenon or with game-changing iodine, which stores as a solid at very low pressure and much higher density than xenon. The use of iodine significantly decreases spacecraft dry mass, and dramatically decreases propellant volume. The impact of switching from xenon to iodine is most significant for volume limited spacecraft like CubeSats. Whether the thruster is fueled by xenon or by iodine, the ion beam will be neutralized by a hollow cathode flowing noble gas. The thruster will be powered by a compact, radiation tolerant power processing unit (PPU) previously developed for NASA and Air Force applications. ACS may be provided by cold gas thrusters fed from the noble gas storage system. In Phase I, the system design will be detailed and studied. Work will include a proof of concept hardware demonstration at relevant power levels.","startYear":2018,"startMonth":7,"endYear":2019,"endMonth":2,"statusDescription":"Completed","principalInvestigators":[{"contactId":200442,"canUserEdit":false,"firstName":"James","lastName":"Szabo","fullName":"James Szabo","fullNameInverted":"Szabo, James","primaryEmail":"jszabo@busek.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 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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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