SBIR/STTR Research Award

Propellant Storage and Distribution System Based on Textured Ceramic Valves for Xenon Electric Propulsion Systems

Award identifier f68a0fd7afdfd9474858f280dd0162883da3394cd79ab67bf463342c95ea855bAwarding agency National Aeronautics and Space Administration

Award amount

$749,184

Program and phase

STTR · Phase II

Award year

2021

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Award details

Awarding agency
National Aeronautics and Space Administration
Branch
Not reported
Recipient company
QORTEK INC
Proposal award date
2021-01-26
Contract end date
2023-01-25
UEI
TLD8L3APDZM3
Solicitation number
STTR_19_P2
Topic code
T2

Research abstract

The central thrust of this program is to provide NASA with higher performance components that can engender large advances in performance of satellite thruster systems while also introducing large SWaP savings and improved reliability as to meet the needs of the rapidly increasing smaller satellite market.nbsp; QorTek is proposing a revolutionary design of a subcompact solid-state (textured ceramic actuated) flow control systems for electric propulsion system thrusters (cathode tubes) such as envisaged Xe, Ar, Kr, He, or I.nbsp; At under 12 cu-cm volume, and operating at under 2mW, these new flow control components will introduce large power savings for most EP thruster systems being designed for small satellites and other mission equipment (included landed equipment).nbsp; Designed to benbsp;the first ever EP flow controllers that can function to high temperatures (gt; 300deg;C) opening a newnbsp;design where the controller is directly mated to the thruster as to reduce downstream tubing, reduce propellant waste, and accelerate acceptance testing as well as they are readily amenable to radhard implementation ndash; including their subcompact drive/control electronics employing recent advances at QorTek. Although the initial system is targeted toward NASA Class D missions, the extremely high reliability of our solid-state drive technology will enable all many NASA and commercial space missions to benefit from its use. Because this is a direct drive solution, the first such for propulsion flow control on spacecraft, these can apply fast valve open/close rates (estimated gt;1.2KHz) and deliver true linear proportional flow control.nbsp; The large reduction in power cost and mass, combined with ability for radhard implementation would make these new components and ideal selection for on-board prop. systems and other equipment for small spacecraft are now envisaged for Moon-Mars (Artemis) and other deep space missions that will have immediate applications to the booming market in LEO/GEO small satellites.

Technology keywords

Not reported

Other awards by this recipient

Verified by the same UEI. These are other public SBIR/STTR award pages, not a merged company record.

Research funding history

136 SBIR/STTR records share this UEI (1996–2025). Reported award amounts total $62,777,779. Reported amounts are not federal obligations.

Phases: Phase I, Phase II, Phase II – Direct to Phase II

Agencies: Department of Defense, National Aeronautics and Space Administration

Agency intelligence

National Aeronautics and Space Administration

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