Gridded Ion Thruster Mission Life Prediction through Reduced Order Modeling

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This paper presents a simplified Gridded Ion Thruster Predictive Engineer Model (GIT PEM) that captures coupled effects of facility-induced neutral and sputterant flux on thruster performance and grid erosion, demonstrating how different life mechanisms dominate based on uncertainties and assumptions.

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This preprint studies gridded ion thruster (GIT) mission life prediction in the context of vacuum facility ground tests, using a “GIT Predictive Engineer Model” that captures coupled facility effects (neutral and sputterant flux) affecting grid erosion and performance for NASA’s NSTAR thruster. The authors exercise key aleatoric and epistemic uncertainties—including life-threshold, model estimation and relevant physics, operating conditions, and mission scenarios—to quantify how sensitive predictions are to different assumptions. They find that different life mechanisms can dominate depending on imposed assumptions and uncertainties, with electron backstreaming—a common thruster life mechanism—showing high uncertainty under simplified approximations and being strongly influenced by facility-related uncertainties such as charge exchange collisions and sputter deposition. The model is presented as a simple engineering framework relying on available experimental/computational data rather than a peer-reviewed study of validated predictive accuracy. The paper does not explicitly discuss endometriosis or adenomyosis; it was included in the corpus via a keyword match in the upstream search index.

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Abstract

Abstract High power electric propulsion space missions require vacuum facility ground tests to predict in-space life and performance. Gridded ion thruster (GIT) mission life prediction must account for facility effects such as facility induced neutral and sputterant flux, which affect thruster performance and grid erosion, which can obfuscate predictions of grid transparency and electron backstreaming. This work demonstrates a simple GIT Predictive Engineer Model (GIT PEM) that captures these coupled effects. The model uses experimental and computational data from NASA’s NSTAR thruster, though any GIT could be used. The GIT PEM is exercised for key aleatoric and epistemic uncertainties, including those related to life threshold, model estimations, relevant physics, thruster operating conditions, and mission scenarios to characterize model sensitivities and uncertainty quantification. Results show that different life mechanisms dominate depending on imposed assumptions, examined factors, and uncertainties. For example, the most common life mechanism for ion thrusters, electron backstreaming, can exhibit high uncertainty for simplified approximations and is strongly influenced by facility-related uncertainties such as charge exchange collisions and sputter deposition.
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Obenchain, Richard E. Wirz This is a preprint; it has not been peer reviewed by a journal. https://doi.org/ 10.21203/rs.3.rs-7802308/v1 This work is licensed under a CC BY 4.0 License Status: Posted Version 1 posted You are reading this latest preprint version Abstract High power electric propulsion space missions require vacuum facility ground tests to predict in-space life and performance. Gridded ion thruster (GIT) mission life prediction must account for facility effects such as facility induced neutral and sputterant flux, which affect thruster performance and grid erosion, which can obfuscate predictions of grid transparency and electron backstreaming. This work demonstrates a simple GIT Predictive Engineer Model (GIT PEM) that captures these coupled effects. The model uses experimental and computational data from NASA’s NSTAR thruster, though any GIT could be used. The GIT PEM is exercised for key aleatoric and epistemic uncertainties, including those related to life threshold, model estimations, relevant physics, thruster operating conditions, and mission scenarios to characterize model sensitivities and uncertainty quantification. Results show that different life mechanisms dominate depending on imposed assumptions, examined factors, and uncertainties. For example, the most common life mechanism for ion thrusters, electron backstreaming, can exhibit high uncertainty for simplified approximations and is strongly influenced by facility-related uncertainties such as charge exchange collisions and sputter deposition. predictive model electric propulsion ion thruster uncertainty Full Text Additional Declarations No competing interests reported. Cite Share Download PDF Status: Posted Version 1 posted You are reading this latest preprint version Research Square lets you share your work early, gain feedback from the community, and start making changes to your manuscript prior to peer review in a journal. As a division of Research Square Company, we’re committed to making research communication faster, fairer, and more useful. We do this by developing innovative software and high quality services for the global research community. Our growing team is made up of researchers and industry professionals working together to solve the most critical problems facing scientific publishing. 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