Indirect Thrust Measurement of the MP2S Pulsed Magnetoplasmadynamic Thruster

Indirect Thrust Measurement of the MP2S Pulsed Magnetoplasmadynamic Thruster | Research Square window.SnipcartSettings = { analytics: { enabled: false } }; (function() { var accessVector = localStorage.getItem('access_vector') || ''; window.dataLayer = window.dataLayer || []; if (accessVector) { window.dataLayer.push({ user: { profile: { profileInfo: { snid: accessVector } } } }); } })(); (function(w,d,s,l,i){w[l]=w[l]||[];w[l].push({'gtm.start':new Date().getTime(),event:'gtm.js'});var f=d.getElementsByTagName(s)[0],j=d.createElement(s),dl=l!='dataLayer'?'&l='+l:'';j.async=true;j.src='https://www.googletagmanager.com/gtm.js?id='+i+dl;f.parentNode.insertBefore(j,f);})(window,document,'script','dataLayer','GTM-K279D39R'); Browse Preprints In Review Journals COVID-19 Preprints AJE Video Bytes Research Tools Research Promotion AJE Professional Editing AJE Rubriq About Preprint Platform In Review Editorial Policies Our Team Advisory Board Help Center Sign In Submit a Preprint Cite Share Download PDF Research Article Indirect Thrust Measurement of the MP2S Pulsed Magnetoplasmadynamic Thruster Rune Fritzsche, Felix Schäfer, Georg Herdrich, Thomas Yung, Julien Scheiner, and 2 more This is a preprint; it has not been peer reviewed by a journal. https://doi.org/ 10.21203/rs.3.rs-9245821/v1 This work is licensed under a CC BY 4.0 License Status: Under Review Version 1 posted 6 You are reading this latest preprint version Abstract Pulsed, gas-fed electric propulsion systems are a promising option for future small satellite missions but pose significant challenges for accurate thrust characterization due to parasitic forces introduced by propellant feed lines. This paper presents and experimentally demonstrates an indirect thrust measurement methodology for a pulsed quasi steady-state magnetoplasmadynamic thruster prototype of the Modular Pulsed Propulsion System (\name). The thruster plume is directed onto a graphite target mounted on a high-precision thrust balance, decoupling the balance mechanically from the gas supply system. Since the impulse transfer between the argon plume and the target is unknown, it is quantified using LAMMPS molecular dynamics simulations to obtain an impulse transfer correction factor. The impulse bit is measured using nanometer-resolution pendulum displacement measurements processed via sinusoidal curve fitting and wavelet filtering. A comprehensive uncertainty analysis based on Gaussian error propagation is performed, accounting for calibration, sensor resolution, geometry, timing, frequency determination, damping, and impulse transfer. The methodology is used to determine impulse bit, specific impulse, and thrust efficiency of the \name, demonstrating thrust levels significantly above the cold-gas contribution alone, identifying distinct discharge modes, and outlining the design and operational changes required to approach the targeted performance. Pulsed thruster Magnetoplasmadynamics Thrust determination Full Text Additional Declarations No competing interests reported. Cite Share Download PDF Status: Under Review Version 1 posted Reviewers agreed at journal 29 Apr, 2026 Reviewers agreed at journal 23 Apr, 2026 Reviewers invited by journal 03 Apr, 2026 Editor assigned by journal 30 Mar, 2026 Submission checks completed at journal 30 Mar, 2026 First submitted to journal 27 Mar, 2026 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. 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Also discoverable on Platform About Our Team In Review Editorial Policies Advisory Board Help Center Resources Author Services Accessibility API Access RSS feed Manage Cookie Preferences © Research Square 2026 | ISSN 2693-5015 (online) Privacy Policy Terms of Service Do Not Sell My Personal Information {"props":{"pageProps":{"initialData":{"identity":"rs-9245821","acceptedTermsAndConditions":true,"allowDirectSubmit":false,"archivedVersions":[],"articleType":"Research Article","associatedPublications":[],"authors":[{"id":618330375,"identity":"ca406b47-f953-4f04-ac63-6e71e4c9a4a7","order_by":0,"name":"Rune 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This paper presents and experimentally demonstrates an indirect thrust measurement methodology for a pulsed quasi steady-state magnetoplasmadynamic thruster prototype of the Modular Pulsed Propulsion System (\\name). The thruster plume is directed onto a graphite target mounted on a high-precision thrust balance, decoupling the balance mechanically from the gas supply system. Since the impulse transfer between the argon plume and the target is unknown, it is quantified using LAMMPS molecular dynamics simulations to obtain an impulse transfer correction factor. The impulse bit is measured using nanometer-resolution pendulum displacement measurements processed via sinusoidal curve fitting and wavelet filtering. A comprehensive uncertainty analysis based on Gaussian error propagation is performed, accounting for calibration, sensor resolution, geometry, timing, frequency determination, damping, and impulse transfer. 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