Nikita Tumanov

Mr. Nikita Tumanov

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Research Focus & Metrics

Academic Career Length

1Year (2026-Present)

(Calculated once Scilit publication data is synced: current year − year of first publication + 1)

Representative Publications

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19 January 2026 in Preprints.org
Verified
Preprint
Open access
PDF file
ASAndrei Shumeiko
Andrei Shumeiko
APAleksei Pavlov
Aleksei Pavlov
DFDaria Fedorova
Daria Fedorova
NTNikita Tumanov
Nikita Tumanov
Propulsion systems aboard small satellites assisting dynamic space missions at the proximity of deep space natural objects may face challenges in long-term non-serviceable operations, achieving thrust vector direction control, and adapting to severe environmental conditions. The proposed solution involves using pulsed plasma thrusters with multiple spark plugs for uniform ignition and thrust vector control, enhancing reliability and efficiency of propulsion system. Key advantages of the use of such an approach include minimal power consumption, efficient volume utilization, and enhanced reliability through redundant ignition points. Experimental validation confirms the effectiveness of the proposed architecture, demonstrating uniform ignition patterns and capability of thrust vector adjustment. It can be supposed that this approach supports the viability of small satellites in future deep space missions, promising dynamic, resilient, and reusable proliferated space systems.

28 February 2026 in Aerospace
Verified
Journal Article
Open access
PDF file
ASAndrei Shumeiko
Andrei Shumeiko
APAleksei Pavlov
Aleksei Pavlov
DFDaria Fedorova
Daria Fedorova
NTNikita Tumanov
Nikita Tumanov
Propulsion systems aboard small satellites assisting dynamic space missions at the proximity of deep space natural objects may face challenges in long-term non-serviceable operations, achieving thrust vector direction control, and adapting to severe environmental conditions. The proposed propulsion solution involves using a pulsed plasma thruster with multiple spark plugs for uniform ignition and thrust vector control, enhancing reliability and efficiency. Key advantages of the use of such an approach include minimal power consumption, an efficient volume utilization, and enhanced reliability through redundant ignition points realized within a single thruster head. Experimental validation demonstrates the effectiveness of the proposed architecture, confirming uniform ignition patterns. Also, the results of the experimental investigation qualitatively demonstrate the capability of thrust vector control by selectively discharging the distributed spark plugs. It can be supposed that this approach supports the viability of small satellites in dynamic space missions, promising dynamic, resilient, and reusable proliferated space systems for development of deep space economies.