Designing and testing of HDPE–N2O hybrid rocket engine

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dc.contributor.authorArora, Triyan Pal
dc.contributor.authorButtrey, Noah
dc.contributor.authorKirman, Peter
dc.contributor.authorKhadtare, Sanmukh
dc.contributor.authorKamath, Eeshaan
dc.contributor.authordel Gatto, Dario
dc.contributor.authorIsoldi, Adriano
dc.date.accessioned2025-04-16T11:02:59Z
dc.date.available2025-04-16T11:02:59Z
dc.date.freetoread2025-04-16
dc.date.issued2025-03-13
dc.date.pubOnline2025-03-13
dc.description.abstractHybrid Rocket Engines (HREs) combine the advantages of solid and liquid propellants, offering thrust control, simplicity, safety, and cost efficiency. Part of the research on this rocket architecture focuses on optimising combustion chamber design to enhance performance, a process traditionally reliant on time-consuming experimental adjustments to chamber lengths. In this study, two configurations of HREs were designed and tested. The tests aimed to study the impact of post-chamber lengths on rocket engine performance by experimental firings on a laid-back test engine. This study focused on designing, manufacturing, and testing a laid-back hybrid engine with two chamber configurations. The engine features a small combustion chamber, an L-shaped mount, a spark ignition, and nitrogen purging. Data acquisition includes thermocouples, pressure transducers, and a load cell for thrust measurement. Our experimental findings provide insights into thrust, temperature gradients, pressure, and plume characteristics. A non-linear regression model derived from the experimental data established an empirical relationship between performance and chamber lengths, offering a foundation for further combustion flow studies. The post-chamber length positively impacted the engine thrust performance by 2.7%. Conversely, the pre-chamber length negatively impacted the performance by 1.3%. Further data collection could assist in refining the empirical relation and identifying key threshold values.
dc.description.conferencename14th EASN International Conference
dc.description.journalNameEngineering Proceedings
dc.description.sponsorshipThe authors would like to thank the School of Aerospace, Transport and Manufacturing, Cranfield University and the Centre for Autonomous and Cyberphysical Systems for their financial backing and technical guidance.
dc.identifier.citationArora TP, Buttrey N, Kirman P, Khadtare S, et al., (2025) Designing and testing of HDPE–N2O hybrid rocket engine. Engineering Proceedings, Volume 90, March 2025, Article number 34. Proceedings of the 14th EASN International Conference on “Innovation in Aviation & Space Towards Sustainability Today & Tomorrow”. 8-11 October 2024, Thessaloniki, Greece
dc.identifier.elementsID567422
dc.identifier.issn2673-4591
dc.identifier.paperNo34
dc.identifier.urihttps://doi.org/10.3390/engproc2025090034
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23768
dc.identifier.volumeNo90
dc.language.isoen
dc.publisherMDPI
dc.publisher.urihttps://www.mdpi.com/2673-4591/90/1/34
dc.relation.isreferencedbyhttps://github.com/Triyanpal/HYROE
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjecthybrid rocket
dc.subjectstatic firing
dc.subjectperformance
dc.subjectchamber length
dc.subjecttest
dc.subjectengine
dc.subjectcorrelation
dc.titleDesigning and testing of HDPE–N2O hybrid rocket engine
dc.typeConference paper
dcterms.coverageThessaloniki, Greece
dcterms.dateAccepted2024-10-01
dcterms.temporal.endDate11-Oct-2024
dcterms.temporal.startDate08-Oct-2024

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