DGLR-Publikationsdatenbank - Detailansicht
Autor(en):
B. Oker, B. Peter
Zusammenfassung:
HyEnD, a student rocketry group from the University of Stuttgart, is developing high-performance liquid rocket engine as part of the BLAST project, aiming to surpass the altitude record for student-built liquid rockets. A performance optimized, lightweight variant of this liquid rocket engine utilizing nitrous oxide and ethanol as propellants, features an ablative combustion chamber liner enclosed within a carbon-fiber-reinforced polymer (CFRP) composite pressure casing. The manufacturing process employs an in-house developed, 4-axis NC-controlled filament winding machine, enabling rapid prototyping of optimized fiber layups and winding patterns. The development cycle involved extensive ignition characterization using an ablatively cooled "battleship" engine to establish a reliable startup sequence and characterize the thermal behavior of the ablative material. The system was iteratively scaled and hot-fire tested at thrust levels ranging from 200 N to 2 kN. The technology achieved flight-proven status during the 2025 European Rocketry Challenge (EuRoC), where a 1 kN variant successfully propelled the LUMINA rocket to a category win. This work demonstrates the feasibility of utilizing automated composite manufacturing for high-pressure rocket engine architectures in student-led aerospace research.
Veranstaltung:
Deutscher Luft- und Raumfahrtkongress 2026, Aachen
Verlag, Ort:
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2026
Medientyp:
Conference Paper
Sprache:
englisch
Format:
21,0 x 29,7 cm, 10 Seiten
URN:
urn:nbn:de:101:1-2610141341282.735145327878
DOI:
10.25967/680504
Stichworte zum Inhalt:
Rocket Propulsion, Green Propellants, Carbon Fiber Reinforced Polymer
Verfügbarkeit:
Download
- Bitte beachten Sie die Nutzungsbedingungen dieses Dokuments: Copyright protected
Kommentar:
Zitierform:
Oker, B.; Peter, B. (2026): Development and Testing of a Carbon Fiber Overwrapped Ablatively Cooled Liquid Rocket Engine using Green Propellants. Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V.. (Text). https://doi.org/10.25967/680504. urn:nbn:de:101:1-2610141341282.735145327878.
Veröffentlicht am:
14.10.2026