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  • A Game-changing, European Small Launch Vehicle for Sustainable Access to Space

    Paper number

    IAC-19,D2,7,8,x55171

    Author

    Dr. Mario Kobald, Germany, HyImpulse Technologies GmbH

    Coauthor

    Dr. Christian Schmierer, Germany, HyImpulse Technologies GmbH

    Coauthor

    Mr. Ulrich Fischer, Germany, German Aerospace Center (DLR)

    Coauthor

    Mr. Konstantin Tomilin, Germany, German Aerospace Center (DLR)

    Coauthor

    Prof. Stefan Schlechtriem, Germany, Deutsches Zentrum für Luft- und Raumfahrt e.V. (DLR)

    Coauthor

    Prof. Vaios Lappas, Greece, University of Patras

    Year

    2019

    Abstract
    A steadily growing demand for smallsat launch capabilities drives on the search for low-cost launch vehicles.
    Hybrid rocket technology has been pushed forward in the recent years and is now ready to meet the demand of this
    low-cost rocket development. Thanks to inherent safety and reliability the development and production cost of
    hybrid rocket engines can be a small fraction of bi-liquid propulsion systems. The New Space start-up HyImpulse
    Technologies GmbH was founded in 2018 from 5 employees from the German Aerospace Center (DLR) which are
    experienced with flight-proven hybrid sounding rockets and excellent hands-on experience. HyImpulse has
    successfully completed its first funding round in 2018 and partnered with a German Aerospace company. A concept
    for a mini-launcher has been started by HyImpulse and the development of the 75 kN (SL) main hybrid rocket engine
    is on-going with a first test campaign in 2019. The propellants are Liquid Oxygen/Paraffin and deliver the same
    performance as a Liquid Oxygen/Kerosene liquid rocket engine while having a much simpler design and lower cost.
    Testing and development is done in collaboration with the DLR Institute of Space Propulsion in Lampoldshausen.
    This engine will be the largest hybrid rocket engine ever tested in Europe. The concept of the HyImpulse minilauncher
    includes eleven engines of this type, which will result in large scale serial production for the foreseen
    launch rate of twelve launches per year. This further reduces production costs of the hybrid rocket engine. The
    advantage of paraffin-based fuel lies in the simple geometry of the grain caused by the high regression rate. This
    paper describes first details of the mini-launcher design and test results of the hybrid rocket engine demonstrator at
    TRL 5.
    Abstract document

    IAC-19,D2,7,8,x55171.brief.pdf

    Manuscript document

    IAC-19,D2,7,8,x55171.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.