Moritz Ertl, Tobias Ecker

DOI Number XXX-YYY-ZZZ

Conference Number HiSST­2022­-0452

Different actors in the space trasport sector are moving towards reusable launch vehicles (RLV) for the first stages of launchers, among them Rocket Lab with the Neutron and SpaceX with the Falcon 9. The current European long term strategy is also aiming towards reusability with plans for THEMIS and Ariane Next. In accordance with this strategy the German Aerospace Center (DLR) has entered into a collaboration with the Japan Aerospace Exploration Agency (JAXA) and the French Space Agency (CNES) for the development of RLV relevant technologies in the frame of a vertical take­off and vertical landing (VTVL) reusable subscale launcher first stage demonstrator ­ the “Cooperative Action Leading to Launcher Innovation in Stage Toss back Operations” (CALLISTO) [1]. Generally a VTVL first stage will return to the launch pad utilising retro­propulsion and deployable landing legs. Callisto uses thrust vector control of a single engine as a method, among others, for guidance and control during reverse flight. The reverse flight leads to new additional aerodynamic and aerothermal design questions compared to traditional launchers as the engine plume is interacting with the vehicle structure due to the air flow. The authors have already analyse some of these aspects in previous articles [2–4]. To aid the development of reusable launch vehicles in the VTVL configuration, in this work we aim to analyse the influence of a gimbaled nozzle on the aerodynamics and aerothermodynamics of a VTVL first stage during reverse flight. The analysis is based on Reynolds averaged Navier­Stokes computational fluid dynamics using the DLR TAU code.

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In Categories: High-Speed Aerodynamics and Aerothermodynamics, HiSST 2022
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