System design of EURASTROS reference configurations and mission
Creators: name:  A. PLEBUCH 
name:   M. WOLF 
name:   P. MARQUARDT 
Publisher: name: Proceedings of  the 9th European Conference for Aerospace Sciences. Lille, France, 27 June - 1 July, 2022
Year: 2022
Subjects: HUMAN
SPACEFLIGHT

description: Abstract Submission EUCASS 2022 System design of EURASTROS reference configurations and mission Alex Plebuch , Marco Wolf ArianeGroup GmbH, Germany Pascal Marquardt , German Aerospace Center (DLR e.V.), Germany Abstract Is Europe technologically ready for an independent astronautical access to space? The EURASTROS study has been carried out following the high level objectives to investigate cost-efficient, robust and relatively short-term accessible astronautical space transportation services based on European assets and technologies [1]. To meet the high level objectives and to maximize the benefit from European heritage on previous spacecrafts and demonstrations, a service module capsule spacecraft concept was baselined. Among others, such a concept directly builds on the knowledge acquired during the activities on the Automated Transfer Vehicle (ATV), the European Service Module (ESM), the Advanced Reentry Demonstrator (ARD) and several studies as the Advanced Reentry Vehicle (ARV) or the BERT study (Bemannter Europaischer Raumtransport). To comply with the high level objectives a set of high level requirements (HLR) was elaborated within the consortium composed of several leading DLR institutes and Ariane group GmbH. The principal HLR driving the system configuration were (1) the accommodation of up to three Astronauts including one seat being interchangeable with cargo, (2) the short development timeframe of 5 years up to non-crewed maiden flight keeping development costs in the frame of comparable services, (3) the reference mission to LEO using the Ariane 6 launch vehicle from Guyana Spaceport, (4) providing end-to-end abort capability for crew safety, (5) in usage of European technology. Based on the HLR an incremental system sizing workflow has been initiated, comparable to a condensed Phase 0 system study. First, A6 performance data was elaborated to provide inputs for nominal and degraded mission scenarios respective crew safety related operations [2]. Following that, critical principal sizing of the crew module subsystems as of the TPS, propulsion system ECLSS were carried out in usage of engineering methods and numerical tools [3]. The resulting crew module mass and the determined A6 trajectory data enabled the technological trade-off analysis on and sizing of the atmospheric abort system. Here, some particularities of the European setting needed to be mastered. In the final step the service module vehicle conceptual design has been elaborated. Due to the end-to-end abort capability and the focus on application of European technology, no easy-fit solution has been identified. Instead, an adaptation of the currently under ESA contract developed ASTRIS kick-stage including its baselined BERTA storable engine was performed. The computed needs of such a service vehicle resulted to be well in line to ASTRIS system boundaries. Despite the identification of several technological gaps, which can be closed with existing European expertise and adequate funding, the performed study revealed no show stopper on the system design. References [1] Ali Gulhan, Marco Wolf, Alex Plebuch, Hendrik Weihs, Martin Sippel, Ludger Frobel; An Overview of the EURASTRUS study, EUCASS-3AF CONFERENCE, LILLE, FRANCE, 2022. [2] Ingrid Dietlein, Pascal Marquardt, Kevin Bergmann; EURASTROS ascent trajectory and abort analysis, EUCASS-3AF CONFERENCE, LILLE, FRANCE, 2022. [3] Pascal Marquardt, Markus Fertig, Thomas Reimer, Ali Gulhan; EURASTROS capsule design and re-entry analysis, EUCASS-3AF CONFERENCE, LILLE, FRANCE, 2022.