Nicole Garbers

Technical Maturation of the SpaceLiner Concept

DLR’s launcher systems analysis division is investigating since a couple of years a visionary, extremely fast passenger transportation concept reaching the edges of space based on rocket propulsion. Work is now focusing on the iterative sizing of all major subcomponents in nominal and off-nominal flight conditions. The paper describes the recent technical progress achieved in the SpaceLiner 7 configuration supported by the EU-funded studies FAST20XX (Future high-Altitude high-Speed Transport 20XX) and CHATT (Cryogenic Hypersonic Advanced Tank Technologies). The focus of the paper is on all system aspects of the reference vehicle’s preliminary design including its nominal trajectory and first assessment of its environmental impact.

Parametric Structural Analysis for the SpaceLiner

The Space Launcher Systems Analysis Group (SART) of the German Aerospace Center DLR has been working for several years on developing a novel hypersonic passenger transportation concept. The SpaceLiner, originally proposed in 2005, is a two staged, rocket propelled and vertical take-off transportation system designed for a 90 minutes Europe- Australia reference mission carrying 50 passengers. In addition to the DLR internal activities, the SpaceLiner is also under investigation in the current European Commission’s (EC) research projects FAST20XX and CHATT. A major challenge for the SpaceLiner is the design of a lightweight structure for this unique vehicle concept and the integration of structure and thermal protection system (TPS). For this task, a finite element based structural analysis tool will be used, providing rapid parametric studies for complex vehicle configurations with a high level of flexibility. This paper summarizes the current and past activities on the preliminary structural analysis for the SpaceLiner. The parametric analysis tool will be described in detail. Different structural concepts will be investigated and the results presented. Also discussed is the integration of TPS and- structure, as well as structural-dynamic considerations. In addition to the SpaceLiner related activities also a brief summary of the parametric structural analysis within the EC co-funded ATLLAS-II research project will be given.

Investigation of Structure, Thermal Protection System, and Passenger Stage Integration for the Hypersonic Transport System SpaceLiner

Suborbital high speed transport is a technology that could significantly impact space transportation, since mass production of rocket propelled aircraft and their engines, as well as operating them on a routinely basis, promises reductions in the manufacturing and launching costs for space launchers. With this vision in mind, the SpaceLiner concept was developed in the Space Launcher Systems Analysis group (SART) of DLR in 2005. Since then, the original design has evolved into several successive configurations. The latest configuration 7-2 is shown in Fig. 1. Currently, the configuration 7-3 is under definition. Various papers have been published about the SpaceLiner or its subsystems, for instance Ref. 1 and Ref. 2 as some of the latest ones. The SpaceLiner is a two staged, rocket propelled and vertical lift off passenger transport aircraft. The reference mission is to carry 50 passengers from Europe to Australia or vice versa within just 90 minutes. The SpaceLiner system is composed of a winged, passenger carrying main stage also denominated orbiter, and a winged booster. Both stages are liquid oxygen (LOX) and liquid hydrogen (LH2) propelled, and fully reusable. After booster separation, the orbiter continues the ascent with its own rocket engines until main engine cut-off (MECO) at an altitude of around 75 km. Subsequently, the range flight is being performed in gliding mode, whereas Mach numbers of up to 24 are reached.

SpaceLiner Technical Progress and Mission Definition

DLR’s launcher systems analysis division is investigating since a couple of years a visionary, extremely fast passenger transportation concept reaching the edges of space based on rocket propulsion. Thanks to multi-national collaboration, the technical lay-out of the SpaceLiner has now matured to Phase A conceptual design level. Iterative sizing of all major subcomponents in nominal and off-nominal flight conditions has been performed. The paper describes the recent technical progress achieved in the SpaceLiner 7 configuration, • mainly system aspects of the reference vehicle’s preliminary design including establishment of a preliminary structural concept, • main propulsion system definition, • pre-development of a passenger cabin and rescue capsule and its specific challenges, • preliminary sizing of the thermal protection and active cooling systems, • mission definition with its nominal trajectories including potential ground infrastructure, • programmatic development aspects