The Logistical Challenges of the SpaceLiner Concept

The SpaceLiner concept developed at DLR combines extremely fast transport (90 minutes from Europe to Australia) with the experience of Space flight. As such it is different from the spaceflight which focuses exclusively on space tourism but it combines space tourism with for example business travel. The SpaceLiner is designed to carry 50 passengers in suborbital flight. The conceptual technical design presents some challenges which have already been partially investigated at DLR [1]. However, the overall commercial concept presents a number of different challenges. This paper will identify and describe the logistical challenges involved

Technical Assessments of Future European Space Transportation Options

The paper describes some of the most recent activities in Germany in the technical assessment of future European launcher architecture. In focus is a joint effort of DLR-SART with German launcher industry in the definition of a next generation upper-medium class expendable TSTO with an initial operational capability after 2020. Involved companies are EADS astrium and MT Aerospace. This DLR-agency funded study WOTAN investigates fully cryogenic launchers as well as those with a combination of solid and cryogenic stages, fulfilling a requirement of 5000 kg single payload into GTO. Solid strap-on boosters should allow both versions further payload growth capability. In its second part the paper analyzes options for new liquid fuel upper stages to be put on the P80 solid first stage of the Vega small launcher. Versions with storable as well as cryogenic propellants are investigated in a preliminary launcher system lay-out and their technical viability is critically assessed

Report on trajectory analysis and optimization of the nominal flight trajectory and sensitivities

This deliverable presents work done on the optimization of the nominal flight of the SpaceLiner (a flight from Sydney to Western Europe). Optimality is measured with respect to the total take-off mass of the SpaceLiner. The main parameter is therefore propellant mass. A trajectory resulting in lowest propellant requirement (low delta V) is considered the most optimal

Modeling of cryogenic sloshing including heat and mass transfer

The paper discusses heat and mass transfer during sloshing of cryogenic liquids. Experiments have been executed to investigate this. The experimental results are analyzed and CFD tools are used to create a better understanding of the physical processes involved. A 1D engineering model has been set up with the goal to simulate the heat and transfer during sloshing with only very short CPU time (not more than a few minutes)

Latest Progress in Research on the SpaceLiner High-Speed Passenger Transportation Concept

A vision aimed at revolutionizing ultra-long distance travel between different points on earth could be realized by a high-speed intercontinental passenger transport using rocket based, suborbital launchers. The paper gives an overview on the latest progress in conceptual design of the DLR SpaceLiner presenting geometrical size and mass data and describing results of trajectory simulations. The rockets are based on an advanced but technically conservative approach not relying on exotic technologies. The two-stage, fully reusable vehicle is designed as an “exceedingly reliable” system to overcome the safety deficits of current state-of-the-art launchers. The paper further outlines the latest technical lay-out and flight performance. The question on how to flexibly adjust diverse passenger volume and range distances for different interesting destinations is discussed. The paper also briefly describes innovative active cooling technologies investigated in DLR's arc-heated facility including most recent efficiency data and presents first assessments on system performance

SpaceLiner Rocket-Powered High-Speed Passenger Transportation Concept Evolving in FAST20XX

The revolutionary ultrafast passenger transport SpaceLiner is under investigation at DLR since more than 5 years. The two-stage, fully reusable vehicle is powered by rocket engines. The EU-funded study FAST20XX (Future high-Altitude high-Speed Transport 20XX) recently set off further deepening the research in this advanced transportation concept. The paper describes the latest progress of the SpaceLiner configuration achieved in the last two years: • Vehicle trade-off studies including the choice of propellant (RP vs. LH2) and • staging characteristics (e.g. the challenges of single stage concepts for shorter distances) • Pre-development of a passenger rescue capsule • Aerodynamic shape refinement • Resizing and optimization of the passenger stage including establishing a preliminary structural concep

A fast engineering tool for simulation and design of propellant management systems in liquid propelled launcher stages

At the Space Launcher System Analysis (SART) department of DLR, an engineering tool for the simulation of propellant management systems is under development. The tool is called PMP (Propellant Management Program). This paper will describe the tool and some of the models the tool uses. Some models have been adapted or added and some will be implemented in the future. The paper will also describe the results of a test case compared to the EADS Astrium tool EUCES

System Investigations of the SpaceLiner Concept in FAST20XX

DLR’s launcher systems analysis division has proposed a visionary, extremely fast passenger transportation concept reaching the edges of space based on rocket propulsion. The paper describes the recent technical progress achieved in the SpaceLiner configuration. The revolutionary ultrafast transport is now under investigation in the EU-funded study FAST20XX (Future high-Altitude high-Speed Transport 20XX) set off in December 2009. The focus of the paper is on all system aspects of the preliminary design including its flight performance impact on design choices. A major new result is the replacement of the original skipping trajectory by a smooth glide obtained in system optimizations

Study Trade-Offs on Future European Expendable Launchers

The paper describes latest results of recent activities in Germany in the technical assessment of future European launcher architecture. In a joint effort of DLR-SART with German launcher indus-try a next generation upper-medium class expendable TSTO and options for new liquid fuel upper stages for the small VEGA-launcher are addressed. The WOTAN study has investigated fully cryogenic launchers as well as those with a combination of solid and cryogenic stages, fulfilling a requirement of at least 5000 kg single payload into GTO. With this study finished, final performance data as well as critical technical and programmatic issues are presented. The VENUS research on potential new VEGA upper stages is focused on storable and on Vinci-based cryogenic propulsion and includes not only the VEGA solid propellant lower composite, but also its potential more powerful future upgrade. The challenges in achieving a considerable per-formance gain compared to VEGA are revealed