Artist's impression of the SpaceLiner 7 during ascent
|Function||Hypersonic passenger transport|
|Country of origin||European Union|
SpaceLiner is an advanced concept for a suborbital, hypersonic, winged passenger transport, which is currently under investigation at the German Aerospace Center (Deutsches Zentrum für Luft- und Raumfahrt, or DLR) since 2005.
The SpaceLiner concept consists of a two-stage, vertical takeoff, horizontal landing configuration with a large unmanned booster and a manned stage designed for 50 passengers and 2 crew members. The fully reusable system is accelerated by a total of eleven liquid rocket engines (9 for the booster stage, 2 for the passenger stage), which are to be operated using cryogenic liquid oxygen (LOX) and hydrogen (LH2). After engine cut-off, the passenger stage will enter a high-speed gliding flight phase and shall be capable of traveling long intercontinental distances within a very short time. Altitudes of 80 kilometers and Mach numbers beyond 20 are projected, depending on the mission and the associated trajectory flown. SpaceLiner flight times from Australia to Europe, the chosen reference mission, should take just 90 minutes. Shorter distances, such as Europe to California for example, would then be achievable in no more than 60 minutes. Acceleration loads for the passengers, and only during the propelled section of the flight, are designed to remain below 2.5 g, and well below those experienced by the Space Shuttle astronauts.
The concept design also foresees the specially designed passenger cabin to function as an autonomous rescue capsule which can be separated from the vehicle in case of an emergency, thus allowing the passengers to return safely to Earth.
A key aspect of the SpaceLiner concept is its full reusability and vehicle mass-production, which will closely resemble production rates of the aviation industry. Serial production is expected to deliver a significant increase in cost effectiveness compared to conventional space transportation systems of the early 2000s. A major challenge lies in improving the safety standards and especially the robustness and reliability of space components such as rocket engines, so that they will become suitable for the daily operation of a passenger transporter like the SpaceLiner, while also meeting the required reusability criteria.
The development of the concept is funded by DLR's internal resources, as well as in the context of EU-FP7 funded projects such as FAST 20XX and CHATT. In addition to DLR, various partners from the European aerospace sector are involved.
As of the end of 2011, early investigations and ongoing research conducted within context of the FAST 20XX framework led to the refinement and definition of the latest SpaceLiner 7 version. Based on the results of previous studies, development has been progressing continuously with increasingly detailed and in-depth considerations, modeling and simulations of the various subsystems, and their design and integration being performed. Selected variants to the baseline configuration given different requirements and specifications were studied with associated results influencing and redirecting the entire design process.
SpaceLiner 1 was the very first version conceived in 2005.
SpaceLiner 2 refers to the first version, which featured the integration of an innovative active cooling system for the areas of particularly high thermal stresses during atmospheric, re-entry, being the nose and wing leading edge sections.
The SpaceLiner 4 is an evolution of the version 2 with improved aerodynamic and flight dynamic characteristics. Based on this configuration, various technologies necessary for the SpaceLiner were experimentally and numerically examined, research that was funded by the EU research project FAST20XX.
The latest configuration under investigation at the DLR is the SpaceLiner 7. Based on results obtained from application of numerical optimization methods which achieved an improvement of the aerodynamic, thermal and structural-mechanical properties in hypersonic flight, the initial double delta wing of previous versions has been modified and replaced by a single delta wing. Presently, subsystems such as the passenger cabin, the cryogenic tanks, the propellant feed system and the vehicle thermal protection have been preliminarily designed and integrated, and this process documented and detailed in various papers and publications. Studies have also been carried out on the economic and logistical aspects of the concept, with preliminary calculations of expected program development and production costs given necessary assumptions.
Possible routes, which have then formed the basis of trajectory analyses for SpaceLiner, have been identified. These are classified and grouped in terms of their distances, with Class 1 representing the longest route, and Class 3 describing the shortest yet still economically interesting and relevant distance. In line with this, a modified version of the SpaceLiner 7 capable of flying medium long-haul distances while carrying 100 passengers has been examined. Given the name SL7-100, this concept variant is suitable for Class 2 and Class 3 distance flights. To accommodate for the different SpaceLiner configurations, a long and short version of the booster stage have therefore been considered to accordingly fulfill the mission requirements depending on the required range, either in combination with the 50 or 100-passenger stage version. In addition, research into possible spaceport variants has been performed, determining mainland, offshore platform and artificial island possibilities, as well as the required infrastructure for a potential SpaceLiner spaceport.
The specifications of the SpaceLiner 7 are:
(50 passenger version)
|Overall length:||65.6 m||82.3 m|
|Wing span:||33.0 m||36.0 m|
|Overall height:||12.1 m||8.7 m||21.5 m|
|Cabin length:||15.3 m||-|
|Max. fuselage diameter:||6.4 m||8.6 m|
|Empty mass:||140 t||201 t||341 t|
|Total mass:||370 t||1485 t||1855 t|
|Propellant mass:||230 t||1284 t||1514 t|
|Main Engines Cut-Off mass:||160 t||180 t|
|Max. altitude:||approx. 80 km||approx. 75 km|
|Max. speed:||7 km/s (25,200 km/h)||3.7 km/s (13,300 km/h)|
|Max. Mach number:||24||14|
|Max. range:||up to about. 18,000 km|
|Number of engines:||2||9||11|
The SpaceLiner concept intends to use a single type of reusable liquid rocket engine, which operates in the full-flow staged combustion cycle mode. Having a common engine design for both SpaceLiner stages is in line with system commonality and should support cost optimization in both the development and production phases. The nozzle expansion ratio is adapted to the different missions of the booster and passenger stages. Furthermore, liquid hydrogen and liquid oxygen will be used as the propellants, a combination which is both very powerful while still remaining eco-friendly.
|Combustion chamber pressure:||16.0 MPa|
|Mass flow rate (per engine):||515 kg/s|
|Specific impulse (vacuum):||449 s||437 s|
|Specific impulse (sea level):||363 s||389 s|
|Thrust per engine (vacuum):||2268 kN||2206 kN|
|Thrust per engine (sea level):||1830 kN||1961 kN|
|Wikimedia Commons has media related to SpaceLiner.|
- "The SpaceLiner", Institut für Raumfahrtsysteme, Systemanalyse Raumtransport (SART), DLR.
- "New Road Map For DLR’s Suborbital SpaceLiner", Aviation Week, 18 August 2015.
- To Australia in 90 minutes at hypersonic speed (blog) (video), DE: DLR.
- "SpaceLiner - Animation (2012)", You tube (video), Google.
- "The SpaceLiner", You tube (video), Google.
- "FAST20XX", Space engineering, ESA.
- Sippel, M; Klevanski, J; Steelant, J (October 2005), "Comparative study on options for high-speed intercontinental passenger transports: air-breathing- vs. rocket-propelled", IAC-05-D2.4.09
- Sippel, M; Schwanekamp, T; Trivailo, O; Kopp, A; Bauer, C; Garbers, N (July 2015), "SpaceLiner Technical Progress and Mission Definition", AIAA 2015-3582, 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, Glasgow.
- Sippel, M (Jun–Jul 2010). "Promising roadmap alternatives for the SpaceLiner". Acta Astronautica. pp. 1652–58. doi:10.1016/j.actaastro.2010.01.020. Retrieved 26 August 2015.
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- Schwanekamp, T; Bauer, C; Kopp, A. "Development of the SpaceLiner Concept and its Latest Progress" (PDF; 1672 kB). 4th CSA-IAA Conference on Advanced Space Technology, September 2011. DE: DLR. Retrieved 2013-05-10.
- van Foreest, A; et al., "Transpiration Cooling Using Liquid Water" (PDF), Journal of Thermodynamics and Heat Transfer (DLR) 23 (4), retrieved 26 August 2015
- van Foreest, A (2009). "The Progress on the SpaceLiner Design in the Frame of the FAST 20XX Program". 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. AIAA. Retrieved 26 August 2015.
- Garbers, N (2013). "Overall Preliminary Design of the Thermal Protection System for a Long Range Hypersonic Rocket-Powered Passenger Vehicle (SpaceLiner)" (PDF; 138 kB). 7th European Workshop on Thermal Protection Systems and Hot Structures. Retrieved 2014-04-24.
- T. Schwanekamp, C. Ludwig, M. Sippel. "Cryogenic Propellant Tank and Feedline Design Studies in the Framework of the CHATT Project" (PDF; 2370 kB). 19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, June. 2014. Retrieved 2015-10-14.
- T. Schwanekamp, F. Mayer, T. Reimer, I. Petkov, A, Tröltzsch, M. Siggel. "System Studies on Active Thermal Protection of a Hypersonic Suborbital Passenger Transport Vehicle" (PDF; 2370 kB). AIAA Aviation Conference, AIAA 2014-2372, Atlanta, June. 2014. Retrieved 2015-10-14.
- Trivailo, O (March 2015), "Innovative Cost Engineering Approaches, Analyses and Methods Applied to SpaceLiner - an Advanced, Hypersonic, Suborbital Spaceplane Case-Study", Ph.D. Thesis
- T. Schwanekamp, J. Bütünley, M. Sippel. "Preliminary Multidisciplinary Design Studies on an Upgraded 100 Passenger SpaceLiner Derivative" (PDF; 2370 kB). 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference. 2012. Retrieved 2013-05-10.
- Sippel, M; et al. (2012). "Technical Maturation of the SpaceLiner Concept". 18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference. AIAA. Retrieved 2013-04-22.
- Sippel, M; Schwanekamp, T; et al. (2014). "Staged Combustion Cycle Rocket Engine Subsystem Definition for Future Advanced Passenger Transport" (PDF). Space Propulsion 2014, Session 30 - ST - Future Liquid Stages & Engines. Retrieved 2015-10-14.