Technical Maturation of the SpaceLiner Concept (original) (raw)
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Preliminary Multidisciplinary Design Studies on an Upgraded 100 Passenger SpaceLiner Derivative
18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, 2012
The visionary ultrafast passenger transportation concept SpaceLiner has been proposed by the Space Launcher System Analysis Department of the German Aerospace Center DLR. Based on rocket propulsion the baseline configuration of the two stage RLV should be capable of carrying about 50 passengers along the ambitious westbound route from Australia to Europe within 90 minutes. Based on the most recent and mature SpaceLiner configuration and its mission data, an upgraded 100 passenger derivative is explored since an increase of efficiency is expected and potential promising alternative travel routes and the correspondent system requirements are investigated. Preliminary estimation engineering tools are utilized within the initial, iterative design process, in order to identify potential configurations. The configuration approach most consistent with the predefined system and mission requirements is presented.
Investigation of Structure for the Hypersonic Transport System SpaceLiner
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2011
The Space Launcher Systems Analysis group (SART) of the German Aerospace Center (DLR) has been working for several years on the SpaceLiner, a novel concept for hypersonic intercontinental travel. The SpaceLiner is currently also under investigation in the EUfunded FAST20XX study, with contributions from several partners. The present paper focuses on the structural preliminary design and summarizes the works performed so far on structural and TPS layout. A large number of load cases have been defined and will be described. Special attention will be paid to the detailed wing design and corresponding static-and dynamic-structural analysis. Also, integration of wing and fuselage and the resulting structural-dynamic vehicle characteristics will be illuminated. A discussion concerning the preliminary TPS concept will follow. Finally, a brief outlook on some future activities will be presented. Nomenclature C.O.G = Center of Gravity E = Young's modulus G = Shear modulus H = altitude Ma = Mach number n x = axial acceleration n z = normal acceleration q = dynamic pressure T b = back-structure temperature TPS = Thermal Protection System v = velocity = angle of attack = Poisson's ratio = density all = allowable stress
Cryogenic Propellant Tank and Feedline Design Studies in the Framework of the CHATT Project
19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2014
The EU-funded project CHATT (Cryogenic Hypersonic Advanced Tank Technologies) has been initiated early 2012 and is part of the European Commission's Seventh Framework Programme (FP7). CHATT focuses on the development of novel cryogenic tank and propellant supply technologies. One of the tasks within the project is the investigation of adequate propellant crossfeed systems. Propellant crossfeed principally allows large mass savings for parallel burn vehicles such as the visionary passenger transport concept "SpaceLiner" which has been proposed by the Space Launcher Systems Analysis Department of the German Aerospace Center DLR. Therefore the tank and feedline systems of the SpaceLiner concept are studied by means of reference data and the results of simulations conducted with in-house and commercial tools.
Parametric Structural Analysis for the SpaceLiner
18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference, 2012
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.
9th International Space Planes and Hypersonic Systems and Technologies Conference, 1999
This paper presents a new conceptual launch vehicle design in the Bantam-X payload class. The new design is called Stargazer. Stargazer is a two-stage-toorbit (TSTO) vehicle with a reusable flyback booster and an expendable LOX/RP upper stage. Its payload is 300 lbs. to low earth orbit. The Hankey wedge-shaped booster is powered by four LOX/LH2 ejector scramjet rocket-based combined-cycle engines. Advanced technologies are also used in the booster structures, thermal protection system, and other subsystems. Details of the concept design are given including external and internal configuration, mass properties, engine performance, trajectory analysis, aeroheating results, and a concept cost assessment. The final design was determined to have a gross mass of 115,450 lb. with a booster length of 99 ft. Recurring price per flight was estimated to be $3.49M. The overall conceptual design process and the individual tools and processes used for each discipline are outlined. A summary of trade study results is also given. NOMENCLATURE C t thrust coefficient I sp specific impulse (sec.) q dynamic pressure (psf) T/W e engine thrust-to-weight ratio This paper summarizes part of an 18 month Bantam-X concept study conducted by the Space Systems Design Laboratory at Georgia Tech with the support and collaboration of NASA Marshall Space Flight Center. The study goal was to investigate a promising concept based on rocket-based combinedcycle (RBCC) propulsion for longer range Bantam-class missions. NASA MSFC currently has an ongoing development program in RBCC engines.
Heavy Satellite Launch Vehicles: An Assessment
This brief has carried out an assessment of the launch vehicles used globally for launching of heavy satellites into the geostationary orbit. This assessment is mainly based on the comparison of the various features of different launch systems and the characteristics of the propellants put in use.
Preliminary Sizing of an Hypersonic Airbreathing Airliner
Transactions of the Japanese Society For Artificial Intelligence Aerospace Technology Japan, 2010
The purpose of this paper is to identify, for given technology levels (TRL) and mission requirements, those parameters that are critical for preliminary sizing of a hypersonic airbreathing airliner. Mission requirements will dictate a solution space of possible vehicle architecture capable of meeting cruise conditions as well as of taking-off (TO) and landing. In practice, once defined a range of cruise vehicle architectures, constraints are imposed (as to all passenger airliners), such as: 1. take off (=TO) and landing distance (so-called field length, FL): FL no longer than for the B-747-400, or 10000 ft; 2. completing TO with one engine off; 3. max acceleration at TO and climb-out (CO) = 0.4 g; 4. Hydrogen fuel (Meeting NOx emission limits (EINOx) is a further constraint not discussed in this paper). These constraints enable focusing on a realistic design out of the broad range of vehicles capable of performing the given mission. Thus a realistic vehicle must not only integrate aerodynamics and propulsion system; in fact, it is the result of many iterations in the design space, until performance and constraints are successfully achieved and met. The Gross Weight at Take Off (TOGW) was deliberately discarded as a constraint, based on Previous studies by Czysz. Typically, limiting from the beginning the TOGW leads to a vicious spiral where weight and propulsion system requirements keep growing, eventually denying convergence. In designing passenger airliners, in fact, it is the payload that is assumed fixed from the start, not the total weight. A parametric analysis of the hypersonic vehicle architecture is presented: in particular, optimal size, weight and geometrical shape are defined for different mission requirements. This analysis has shown that, it is possible to define a range of possible successful solutions for the European LAPCAT II project.
Progress in Propulsion Physics, 2011
The current European project LAPCAT II has the ambitious goal to de¦ne a conceptual vehicle capable of achieving the antipodal range Brussels Sydney (∼ 18,000 km) in about 2 h at Mach number Ma = 8. At this high speed, the requirement of high lift to drag (L/D) ratio is critical to high performance, because of high skin friction and wave drag: in fact, as the Mach number increases, the L/D ratio decreases. The design of the vehicle architecture (shape and propulsion system) is, as a consequence, crucial to achieve a reasonably high L/D. In this work, critical parameters for the preliminary sizing of a hypersonic airbreathing airliner have been identi¦ed. In particular, for a given Technology Readiness Level (TRL) and mission requirements, a solution space of possible vehicle architectures at cruise have been obtained. In this work, the Gross Weight at Take-O¨(TOGW) was deliberately discarded as a constraint, based on previous studies by Czysz and Vanderkerkhove [1]. Typically, limiting from the beginning, the TOGW leads to a vicious spiral where weight and propulsion system requirements keep growing, eventually denying convergence. In designing passenger airliners, in fact, it is the payload that is assumed ¦xed from the start, not the total weight. In order to screen the solutions found, requirements for taking-o¨(TO) and landing as well as the trajectory have been accounted for. A consistent solution has ¦nally been obtained by imposing typical airliner constraints: emergency take-o¨and landing. These constraints enable singling out a realistic design from the broad family of vehicles capable of performing the given mission. This vehicle has been obtained by integrating not only aerodynamics, trajectory, and airliner constraints, but also by integrating the propulsion system, the trimming devices and by doing some adjustments to the conceptual vehicle shape (i. e., spatular nose). Thus, the ¦nal vehicle is the result of many iterations in the design space, until performance, trajectory, propulsion systems, and airport constraints are successfully met. 1 INTRODUCTION Studies on hypersonic con¦gurations in USA, Russia, and EU date back to the early 1960s. The lesson learned in the past [1 5] is that hypersonic vehicle sizing