Cost Modeling Considerations &amp; Challenges of the SpaceLiner - An Advanced Hypersonic, Suborbital Spaceplane

Trivailo, Olga; Sippel, Martin; Lentsch, A.; Şekercioğlu, Y. Ahmet

doi:10.2514/6.2013-5521

Cited by 5 publications

(4 citation statements)

References 13 publications

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“…Using this approach a market oriented development can be performed. A paper has been published [25] giving a detailed description.…”

Section: Cost Estimation and Business Casementioning

confidence: 99%

“…The combination of the process to establish initial and justifiable development and production cost estimates to use as input for a tool business case simulation tool is considered a solid foundation and methodology for future development of the SpaceLiner LCC assessment. Early results indicate that the SpaceLiner is not only a technically feasible concept but also one for which a viable business case might exist [25,26].…”

Section: Cost Estimation and Business Casementioning

confidence: 99%

See 1 more Smart Citation

SpaceLiner Technical Progress and Mission Definition

Sippel¹,

Schwanekamp²,

Trivailo³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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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 multinational 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 Subscripts, Abbreviations CAD computer aided design GLOW Gross Lift-Off Mass LH2 Liquid Hydrogen LOX Liquid Oxygen NPSP Net Positive Suction Pressure MECO Main Engine Cut Off MR mixture ratio RCS Reaction Control System RLV Reusable Launch Vehicle SLME SpaceLiner Main Engine TPS Thermal Protection System TRL Technology Readiness Level

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“…Using this approach a market oriented development can be performed. A paper has been published [25] giving a detailed description.…”

Section: Cost Estimation and Business Casementioning

confidence: 99%

Section: Cost Estimation and Business Casementioning

confidence: 99%

SpaceLiner Technical Progress and Mission Definition

Sippel¹,

Schwanekamp²,

Trivailo³

et al. 2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…An early assessment of the SpaceLiner's potential business case is described in the references 1, 2, and 5. A more detailed market analyses has been performed and results are published in [22,23]. An operational scenario of the integrated door-to-door travel concept and the comparison with conventional intercontinental travel options are described in [35].…”

Section: Figure 1: the Spaceliner Vision Of A Rocket-propelled Intercmentioning

confidence: 99%

Advanced Simulations of Reusable Hypersonic Rocket-Powered Stages

Sippel¹,

Bussler²,

Kopp³

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

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After successful completion of the MRR, technical progress of the SpaceLiner ultra-high-speed rocketpropelled passenger transport is achieved in Phase A conceptual design work. Following geometry refinement the structural design is maturing based on extensive trade-offs. Aerodynamics are investigated by numerical CFD-simulations of the two winged stages and will be supported by windtunnel tests. Aerodynamic control surfaces of the passenger cabin and rescue capsule and its subsystems are defined. Alternative options for the capsule with innovative morphing shapes are critically investigated taking into account system aspects, structural design, and advanced CFD-simulations. Potential intercontinental flight routes, considering range-safety and sonic boom constraints as well as good reachability from major business centers, are evaluated and flight guidance schemes are established. Extensions to this trajectory model are implemented to investigate the attitude dynamics and related controllability issues of the asymmetric launcher configuration. The space transportation role of the SpaceLiner concept as a TSTO-launcher is now addressed in technical detail. Subscripts, Abbreviations CAD computer aided design CEDRE Calcul d'Écoulements Diphasiques Réactifs pour l'Énergétique (CFD tool of ONERA) CFD

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“…The current and latest configuration under investigation at the DLR is the SpaceLiner 7 10,11,12 . 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.…”

Section: Introductionmentioning

confidence: 99%

Rarefied Aerothermodynamics Technology Development for Future High-Altitude High-Speed Transport (EU-FAST20XX)

Votta

Marini

Ranuzzi

et al. 2013

AIAA SPACE 2013 Conference and Exposition

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First subject of the present paper has been the experimental and numerical characterization of test chamber flow of DLR-V2G low-density wind tunnel, in the frame of EU-FP7 FAST20XX project activities dedicated to the validation of numerical tools able to predict rarefaction effects in suborbital flight. Pitot pressure radial profiles measured at different positions downstream the test chamber have been compared at nozzle exit to numerical results obtained with different methodologies accounting for rarefaction effects (CFD with slip-flow boundary conditions, a hybrid CFD-DSMC procedure), and a re-definition of the V2G facility envelope in terms of flight-relevant parameters (Mach, Reynolds, Knudsen numbers) has been presented. A good agreement between experiments and numerical results has been achieved for M=12 and M=16 cases (not as good for M=22), thus confirming that the test chamber flow knowledge is of fundamental importance for a proper numerical rebuilding of an experimental test campaign. Further, the aerodynamic coefficients of lift, drag and pitching moment of the analyzed lifting body configuration have been experimentally determined by means of three component force and moment measurements in V2G and the influence of rarefaction onto the aerodynamic coefficients have been shown. The results have numerically been validated by means of DSMC calculations. After the validation of the numerical tools, the high altitude effects to the future hypersonic/suborbital re-entry vehicle SpaceLiner have been analyzed. Bridging functions have been developed and validated by means of DSMC calculations. The effects of rarefaction on global longitudinal aerodynamics of SpaceLiner in the range of altitude 65÷85 km have been pointed out by comparing to the aerodatabase in continuum regime conditions. DSMC computation has been done in the higher SpaceLiner altitude point confirming the bridging function results and providing heat transfer estimations. Two versions of SpaceLiner have been analyzed: SL4.3 and SL7.1. Nomenclature AcronymsCEV = Crew Exploration Vehicle CFD = Computational Fluid Dynamics DSMC = Direct Simulation Monte Carlo ENO = Essentially Not Oscillatory FTB-X = Flying Test Bed X HSM = Hard Sphere Model mcs = Mean collision separation NExT = Numerical Experiment Tool PFA = Projected Frontal Area PPA = Projected Planform Area RANS = Reynolds Averaged Navier Stokes WA = Wetted Area Downloaded by PURDUE UNIVERSITY on July 30, 2015 | http://arc.aiaa.org | Symbols A = Surface, m 2 C D = Drag coefficient C L = Lift coefficient C p = Specific heat at constant pressure, J/kg/K d = Diameter of particles, m E H = = Aerodynamic Efficiency Total enthalpy, MJ/kg h Kn = = Altitude, Km Knudsen number, /L L l = = Lift, N Reference length, m L/D = Aerodynamic efficiency LH 2 = Liquid hydrogen LO 2 = Liquid oxygen M = Mach number m = Mass of particles, g mcs = Mean collision separation distance, m P, p = Pressure, Pa or bar P ND , P NL q R = = = Parameters defined by Eq. 5 and Eq. 6 Dynamic Pressure, PA Radius, m R gas = Ga...

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Cost Modeling Considerations & Challenges of the SpaceLiner - An Advanced Hypersonic, Suborbital Spaceplane

Cited by 5 publications

References 13 publications

SpaceLiner Technical Progress and Mission Definition

SpaceLiner Technical Progress and Mission Definition

Advanced Simulations of Reusable Hypersonic Rocket-Powered Stages

Rarefied Aerothermodynamics Technology Development for Future High-Altitude High-Speed Transport (EU-FAST20XX)

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