Technical Maturation of the SpaceLiner Concept

Sippel, Martin; Schwanekamp, Tobias; Bauer, Carola; Garbers, Nicole; Foreest, Arnold van; Tengzelius, Ulf; Lentsch, A.

doi:10.2514/6.2012-5850

Cited by 12 publications

(19 citation statements)

References 12 publications

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“…7, while for liquid propellant tanks data from Ref. 8 (2) Both equations reproduce the tendency that larger aircraft have usually lower NOF than smaller aircraft. For tank barrel sections (cylinders and domes), fixed NOF have been derived (Eq.…”

Section: Non-optimum Mass Considerationmentioning

confidence: 69%

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

Kopp

Garbers

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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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 EuropeAustralia reference mission carrying 50 passengers. In addition to the DLR internal activities, the SpaceLiner was also under investigation in the completed European Commission's research project FAST20XX, and is one of the study vehicles in the current European CHATT project. 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. For this task, a finite element based structural analysis tool will be used, allowing for rapid parametric studies for complex vehicle configurations with a high level of flexibility. This paper summarizes the current activities on the preliminary structural analysis for the SpaceLiner. Different materials and design options will be discussed, as well as the integration of structure and thermal protection system. A special focus will be placed on the design and the vehicle integration of the passenger rescue stage, which shall ensure a safe return of the passengers to ground in the case of a catastrophic failure of the vehicle. NomenclatureAETB = Alumina Enhanced Thermal Barrier Tiles AFRSI = Advanced Flexible Reusable Insulation Al = Aluminum Al-Li = Aluminum-Lithium AoA = Angle of Attack APDL = ANSYS Parametric Design Language CFRP = Carbon Fiber Reinforced Plastic CHATT = Cryogenic Hypersonic Advanced Tank Technologies CMC = Ceramic Matrix Composite c.o.g. = Center of Gravity CRS = Crew Rescue Stage DLR = Deutsches Zentrum fuer Luft-und Raumfahrt (German Aerospace Center) E = Young's Modulus EC = European Commission EF = Eigen-frequency FAST = Future High-Altitude High-Speed Transport FEA = Finite Element Analysis FRSI = Flexible Reusable Insulation GLOW = Gross Lift-Off Weight HySAP = Hypersonic Vehicle Structural 2 LC = Load Case LH2 = Liquid Hydrogen LOX = Liquid Oxygen M = Mach number m = mass MECO = Main Engine Cut-Off MPC = Multi-Point-Constraint NOF = Non-Optimum Factor NOM = Non-Optimum Mass n x = acceleration in vehicle longitudinal direction n z = acceleration in vehicle normal direction q max = Maximum Dynamic Pressure SART = Systemanalyse Raumtransport (Space Launcher Systems Analysis) TABI = Tailorable Advanced Blanket Insulation Ti = Titanium TNT = Trinitrotoluene TOP = TPS Optimization Program TPS = Thermal Protection System TUFI = Toughened Uni-Piece Fibrous Insulation ρ = Material Density σ yield = Yield Stress

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Section: Non-optimum Mass Considerationmentioning

confidence: 69%

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

Kopp

Garbers

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…Since the last hypersonic systems overview paper on the SpaceLiner [22] significant technical progress related to the overall launch configuration as well as to both stages, the reusable booster and the orbiter or passenger stage, has been achieved. The current arrangement of the two vehicles at lift-off is presented in Figure 3.…”

Section: Maturation To Spaceliner 7-3mentioning

confidence: 99%

“…The FOI structural design was not only looking into static load analyses but has been also addressing structural dynamic issues which are potentially critical for the feasibility of the design. A critical point was detected by Eigenmode analysis: The huge winglets were keeping the first few Eigenmodes of the wings below the global bending mode of the fuselage [22]. One option to improve the situation could have been repositioning the lateral stability surfaces to the fuselage.…”

Section: Figure 3: Sketch Of Latest Spaceliner 7-3 Launch Configuratimentioning

confidence: 99%

“…The two tanks are part of the load carrying structure and therefore the structural members are placed internally. The structure of the wing follows aircraft convention with ribs to make up the shape of the wing profile and spars to carry the main bending load [22,23,26]. FOI's booster lay-out served as an initial conceptual model for future iteration of the SpaceLiner [23,26].…”

Section: Figure 3: Sketch Of Latest Spaceliner 7-3 Launch Configuratimentioning

confidence: 99%

“…At the end of 2012 with conclusion of FAST20XX the SpaceLiner 7 reached its first consolidated technical status [22,26]. Several subsystems are sized and integrated, early operational scenarios are established, and cost and potential business cases are assessed.…”

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confidence: 99%

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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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Effects of the rotational vehicle dynamics on the ascent flight trajectory of the SpaceLiner concept

Krummen

Sippel

2018

CEAS Space J

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During the preliminary design of space transportation systems the vehicle dynamics are commonly reduced to a pointmass model for definition of the flight trajectory. While this approach effectively reduces the number of model parameters in the design process, it neglects the rotational dynamics of the vessel completely. Since the rotational degrees of freedom (DOF) have a significant influence on the vehicle's controllability, a sole analysis of the translational dynamics is insufficient to assess the general feasibility of the concept. This study investigates the ascent flight trajectory of the SpaceLiner vehicle, a concept for a hypersonic suborbital space plane, based on a newly developed 6-DOF flight dynamics simulation to determine the influence of the rotational dynamics on the vehicle's controllability and performance. The first part of this paper will focus on the developed vehicle model which features a transient inertia model as well as an algorithmic-designed flight control system. The second part will present several simulations of nominal and off-nominal ascent trajectories. Based on the results it will be shown that SpaceLiner's thrust vector control system is sufficiently dimensioned for the investigated mission scenarios, while the vehicle performance is only slightly influenced by the rotational dynamics.

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Technical Maturation of the SpaceLiner Concept

Cited by 12 publications

References 12 publications

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

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

SpaceLiner Technical Progress and Mission Definition

Effects of the rotational vehicle dynamics on the ascent flight trajectory of the SpaceLiner concept

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