Cryogenic Propellant Tank and Feedline Design Studies in the Framework of the CHATT Project

Schwanekamp, Tobias; Ludwig, Carina; Sippel, Martin

doi:10.2514/6.2014-2370

Cited by 6 publications

(6 citation statements)

References 6 publications

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“…The high static pressure in the LOX tank is the result of a boosterorbiter cross-feed system 15 . The static pressures are complemented by hydrostatic pressures that are computed by ANSYS during the HySAP optimization.…”

Section: B Loadsmentioning

confidence: 99%

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: B Loadsmentioning

confidence: 99%

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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“…American Institute of Aeronautics and Astronautics Paper AIAA 2015-3582 Beyond the steady state simulation also the transient behavior in the propellant feed-system has been analyzed for critical conditions along the powered flight and its preferred actuation sequence has been preliminarily defined [30].…”

Section: E Subsystem Definitionsmentioning

confidence: 99%

“…In particular, the process of booster separation is a dimensioning factor for the design of the crossfeed system due to the switch of the propellant supply from the booster to the orbiter tanks [30]. The propellant feed-and pressurization system is preliminarily designed using the DLR-tool pmp.…”

Section: E Subsystem Definitionsmentioning

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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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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“…Both stages are propelled by 11 bipropellant LOX/LH2 rocket engines (SLME), possessing 9 engines on the SLB and 2 on the SLP stage [4]. The cryogenic propellants for all engines are stored inside the fuselage of both stages, also allowing for a cross-feed from the SLB tanks to the SLP engines [5]. All passengers are seated in the SpaceLiner Passenger Capsule (SLC) in the forward compartment of the SLP stage which could be ejected in case of hazardous flight anomalies [6].…”

Section: Fig 1 Artist's Impression Of the Spaceliner 7-3 During Stagmentioning

confidence: 99%

“…In order to determine the variable propellant mass distribution inside the vehicle a simplified volume model of the propellant system has been established. As shown in FIG 8 this model has been derived from the SpaceLiner's tanks and feedline geometry [5]. During simulation the filling level of each tank and feedline is calculated dynamically to determine the instantaneous inertia tensor of the vehicle.…”

Section: Fig 7 Mass Model Of the Spaceliner Subsystems; The Volume Omentioning

confidence: 99%

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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Cryogenic Propellant Tank and Feedline Design Studies in the Framework of the CHATT Project

Cited by 6 publications

References 6 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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