Fundamental Technologies for the Development of Future Space Transportsystem Components under high Thermal and Mechanical Loads

Haidn, Oskar; Adams, Nikolaus A.; Radespiel, Rolf; Schröder, Wolfgang; Stemmer, Christian; Sattelmayer, Thomas

doi:10.2514/6.2018-4466

Cited by 8 publications

(4 citation statements)

References 61 publications

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“…The investigation of such base flow phenomena on current and future space transportation vehicles with focus on the interaction of the ambient flow and the exhaust jet flow is one of the core research areas of the Collaborative Research Centre (SFB) Transregio 40 (TRR40) [1,7,16]. Previous publications indicate, that the buffet phenomenon, known to be the reason for prominent launcher failures (e.g.…”

Section: Related Activities Within Sfb/trr40mentioning

confidence: 99%

Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne

Kirchheck

Saile

Gülhan

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Rocket wake flows were under investigation within the Collaborative Research Centre SFB/TRR40 since the year 2009. The current paper summarizes the work conducted during its third and final funding period from 2017 to 2020. During that phase, focus was laid on establishing a new test environment at the German Aerospace Center (DLR) Cologne in order to improve the similarity of experimental rocket wake flow–jet interaction testing by utilizing hydrogen–oxygen combustion implemented into the wind tunnel model. The new facility was characterized during tests with the rocket combustor model HOC1 in static environment. The tests were conducted under relevant operating conditions to demonstrate the design’s suitability. During the first wind tunnel tests, interaction of subsonic ambient flow at Mach 0.8 with a hot exhaust jet of approx. 920 K was compared to previously investigated cold plume interaction tests using pressurized air at ambient temperature. The comparison revealed significant differences in the dynamic response of the wake flow field on the different types of exhaust plume simulation.

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Section: Related Activities Within Sfb/trr40mentioning

confidence: 99%

Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne

Kirchheck

Saile

Gülhan

2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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“…Since 2008, aft-body flows of space launch vehicles in various flow regimes have been investigated on generic launcher configurations within the frame of the Collaborative Research Centre (SFB) Transregio 40 (TRR40) (Haidn et al 2018;Adams et al 2021). Since 2016, one of the key interests has been laid in the interaction of the high subsonic ambient freestream with the supersonic overexpanded propulsive jet during the ascent phase of a launcher.…”

Section: Introductionmentioning

confidence: 99%

Plume and wall temperature impact on the subsonic aft-body flow of a generic space launcher geometry

Kirchheck,

Schumann,

Fertig

et al. 2024

Preprint

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Experimental and numerical simulation of launcher base flows is crucial for future launcher design. In experiments, the exhaust plume simulation is often limited to cold or slightly heated gases. In numerical simulations, multi-species reactive flow is often neglected due to limited resources. The impact of these simplifications on the relevant flow features compared to real flight scenarios needs to be characterized in order to enhance the design process. Experimental and numerical investigations were carried out in the frame of the SFB/TRR 40 Collaborative Research Centre in order to study the impact of plume and wall temperature on the base flow of a generic small-scale launcher configuration. Wind tunnel tests were performed in the Hot Plume Testing Facility (HPTF) at DLR Cologne, using subsonic ambient flow and pressurized air or hydrogen-oxygen-combustion as exhaust gases. The tests were numerically rebuilt using the DLR TAU code employing a scale-resolved IDDES approach, including thermal coupling and detailed chemistry. The paper combines the experimental and numerical findings from the SFB/TRR 40 base flow studies and highlights the most prominent influences on the mean flow field, the pressure field, the dynamic wake flow motion and the resulting aerodynamic forces on the nozzle. High-frequency pressure measurements, high-speed Schlieren recordings and time-resolved CFD results are evaluated using spectral and modal analysis of the one- and two-dimensional flow field data.

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“…To address this issue, a multidisciplinary experimental and numerical study of such problems was conducted within SFB TRR 40 [23,26,37,44,45,60].…”

Section: Introductionmentioning

confidence: 99%

Experiments on Aerothermal Supersonic Fluid-Structure Interaction

Daub

Willems

Esser

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Mastering aerothermal fluid-structure interaction (FSI) is crucial for the efficient and reliable design of future (reusable) launch vehicles. However, capabilities in this area are still quite limited. To address this issue, a multidisciplinary experimental and numerical study of such problems was conducted within SFB TRR 40. Our work during the last funding period was focused on studying the effects of moderate and high thermal loads. This paper provides an overview of our experiments on FSI including structural dynamics and thermal effects for configurations in two different flow regimes. The first setup was designed to study the combined effects of thermal and pressure loads. We investigated a range of conditions including shock-wave/boundary-layer interaction (SWBLI) with various incident shock angles leading to, in some cases, large flow separation with high amplitude temperature dependent panel oscillations. The respective aerothermal loads were studied in detail using a rigid reference panel. The second setup allowed us to study the effects of severe heating leading to plastic deformation of the structure. We obtained severe localized heating resulting in partly plastic deformations of more than 12 times the panel thickness. Furthermore, the effects of repeated load cycles were studied.

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Fundamental Technologies for the Development of Future Space Transportsystem Components under high Thermal and Mechanical Loads

Cited by 8 publications

References 61 publications

Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne

Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne

Plume and wall temperature impact on the subsonic aft-body flow of a generic space launcher geometry

Experiments on Aerothermal Supersonic Fluid-Structure Interaction

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