Ali Gülhan

Unsteady loads on a descending launcher first stage demonstrator in the aerodynamic phase

Junnai Zhai, Ansgar Marwege, Ali Gülhan

Abstract Within the Horizon Europe Project SALTO, a demonstrator of a vertically landing first stage equipped with three Prometheus engines (T3) was investigated. The vehicle is designed for recovery using a downrange landing approach. This paper analyzes the aerodynamic phase of the …

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APOSSUM – Asteroid Payload for Obtaining, Storing, and Sample return with Utility Module for the PRIAMOS mission

Christian J. Renggli, T. Kleine, Raphael Marschall, Bastian Gundlach et autres

The proposed PRIAMOS (PRImordial Asteroid Mission to understand the Origin of the Solar system) mission aims to revolutionize our understanding of the solar system’s formation by returning a pristine sample from a D-type asteroid. PRIAMOS would be the first European-led sample return …

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Characterization of Ablator Recession and Thermal Response Using Nonintrusive Techniques

C. Salvi, Oliver Hohn, Ali Gülhan

The main goal of this study is the investigation of the recession augmentation of cork-based ablators in a particle-laden Martian flow environment in the arc-heated facility L2K. The thermal response of the P50 cork-based ablator is assessed through recession and material temperature …

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Experiments on Aerothermal and Incident-Shock Effects on Fluid-Structure Interaction in Hypersonic Flow

Dennis Daub, Sebastian Willems, Ali Gülhan, S. Michael Spottswood et autres

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Informer deep learning forecasting for high-speed aeroelastics

Dimitris Drikakis, Ioannis W. Kokkinakis, Daryl L. X. Fung, S. Michael Spottswood et autres

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1D thickness evolution model of cork ablators, including swelling, ablation and erosion

C. Salvi, Oliver Hohn, Ali Gülhan

A one-dimensional mathematical framework is developed to describe the thickness evolution—swelling and recession—of cork samples in high enthalpy flows, in the arc-heated wind tunnel L2K. The model is formulated to account for swelling effect, constant long-term recession rate, particle-induced erosion, and post-erosion …

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Aerodynamic Excitations in the Near-Wake of Space Launchers: Insights from Hot Flow Experiments using High-Speed PIV

Dominik Saile, Viktor Kühl, Ali Gülhan

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PIV in the vicinity of cork samples in particle-laden high-enthalpy flow

C. Salvi, Ali Gülhan

Abstract This research aims at analysing the particle-laden flow of the high-enthalpy wind tunnel L2K, which is used to characterize the impact of dust particles on the recession behaviour of thermal protection systems during Martian entry flight. In the tests, a slightly …

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Calibration of COSSTA-PL low-pressure sensor of the Dragonfly entry capsule

Iina Jaakonaho, Maria Hieta, María Genzer, Jouni Polkko et autres

NASA is preparing to launch the Dragonfly mission, a rotorcraft lander destined for the surface of Saturn’s moon Titan [1]. As part of this mission, the entry vehicle will carry the Dragonfly Entry Aerosciences Measurements (DrEAM) payload [2], which includes a sensor …

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High-speed fluid–structure interaction predictions using a deep learning transformer architecture

Dimitris Drikakis, Daryl L. X. Fung, Ioannis W. Kokkinakis, S. Michael Spottswood et autres

This paper presents the development and application of a Transformer deep-learning model to fluid–structure problems induced by shock-turbulent boundary layer interaction. The model was trained on data from experiments conducted at a hypersonic wind tunnel under flow conditions that allowed for a …

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COSSTA-PL - Low-pressure sensor for Dragonfly entry capsule

Iina Jaakonaho, Maria Hieta, María Genzer, Jouni Polkko et autres

NASA's upcoming Dragonfly rotorcraft mission is planned to be deployed to the surface of Saturn’s moon Titan [1]. As part of the Dragonfly Entry Aerosciences Measurements (DrEAM) suite [2], the Dragonfly entry capsule will include a subsystem known as the COmbined Sensor …

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Preliminary Design of Expendable and Reusable Mixed-Staged Launch Vehicles

Pawel Goldyn, Ansgar Marwege, Johannes Riehmer, Josef Klevanski et autres

One of the very first tasks in launch vehicle design is the preliminary sizing. It is necessary for further design choices, but it should deliver a precise estimate of the launch vehicle’s mass and geometry as possible. Orbital launch vehicles can be …

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