Aerodynamic Phenomena of Retro Propulsion Descent and Landing Configurations

Ansgar, Marwege,; Hantz, Christian; Kirchheck, Daniel; Klevanski, Josef; Vos, Jan B.; Laureti, Mariasole; Karl, Sebastian; Gülhan, Ali

doi:10.5281/zenodo.6783922

Cited by 2 publications

(9 citation statements)

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“…Where 𝜌 𝑒 , 𝑒 and 𝑢 𝑒 are the density, the temperature and the velocity at the nozzle exit, 𝑐𝑐 is the total pressure in the combustion chamber, and 𝜌 ∞ and 𝑢 ∞ are the density and velocity in the free stream. In (Marwege et al 2022c) this dependence could be confirmed with the same experimental data as in this paper. However, the plume length was measured in Schlieren snapshots, where the plume length can vary strongly.…”

Section: Proper Orthogonal Decomposition and Spectral Analysissupporting

confidence: 89%

“…In Fig. 4 the variance for each pixel was evaluated over 200 images (Marwege et al 2022c). In the resulting image the multi cell structure of the retro propulsion jet is visible.…”

Section: Subsonic Retro Propulsionmentioning

confidence: 99%

“…Furthermore, high fluctuations can be observed in the stagnation region between the jet and the free stream, as the variance is especially high in this region. In subsonic retro propulsion flows the characteristic flow feature, the plume length, depends on the square root of the Momentum Flux Ratio (MFR) as shown in (Jarvinen and Hill 1973), and in (Marwege et al 2022c) using recent experimental data. The MFR is defined as (Jarvinen and Hill 1973):…”

Section: Subsonic Retro Propulsionmentioning

confidence: 99%

“…The aerodynamics of RETALT1 have been studied with the aid of exhaustive Wind Tunnel Test series at the Department of Supersonic and Hypersonic Technologies of the German Aerospace Center (DLR) in Cologne. The reentry burn was modeled in the Hypersonic Wind Tunnel Cologne (H2K) (Marwege et al 2022c, Marwege et al 2022d), the aerodynamic phase was studied in the Trisonic Wind Tunnel Cologne (TMK) (Marwege et al 2022b, Marwege et al 2022c) and the landing burn was tested in the Vertical Free-Jet Facility Cologne (VMK) (Marwege et al 2022c). This paper is focused on cold gas tests of the landing burn.…”

Section: Introductionmentioning

confidence: 99%

“…This paper is focused on cold gas tests of the landing burn. While some insights on the flow field in this flight phases were presented in (Marwege et al 2022c), a dedicated modal analysis and frequency analysis was not performed, which is the aim of the work at hand. Furthermore, an averaged modal solution is proposed for a comprehensive description of the flow field phenomena.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Characteristics of the Retro Propulsion Landing Burn of Vertically Landing Launchers

Marwege,

Gülhan

2023

Preprint

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In the frame of the European funded H2020 project RETALT (Retro Propulsion Assisted Landing Technologies) the unsteady aerodynamics of vertically descending and landing launchers have been investigated. In this paper experimental data of the landing burn tested in the Vertical Free-Jet Facility Cologne (VMK) at DLR in Cologne is presented. The landing burn was simulated with a cold gas jet of pressurized air opposing the wind tunnel free stream. Tests with several jet conditions were compared to results without active jet. Proper Orthogonal Decomposition of Schlieren recordings and spectral analyses of their time histories are performed and are compared to frequencies in pressure measurements. Dominant frequencies were found, which are strongest at Mach 0.8. Especially a Strouhal number of 0.2 was found to be most dominant. The intensity of the dominant frequencies, can be lowered if the engine is active. The normalized root mean square pressure fluctuations are between 0.1 and 0.3 during the landing maneuver. Additionally, the steady flow features scale well with the ambient pressure ratio and the momentum flux ratio.

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Section: Proper Orthogonal Decomposition and Spectral Analysissupporting

confidence: 89%

“…In Fig. 4 the variance for each pixel was evaluated over 200 images (Marwege et al 2022c). In the resulting image the multi cell structure of the retro propulsion jet is visible.…”

Section: Subsonic Retro Propulsionmentioning

confidence: 99%

Section: Subsonic Retro Propulsionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Characteristics of the Retro Propulsion Landing Burn of Vertically Landing Launchers

Marwege,

Gülhan

2023

Preprint

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Mission Performance Assessment of the Recovery and Vertical Landing of a Reusable Launch Vehicle

Guadagnini,

De Zaiacomo,

Lavagna

2023

Aerospace

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This paper focuses on the mission analysis of the return trajectory of a Vertical Landing Reusable Launch Vehicle, both for Return-to-Launch-Site (RTLS) and DownRange Landing (DRL) recovery strategies. The main objective is to assess the mission performance of propellant-optimal re-entry and landing trajectories from the Main Engine Cut-Off (MECO) while considering propellant budget and peak entry conditions constraints. As a result, performance envelopes and feasibility regions are built to comprehensively assess the required propellant and compare recovery strategies across a broad spectrum of MECO conditions. The results show that the DRL strategy achieves higher efficiency concerning the propellant consumption and a larger robustness regarding the dispersed MECO conditions.

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Aerodynamic Phenomena of Retro Propulsion Descent and Landing Configurations

Cited by 2 publications

References 0 publications

Aerodynamic Characteristics of the Retro Propulsion Landing Burn of Vertically Landing Launchers

Aerodynamic Characteristics of the Retro Propulsion Landing Burn of Vertically Landing Launchers

Mission Performance Assessment of the Recovery and Vertical Landing of a Reusable Launch Vehicle

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