Shallow water experiments to verify a numerical analysis on an aerodynamically thrust-vectored aerospike nozzle

Sieder, J.; Propst, Martin; Bach, Christian

doi:10.1051/eucass/201911529

Cited by 2 publications

(1 citation statement)

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“…Both analyses confirmed the comparable flow structure with the sonic jet in cross-flow situations, characterised by the high-pressure zone upstream and the low-pressure zone downstream of the injection. A preliminary verification of the simulations was conducted through shallow water experiments, which demonstrated the existence of the high-pressure zone in a qualitative manner [19,20]. However, an adequate quantitative measurement of the flow field could not be derived.…”

Section: Introductionmentioning

confidence: 99%

Surface Pressure Measurement of Truncated, Linear Aerospike Nozzles Utilising Secondary Injection for Aerodynamic Thrust Vectoring

Sieder-Katzmann,

Propst,

Stark

et al. 2024

Aerospace

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A cold-gas test campaign has been conducted at the DLR’s P6.2 test bench in Lampoldshausen, with the objective of investigating the linear aerospike nozzle flow in interaction with secondary injection thrust vector control (SITVC). In this campaign, the influence of nozzle truncation, injection position and injection pressure on the nozzle surface and base pressure is analysed using pressure probes and Schlieren flow-visualisation techniques. The effects of injection position and truncation on the nozzle surface pressure development are comparable for all geometric variations, resulting in a locally increased static pressure upstream and a locally decreased static pressure downstream of the injection. The magnitude and dimension of these high- and low-pressure regions are correlated with the injection pressure. However, the influence of injection position and truncation on the base pressure is not entirely predictable by the named parameters, indicating an interdependence between both geometric parameters. Finally, the required pressure ratio of injection to the primary flow to ensure sonic injection has been analysed on TUD’s cold-gas test bench. This allows the respective injection position-dependent threshold to be identified. The analysis reveals that these experiments have been conducted under transsonic injection conditions.

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Section: Introductionmentioning

confidence: 99%

Surface Pressure Measurement of Truncated, Linear Aerospike Nozzles Utilising Secondary Injection for Aerodynamic Thrust Vectoring

Sieder-Katzmann,

Propst,

Stark

et al. 2024

Aerospace

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The State-of-the-Art and Prospects of Aerospike Engines

Vaulin

Khazhiakhmetov

2021

PoHEI.MB

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Currently, there is a worldwide trend of growing interest in projects aimed at reducing the cost of spacecraft launches. The search for solutions to this topical issue reveals new requirements for the rocket engines. However, existing rocket engines are incapable of fully meeting modern requirements. Consideration of new technical solutions indicates the prospects of using aerospike engines, which have the property of self-regulation and can operate with optimal flow expansion throughout the entire operation. This property allows this type of engine to be used as a propulsion system for single-stage return launcher. However, aerospike engines have not been sufficiently studied at the moment and haven’t found widespread use. Therefore it is necessary to summarize the existing knowledge about aerospike and the aerospike research has been performed. As a result mathematical models of the workflows were created, methods of designing and optimization of the contour were determined, and a number of design and technological solutions were found. However, the mathematical models verified by experimental data were not found.

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Shallow water experiments to verify a numerical analysis on an aerodynamically thrust-vectored aerospike nozzle

Cited by 2 publications

References 10 publications

Surface Pressure Measurement of Truncated, Linear Aerospike Nozzles Utilising Secondary Injection for Aerodynamic Thrust Vectoring

Surface Pressure Measurement of Truncated, Linear Aerospike Nozzles Utilising Secondary Injection for Aerodynamic Thrust Vectoring

The State-of-the-Art and Prospects of Aerospike Engines

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