FESTIP technology developments in liquid rocket propulsion for reusable launch vehicles

Immich, H.; Caporicci, Marco

doi:10.2514/6.1996-3113

Cited by 30 publications

(20 citation statements)

References 3 publications

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“…Various concepts of altitude adaptive nozzles have been proposed in the literature to circumvent this limitation. The dual bell nozzle o¨ers a very promising alternative to conventional nozzles [1].…”

Section: Introductionmentioning

confidence: 99%

“…In 1994, Horn and Fisher [3] investigated the in §uence of the extension contour geometry on the §ow behavior in the ¦rst experimental study. In Europe, the FESTIP research group realized a feasibility and performance analysis [1,4]. Various parametrical studies have also been realized to understand the §ow phenomena and optimize the contour design [5,6].…”

Section: Introductionmentioning

confidence: 99%

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Experimental and numerical study of dual bell nozzle flow

Génin

Stark

Haidn

et al. 2013

Progress in Flight Physics

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The dual bell is a nozzle concept for altitude adaption. The §ow separates at the contour in §ection in sea level mode in a mainly controlled and symmetrical way, reducing the side load generation and increasing the thrust. The transition to altitude mode is reached when the §ow suddenly attaches to the extension for an improved altitude thrust. The conditions of this transition and its evolution are the key for the study of dual bell nozzles. For a better understanding of the §ow behavior, a two-dimensional (2D) subscale dual bell model has been designed and tested at the German Aerospace Center (DLR). The tests were divided into two campaigns and performed under cold and hot §ow conditions. The evolution of the shock system at the in §ection during the transition was observed using schlieren optics. The planar nozzle was tested under various conditions in pressure and temperature. Both test campaigns have been recalculated in cooperation with Astrium. Numerical and experimental results are presented.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental and numerical study of dual bell nozzle flow

Génin

Stark

Haidn

et al. 2013

Progress in Flight Physics

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show abstract

“…After the aerospike nozzle was resurrected as a candidate propulsion system for reusable launch vehicles, research on such nozzles became active again throughout the world, especially in the United States. Research in this area has also become active in Europe 3,4) and Japan. [5][6][7][8][9] Studies on aerospike nozzles in Japan started in the mid 90s at the National Aerospace Laboratory.…”

Section: Introductionmentioning

confidence: 99%

Flow Field and Performance Analysis of an Annular-Type Aerospike Nozzle with Base Bleeding

Ito

Fujii

2003

Trans. Japan Soc. Aero. S Sci.

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Aerospike nozzle flow fields are computationally analyzed by Navier-Stokes simulations. The secondary flow from the base surface is induced for the purpose of increasing total thrust. The computed result shows that base pressure efficiently increases when base bleeding is induced from the tip region of the base surface and injected radially inward towards the nozzle axis. The base bleeding induced at the tip of the base and injected horizontally with the axis produces maximum base thrust because the momentum thrust does not produce any divergence loss and the base pressure is kept high. Base bleeding induced against the existing recirculation flow results in lower base pressure distributions. Base bleeding that produces maximum thrust interacts with the exhaust flow and creates shock waves that emanate from the tip of the base. The shear layer is squeezed more towards the nozzle axis when base bleeding is induced and forces the stagnation point to move closer to the base surface.

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“…[8][9][10] Many features of the aerospike nozzles were clarified. The Future European Space Transportation Investigations Program 1) and Advanced Rocket Propulsion Technologies 2) have also activated similar research on such nozzles in Europe.…”

Section: Introductionmentioning

confidence: 99%

“…After the aerospike nozzle was resurrected as a candidate propulsion system for reusable launch vehicles, the research on such nozzles became active again in the United States. Research also became active in Europe 1,2) and Japan. [3][4][5][6][7][8][9][10] The studies on aerospike nozzles in Japan started in the mid 90's at the National Aerospace Laboratory.…”

Section: Introductionmentioning

confidence: 99%

Flow Field and Performance Analysis of Aerospike Nozzles with Simplified Clustered Modules

Ito

Fujii

2004

Trans. Japan Soc. Aero. S Sci.

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The fundamental characteristics of simplified clustered aerospike nozzles are analyzed by the computational fluid dynamics approach. Several types of aerospike nozzles, having 6, 12 and 24 inner nozzle modules with the same area ratio and total flow rate, are examined. The interactions of the exhaust flows from the neighboring modules create shock waves, which produce high-pressure regions on the nozzle surface. The base regions of the cluster-type aerospike nozzles are not influenced by the clustering of the modules and show features similar to axisymmetric-type aerospike nozzles. The base pressure is nearly equal to the environmental pressure when the pressure ratio is low and suddenly attains a constant pressure when the pressure ratio is high. The computed results show that the number of modules influence the thrust performance, and the major reason for the decrease in thrust performance with a smaller number of modules is due to thrust loss in the ramp region.

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FESTIP technology developments in liquid rocket propulsion for reusable launch vehicles

Cited by 30 publications

References 3 publications

Experimental and numerical study of dual bell nozzle flow

Experimental and numerical study of dual bell nozzle flow

Flow Field and Performance Analysis of an Annular-Type Aerospike Nozzle with Base Bleeding

Flow Field and Performance Analysis of Aerospike Nozzles with Simplified Clustered Modules

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