Ariane 5 Performance Optimization Using Dual-Bell Nozzle Extension

Stark, Ralf; Génin, Chloe; Schneider, Dirk; Fromm, Christian M.

doi:10.2514/1.a33363

Cited by 39 publications

(23 citation statements)

References 24 publications

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“…8 marks the air density corresponding to an altitude of 7 km. In recent system studies [13] this altitude was shown to be the upper transition mode limit of a dual bell nozzle applied, e.g., on Ariane 5 ECA. For densities above the marked value and for separation positions up to X/R th = 10.45, the density impact on nozzle flow separation is negligible.…”

Section: Resultsmentioning

confidence: 99%

Flow separation in rocket nozzles under high altitude condition

Stark

Génin

2016

Shock Waves

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The knowledge of flow separation in rocket nozzles is crucial for rocket engine design and optimum performance. Typically, flow separation is studied under sealevel conditions. However, this disregards the change of the ambient density during ascent of a launcher. The ambient flow properties are an important factor concerning the design of altitude-adaptive rocket nozzles like the dual bell nozzle. For this reason an experimental study was carried out to study the influence of the ambient density on flow separation within conventional nozzles.

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Section: Resultsmentioning

confidence: 99%

Flow separation in rocket nozzles under high altitude condition

Stark

Génin

2016

Shock Waves

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“…To study the impact of dual bell nozzles on the payload capacity of such a GTO launcher, a generic Ariane 5 ECA was defined and the conventional nozzle of its Vulcain 2 like main stage engine was replaced by a set of dual bell nozzles [39]. The generic Ariane 5 ECA launcher was modelled as a three stage rocket (see Tab.…”

Section: Prior Studiesmentioning

confidence: 99%

“…Miyazawa et al [10] stated a specific impulse gain of 10 s for a SSTO vehicle to LEO, based on a LE-7A engine. [39] Numerous system analysis were performed within FESTIP (Future European Space Transportation Investigation Programme). Immich and Caporicci [11,12] as well as Hagemann et al [13] analysed the FESTIP concept vehicle FSS-1 [14].…”

Section: Introductionmentioning

confidence: 99%

“…Hagemann et al [15] pointed out that during sealevel operation mode of the dual bell a 3% performance loss has to be considered, caused by the nozzle extension drag. [39] In the following one and a half decades the work mainly focused on the dual bell flow behaviour itself. Experimentally, the performance [16][17][18], the transition/sneak transition [19][20][21][22][23][24], the hysteresis/buffeting effect [18,21,25], the side loads [26], and the heat loads [27] were studied.…”

Section: Introductionmentioning

confidence: 99%

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Sea-level transitioning dual bell nozzles

Stark

Génin

2017

CEAS Space J

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To evaluate the impact of sea-level transitioning dual bell nozzles on the payload mass delivered into geostationary transfer orbit by Ariane 5 ECA, a detailed study was conducted. For this purpose, a multitude of Vulcain 2 and Vulcain 2.1 nozzle extension contours were designed. The two variation parameters were the position of the wall inflection and the constant wall pressure of the nozzle extension. Considering these parameters an approved analytical method was applied to predict the impact of the dual bell nozzles on the payload mass. The payload gain into geostationary transfer orbit was evaluated to be up to 219 kg.

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“…This increase of engine performance yields a potential payload gain. 11 The principle of the dual bell nozzle concept is illustrated in figure 1. Sea-level mode (top) and altitude mode (bottom) are both well known stable operation conditions and are of lesser interest in scientific research.…”

Section: Introductionmentioning

confidence: 99%