Experimental study of detonation in a cryogenic two-phase H2–O2 flow

Jouot, F.; Dupré, G.; Quilgars, A.; Gökalp, İskender; Cliquet, Elisa

doi:10.1016/j.proci.2010.06.160

Cited by 4 publications

(3 citation statements)

References 13 publications

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“…This result leads to an important conclusion: a strong detonation blast may be initiated by a spark or injection of hot gas in an aerosol mixture, not just by a strong shock wave, as is the case for gaseous mixtures [8]. Note that this conclusion has been confirmed in the very recent studies of detonation initiation in two-phase GH2/ LOx mixtures [17]. Also note that the maximum pressure of the aerosol detonation wave can even exceed that of the detonation wave in gas mixtures.…”

Section: Deflagration-to-detonation Transition In Unconfined Aerosmentioning

confidence: 57%

“…The laminar flame speed, which is determined by the conductive heat transfer in a quiescent gas, can be estimated as v D L D ∕τ burn κ air R burn ∕C air ρ air p ≃ 1.5 ÷ 2 m∕s where τ burn R −1 burn τ H2 ≃ 3 × 10 −6 s is the typical reaction time for the GH2/GOx/GN2 mixtures. Here we took advantage of a simplified model that takes into account that in the parameter regime of interest the reaction rate is mainly limited by the initiation reactions H 2 O 2 → OH OH and H 2 O 2 → HO 2 H [17]. The rate of these reactions may be written as R burn ATC H2 C Ox ≡ C H2 ∕τ burn [18] where AT 5.5 × 10 7 exp−19680∕T 0.74T 2.43 exp−26926∕T m 3 ∕mol • s and T is in degrees Kelvin.…”

Section: A Detonation and Deflagration Waves In Unconfined Gaseous Gmentioning

confidence: 99%

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Explosion Hazard from a Propellant-Tank Breach in Liquid Hydrogen-Oxygen Rockets

Осипов

Muratov

Hafiychuk

et al. 2013

Journal of Spacecraft and Rockets

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An engineering risk assessment of the conditions for massive explosions of cryogenic liquid hydrogen-oxygen rockets during launch accidents is presented. The assessment is based on the analysis of the data of purposeful rupture experiments with liquid oxygen and hydrogen tanks and on an interpretation of these data via analytical semiquantitative estimates and numerical simulations of simplified models for the whole range of the physical phenomena governing the outcome of a propellant-tank breach. The following sequence of events is reconstructed: rupture of fuel tanks, escape of the fluids from the ruptured tanks, liquid film boiling, fragmentation of liquid flow, formation of aerosol oxygen and hydrogen clouds, mixing of the clouds, droplet evaporation, self-ignition of the aerosol clouds, and aerosol combustion. The power of the explosion is determined by a small fraction of the escaped cryogens that become well mixed within the aerosol cloud during the delay time between rupture and ignition. Several scenarios of cavitation-induced self-ignition of the cryogenic hydrogen/oxygen mixture are discussed. The explosion parameters in a particular accident are expected to be highly varied and unpredictable due to randomness of the processes of formation, mixing, and ignition of oxygen and hydrogen clouds. Under certain conditions rocket accidents may result in very strong explosions with blast pressures from a few atm up to 100 atm. The most dangerous situations and the foreseeable risks for space missions are uncovered.

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Section: Deflagration-to-detonation Transition In Unconfined Aerosmentioning

confidence: 57%

Section: A Detonation and Deflagration Waves In Unconfined Gaseous Gmentioning

confidence: 99%

Explosion Hazard from a Propellant-Tank Breach in Liquid Hydrogen-Oxygen Rockets

Осипов

Muratov

Hafiychuk

et al. 2013

Journal of Spacecraft and Rockets

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“…Therefore, we have to verify that the measurements of the head pressure can be used to infer pressure at an arbitrary location of the hole along the rocket axis. To do so we simulate the model of internal ballistics of the SRM in the off-nominal regime with the case breach area dynamics given by (17) at arbitrary location. The results of such simulations for the case breach at the middle of the SRM are shown in the Figure 8.…”

Section: Modeling Case Breach Faultmentioning

confidence: 99%

Mathematical and Critical Physics Analysis of Engineering Problems: Old-New Way of Doing Things

Smelyanskiy¹,

Осипов

Luchinsky

et al. 2011

AIAA SPACE 2011 Conference &Amp; Exposition

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In a modern world, importance of computer modeling for solving complex engineering problems cannot be overstated. However, in a number of critical engineering problems computational models cannot provide unique answer and so further physical and analytical insight is required to guide computer simulations. Such an insight becomes even more valuable when off-nominal regimes of operation have to be considered. To deal with complexity of the physical process at the interface of multiple engineering systems a new discipline is emergingoperational physics of critical missions. This discipline combines an old-good physics based approach to modeling engineering problems with modern advanced technologies for analyzing continuous and discrete information flow involving multiple modes of operation in uncertain environments, unknown state variables, heterogeneous software and hardware components. In this paper the new approach is illustrated using as an example analysis of the critical physics phenomena that lead to Challenger accident including physics of cryogenic explosion and propagation of detonation waves, internal ballistics of SRM's in the presence of the case breach fault, and monitoring of the structural integrity of the spacecraft.

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