Analysis of rocket-engine transient regimes

Barrère, M.

doi:10.1016/0094-5765(77)90113-8

Cited by 3 publications

(3 citation statements)

References 11 publications

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“…Conversely, with regard to the definition of combustion delay time, the mass of propellant (m·b) burned at moment t is equal to the flow rate of liquid propellant injected at time t-τdc. In other words 14,19 …”

Section: Mathematical Modelingmentioning

confidence: 99%

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Mathematical modeling and analysis of cutoff impulse in a liquid-propellant rocket engine

Dehaj

Ebrahimi

Karimi

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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Thrust termination transient behavior of liquid-propellant rocket engines is important for launch vehicle to achieve the desired final velocity and, hence, fulfill the desired mission in placing a satellite in the intended orbit. A mathematical model has been developed for an open-cycle engine to predict the transient behavior of engine components, obtain the pressure changes of the combustion chamber, and to determine the cutoff impulse. By employing this model, the engine shutdown process has been simulated in four time intervals: (1) the duration from when cutoff command is issued to the time when the cutoff valves start to close, (2) closing of the cutoff valves, (3) discharge of combustion products from the chamber, and (4) the duration of the phase change and pressure fluctuations. The propellant flow has been modeled one-dimensionally in the cutoff valve and thermodynamically in the cooling channels and the combustion chamber. The results indicate that the time duration of the first two stages and the working pressure of the engine during the transmission of the cutoff command have considerable impacts on the increase or reduction of the thrust force. Also, with the improvement in modeling accuracy and the complete development of the engine processes, the results indicate a maximum error of 9% compared with the 15–41% error in the calculation of cutoff impulse achieved by previous works, which demonstrates the enhanced accuracy of the present modeling.

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Section: Mathematical Modelingmentioning

confidence: 99%

“…By differentiation equation (12) and substituting the result together with equations (10) and (9) into equation (8) and disregarding the changes in Rc, the following (combustion chamber) equation is obtained. 14,19 where …”

Section: Mathematical Modelingmentioning

confidence: 99%

Mathematical modeling and analysis of cutoff impulse in a liquid-propellant rocket engine

Dehaj

Ebrahimi

Karimi

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Barrere [13] stated that the accumulation of propellant energy occurs during the ignition transient phase, leading later to increase in the burning rates which are due to the change in initial temperature of the propellant. Isfahani et al [14] observed that the average burning rate of the solid propellant has threefold increase from its base value due to shear amplitude in the flow field.…”

Section: Introductionmentioning

confidence: 99%

Oscillatory Pressure Effect on Mean Burning Rates of Solid Propellant Combustion at Low Frequency Conditions

Kathiravan

Rajak

et al. 2019

Propellants Explo Pyrotec

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The investigation on acoustic pressure oscillation effect on the mean burning rate of solid propellant combustion under quasi and unsteady conditions has been carried out at elevated pressures typical of rocket operation. Experiments were conducted in the window bomb test facility to measure mean burning rate for the mean chamber pressure ranging from 1 to 7 MPa. This analysis facilitates current understanding regarding the mean burning rate variation due to the acoustic wave interaction with propellant flame complexes. The present work is focused on low frequency combustion instability and characterization of the long rocket motor configurations. The window bomb is connected with an exclusively designed rotating valve for the generation of acoustic pressure oscillations at selected mean chamber pressures and the corresponding frequency of operations. Two kinds of ammonium perchlorate/hydroxyl terminated poly butadiene (AP/HTPB) based composite propellants, one with aluminium, and the other without aluminium were considered. Experiments were conducted at the excited frequency of 140 Hz with different excited acoustic pressure amplitudes. This experimental setup facility has the provision of visual observation during propellant combustion using optical methods. The performance of the rotating valve was competent over the tested conditions. These studies reveal that the acoustic pressure amplitudes significantly enhance the mean burning rate of the solid propellants. The response of the aluminized propellants to the excited acoustic oscillations was relatively prominent as compared to that of its non‐aluminized counterparts. The results obtained are extremely useful in combustion instability characteristics of large scale rocket motors.

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Mitigation of Slivers Using a New Propellant Grain Design to Improve Propulsion Systems

Farrukh¹,

Khan²

2012

Aviation

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The research work addresses mathematical modelling and computational analysis of novel solid propellant grain configuration. The aviation industry is working on propulsion systems as well. For high thrust in rockets, space ships, and even in aircraft, solid propellant grains can be used as fuel. Grain design is a vital and integral part of solid propellant design. The designer has many options available for selecting grain configuration. Several design parameters – volumetric loading fractions, web fraction, length to diameter ratio, and port area – are normally tailored to mission demands. The star grain configuration has been a mainstay in this industry since 1935. The star grain configuration does however have a long-standing drawback, namely the formation of slivers. In this paper we present a new grain configuration, the “rose petal”, which overcomes the drawback of the traditional star grain design. The configuration is modelled using relevant internal ballistic relations. The design computation is executed in MATLAB. Thrust and time and burn area time curves are generated for a prescribed port area. Comparisons are drawn between the two configurations, clearly revealing that the new configuration obviates the occurrence of unwanted slivers otherwise generated in the old star design, which lowers the efficiency of all those propulsion systems in which solid propellants are used.

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Analysis of rocket-engine transient regimes

Cited by 3 publications

References 11 publications

Mathematical modeling and analysis of cutoff impulse in a liquid-propellant rocket engine

Mathematical modeling and analysis of cutoff impulse in a liquid-propellant rocket engine

Oscillatory Pressure Effect on Mean Burning Rates of Solid Propellant Combustion at Low Frequency Conditions

Mitigation of Slivers Using a New Propellant Grain Design to Improve Propulsion Systems

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