Improved method of measuring pressure coupled response for composite solid propellants

Su, Wanxing; Wang, Ningfei; Li, Junwei; Zhao, Yandong; Yan, Mi

doi:10.1016/j.jsv.2013.12.003

Cited by 26 publications

(7 citation statements)

References 27 publications

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“…During unsteady burn rate measurements, the rotating valve usually runs, slightly at a higher rpm than the calibrated test conditions. The natural frequency of the tube or any duct depends on length of tube and local speed of the sound, i. e., gas temperature [27]. FFT is the tool which validates the occurrence of resonant mode inside tube from its harmonic contents.…”

Section: Calibration Results Of Rotating Valvementioning

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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Section: Calibration Results Of Rotating Valvementioning

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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“…α is a real value, and  denotes the growth (>0) or decay (<0) rate of the acoustic disturbances. In the literature, Su et al [31] conducted experimental measurements of the decay rate (characterizing the acoustic attenuation/loss effect) of a solid-propellant rocket motor. The decay rate G=α/ω is in the range of -0.05≤G≤-0.0068 [31].…”

Section: Chemical Reaction-thermodynamics-acoustics Analysismentioning

confidence: 99%

Thermodynamics-Acoustics Coupling Studies on Self-Excited Combustion Oscillations Maximum Growth Rate

Zhao

2020

J. Therm. Sci.

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Unlike electric vehicles and electric aircrafts, hydrocarbon-fuelled (fossil) engine systems are much noisier. By conducting one-step chemical reaction-thermodynamics-acoustics coupling studies and experimental measurements, we explore the universal physics of how hydrocarbon-fuelled combustion is a noise maker. We also explain that how combustion-sustained noise at a particular frequency ω is intrinsically selected. These frequencies correspond to the acoustic resonance nature of the combustor. We find that a reacting gas in which the rate of chemical reacting increases with temperature is intrinsically and naturally unstable with respect to acoustic wave motion, since its modal growth rate α is greater than 0. Acoustic disturbances tend to exponentially i.e. exp(αt) increased first and then are limited by nonlinear effects and finally grow into limit cycle oscillations. The growth rate α is found to increase first and then decrease with the gradient of the heat release rate with respect to the temperature change, i.e. heat capacity. The maximum (α/ω) max depends on the specific heat ratio γ, which is related to the speed of sound. The unstable nature could be changed by introducing some acoustic dissipative/damping mechanism, such as the boundary layer viscous drag and boundary losses. It is shown that such losses could lead to increased critical heat capacity, below which stable combustors can be designed. Finally, the acoustical energy consisting of both potential and kinetic energy is found to grow exponentially faster by 100% than the acoustic disturbance amplitude.

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“…The dependence of the mechanical properties of composite modified double base propellant on the strain rate is investigated in [4]. The method for measuring the pressure coupled response of composite propellant is suggested in [5]. A numerical approach for simulating the fluid-solid interaction problems in the ignition transient is suggested by Li, Liu, He [6].…”

Section: Introductionmentioning

confidence: 99%

Model of Segmentation of Rocket Fairings Due to the Action of a Cumulative Charge

et al. 2018

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Safe separation of the rocket payload fairing is one of the most important factors that affect the success of a flight mission. In recent years, composite materials instead of aluminum alloys are widely used in rocketry. Such materials must satisfy a number of requirements that include the certainty of a local failure due to the action of a cumulative charge of the given power. To analyze this process numerical research is an advisable approach. The model of a composite rocket fairing separating due to the action of a cumulative charge has been developed. The properties of the composite material have been modeled based on the averaged characteristics obtained experimentally. The cumulative charge has been modeled by impulse loading having parameters adequate to the charge type. The time of action of the impulse, maximum pressure and width of the loading area are determined from the charge properties and geometry. The rocket fairing is considered as a composite shell composed of conical and cylindrical parts. A technique for 3D numerical analysis of the dynamic strength and structural failure has been developed. The mathematical model of the structure deformation and failure takes into account the dynamical properties of the material. The maximum plastic deformation is used as a failure criterion. The results of numerical simulation for the typical rocket payload fairing are presented.

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Improved method of measuring pressure coupled response for composite solid propellants

Cited by 26 publications

References 27 publications

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

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

Thermodynamics-Acoustics Coupling Studies on Self-Excited Combustion Oscillations Maximum Growth Rate

Model of Segmentation of Rocket Fairings Due to the Action of a Cumulative Charge

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