Transient Combustion in Solid Propellant Cracks PDF Download
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Languages : en
Pages : 50
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Book Description
A one-dimensional theoretical model, incorporating the Noble-Abel dense gas law, has been developed to describe the transient model combustion phenomena inside a propellant crack. The theoretical model can be used to predict wave phenomena, heat transfer from the gas to the propellant surface and associated thermal penetration, flame propagation, and resultant pressurization at various locations along the propellant cavity. Calculations made with the current theoretical model revealed that the internal pressurization rate, pressure gradient, and flame velocity in propellant cracks (for which gases can penetrate) decrease as: the gap width increases, the rocket chamber pressurization rate decreases, and the propellant gasification temperature increases. Additionally, the predicted flame spreading was found to decelerate in a region near the crack tip; this phenomena has been experimentally observed by others.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 50
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Book Description
A one-dimensional theoretical model, incorporating the Noble-Abel dense gas law, has been developed to describe the transient model combustion phenomena inside a propellant crack. The theoretical model can be used to predict wave phenomena, heat transfer from the gas to the propellant surface and associated thermal penetration, flame propagation, and resultant pressurization at various locations along the propellant cavity. Calculations made with the current theoretical model revealed that the internal pressurization rate, pressure gradient, and flame velocity in propellant cracks (for which gases can penetrate) decrease as: the gap width increases, the rocket chamber pressurization rate decreases, and the propellant gasification temperature increases. Additionally, the predicted flame spreading was found to decelerate in a region near the crack tip; this phenomena has been experimentally observed by others.
Author: K. K. Kuo
Publisher:
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Category :
Languages : en
Pages :
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Author:
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Category :
Languages : en
Pages : 66
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Book Description
This report is a facsimile of a report submitted by Systems Associates, Pennsylvania State University, under Contract N60530-79C-0006 and maintains the original format. It includes the study of dynamic burning effects in the combustion of solid propellants with cracks, and the use of granular bed combustion codes for solving hazard problems in rocket propulsion systems. The Zeldovich quasi-steady flame model was used in the evaluation of the dynamic burning effect. The dynamic burning rate was obtained by solving the transient heat conduction equation for the solid propellant and using the Zeldovich map for determining the heat feedback. Results indicate a stronger dynamic burning response for a higher pressurization rate, larger energy storage in the propellant, and lower initial pressure. A dynamic burning-rate augmentation function was developed to facilitate the incorporation of the transient burning effect into the crack combustion code. The augmentation function is in close correlation with results obtained from the finite difference method over the broad range of conditions studied. The mobile and fixed granular bed combustion codes (MGBC and FGBC), users manuals for these two programs, sample input data, and output listing were delivered to NWC.
Author:
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Category :
Languages : en
Pages : 100
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Book Description
This report presents results of a study of combustion processes in solid propellant cracks. As might be expected, under moderate chamber pressurization rates (10,000 atm/s), the theoretical predictions, as well as the experimental observations, indicate that the ignition front propagates from the entrance of the crack to the tip. However, under rapid chamber pressurization rates (100,000 atm/s or higher), the tip region of the crack was observed to ignite before the arrival of the convective ignition front. (Ignition is defined here as the onset of emission of luminous light from the propellant surface with some material loss. A theoretical model has been developed to explain the tip ignition phenomena. The model considers: a one-dimensional transient heat conduction equation for the solid phase; and one-dimensional, unsteady mass and energy conservation equations for the gas phase near the crack tip. Both experimental and theoretical results indicate that the ignition delay time decreases as the pressurization rate is increased.
Author: Martin Summerfield
Publisher: AIAA
ISBN: 9781600863967
Category : Solid propellants
Languages : en
Pages : 922
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Book Description
Author: Mridul Kumar
Publisher:
ISBN:
Category : Combustion
Languages : en
Pages : 196
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 400
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Author: Jerald L. Cunningham
Publisher:
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Category :
Languages : en
Pages : 173
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Book Description
An experimental study was conducted to investigate the spread of combustion flames into solid rocket propellant cracks. Experiments were performed using a combustion vessel with a free flowing nitrogen atmosphere under pressures of 300, 500, and 750 psig. Samples of three different propellants having crack widths varying from 0.022 in to 0.044 in were used. The ignition of the samples and the flame spread were recorded with a high-speed motion camera. Tests showed that the flame velocity inside the crack channels increased as the crack width decreased, and an entrance delay time usually exists prior to the flame entering the crack channel. For the range of crack widths investigated, no crack width was found for which flame penetration did not occur. Crack width demonstrated a greater effect on flame spread velocity in the crack than combustion pressure. The flame velocity flow inside a crack as a function of pressure and crack size is unique for each propellant tested.
Author: Yeu-Cherng Lu
Publisher:
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Category :
Languages : en
Pages :
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Author: Norman W. Ryan
Publisher:
ISBN:
Category :
Languages : en
Pages : 70
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The report is largely a restatement of conclusions, with reference to previous publications for details. The areas of study reported are an evaluation of the hot-wire-ignition method for characterizing propellants; the development and study of a gas-fueled analog of the solid-propellant T-burner; a study of low frequency (L*) combustion of L* during a test; a study of high frequency acoustic instability of solid propellants, both a T-burner and a radial-mode, radial-flow burner being used with the same propellants systems; the development and evaluation of a technique for measuring the solid-propellant response function to external energy perturbations at the burning surface; the measurement and evaluation of transient temperatures of propellant flames during rapid depressurization; and a detailed characterization of the low-pressure-combustion phenomena for several different solid propellants including studies of the low-pressure deflagration limit, the electrical conductance near the surface, the extinguishment requirements, and spontaneous reignition. (Author Modified Abstract).
