Topic
Burn rate (chemistry)
About: Burn rate (chemistry) is a research topic. Over the lifetime, 847 publications have been published within this topic receiving 8908 citations. The topic is also known as: Burning rate.
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TL;DR: In this article, the ignition characteristics of three typical composite propellants were studied, in order to promote the new high energy composite propellant's application, and the result showed that the new generation high energy propellant can be ignited easily, the ignition energy of it is less than the other two propellants, its ignition security should be paid more attention.
Abstract: The ignition characteristics of three typical composite propellants were studied,in order to promote the new high energy composite propellant's application.On different density of heat flow rate, environmental pressure and original temperature conditions, the ignition law of the HTPB propellant, two types of high energy propellant were obtained.The result shows that the new generation high energy propellant can be ignited easily, the ignition energy of it is less than the other two propellants ,its ignition security should be paid more attention.
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01 Jan 2017TL;DR: In this article, the effects of burning rate and grain design effects on thrust-time tailoring were discussed as well as the sensitivity of the solid propellant to temperature, and the transient behavior and equilibration of the combustion chamber pressure was analyzed.
Abstract: Solid rocket motors and various solid propellant grain configurations are described. Burning rate and grain design effects on thrust-time tailoring are discussed as well as the sensitivity of the solid propellant to temperature. Analysis of the transient behavior and equilibration of the combustion chamber pressure, the stability of the combustion chamber pressure, and the effects of erosive burning is presented. Solid rocket performance characteristics, dual thrust solid rockets, rocket motor casings, and transient operation are discussed. Rocket motor nozzle heat transfer and ablative and film cooling techniques are described. Methods for optimally sizing a rocket motor are presented. Hybrid rocket motors are introduced and their characteristics and operation are covered.
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TL;DR: In this paper, the effect of different mixture in a high volumetric concentration of oxidizer (AP), with least percentage of binder (HTPB+TDI), for improving the propellant burn rate was investigated.
Abstract: The effect of the different mixture in a high volumetric concentration of oxidizer – (AP), with least percentage of binder – (HTPB+TDI), for improving the propellant burn rate was investigated. The combustion experiment is performed using a window bomb set-up and the high-speed camera is utilized to capture the flame images. An image processing approach is used to measure the burn rate and intrinsic instability of flame by discrete wavelet transform method. Region growing algorithm technique is used for image segmentation. The morphological operation is implemented with Euclidean distance measurement for the identification of flame height in configuring with dependent parameters (burning rate, diffusion flame height). The qualitative analysis (signal characterization) and quantitative analysis (mean, kurtosis, skewness, standard deviation, and frequency) were used to study the intrinsic instability characteristics of the flame diffusion. A result obtained from the analysis proves that the instability in fuel combustion occurs at higher mix and pressure level.
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TL;DR: In this article, the influence of meteorological factors, ignition method, and fuel conditions on the behavior of smoke plumes from open field burning was quantified using ground-based and airborne instrumentation.
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