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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13 Nov 2003
TL;DR: In this paper, a perchlorate oxidizing agent, a nitrogen-containing fuel, and a burn rate catalyst were used as a propellant material for the first time in a rocket.
Abstract: The invention relates to propellant compositions comprising a solid inorganic perchlorate oxidizing agent, a nitrogen-containing fuel, and a burn rate catalyst. Such compositions may be used as a propellant material, (e.g., in rocketry), a pyrotechnie material, an explosive material, a light generating material, a heat generating material, or a sound generating material.
6 citations
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29 Jun 2004TL;DR: In this paper, a solid rocket motor including a combustion chamber, in which propellant is ignited to produce combustion gas, and a nozzle having a throat with an effective flow area, implements a system and method to inject gas into the nozzle throat to control its effective cross sectional flow area.
Abstract: A solid rocket motor including a combustion chamber, in which propellant is ignited to produce combustion gas, and a nozzle having a throat with an effective flow area, implements a system and method to inject gas into the nozzle throat to control its effective cross sectional flow area. Controlling the effective cross sectional flow area of the nozzle throat in turn controls combustion chamber pressure, thus the burn rate of the propellant in the combustion chamber, and thus the thrust generated thereby.
6 citations
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10 Aug 1966
6 citations
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TL;DR: In this article, the effect of transition metal Phthalocyanines on the burn rate of composite solid propellants was investigated, as well as the combustion characteristics of such propellants.
Abstract: Transition metal Phthalocyanines have been used as burn rate modifiers for AP-HTPB composite solid propellants. An effort has been made to investigate the effect of Cu-Co-and Fe Phthalocyanines on the burn rate of composite propellants, as also on the combustion characteristics of such propellants. The burn rate has been determined in Crawford Strand Burner at 56 kg/cm 2 pressure as also in low pressure burner setup at vacuum of 0.5 kg/cm 2 . Thermal analysis was performed using Thermo Gravimetric Analyzer (TGA), Differential Scanning Calorimeter (DSC) and heat of reaction has been measured by conventional Bomb Calorimeter. Scanning Electron Microscope (SEM) and Elemental Analyzer have been used for material characterization and possible composition of composite solid propellants. Metal Phthalocyanines have been found to influence the decomposition and to enhance the burn rate of the composite solid propellants.
6 citations
01 Nov 1971
TL;DR: In this article, a mathematical model for transient internal ballistics developed during the study can be applied to a wide range of high preformance rocket motors which experience rapid ignition and pressurization transients.
Abstract: : Light weight solid propellant motors which supply high thrusts (greater than 500 lbf) for durations on the order 0.010 sec. (referred to as impulsive thrusters) require special analysis of items such as internal ballistics, propellant combustion, ignition stimuli, exhaust plume envelope, and inert hardware. A survey of the rocket motor concepts revealed that the desired thrust versus time program can be achieved by internal burning grains and existing high burning rate composite propellants. The mathematical model for transient internal ballistics developed during the study can be applied to a wide range of high preformance rocket motors which experience rapid ignition and pressurization transients.
6 citations