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 average burning rates of a parametric series of aluminized propellants were determined in acceleration fields up to 1000 g using a combustion bomb mounted on a centrifuge.
Abstract: The average burning rates of a parametric series of propellants were determined in acceleration fields up to 1000 g using a combustion bomb mounted on a centrifuge. The propellant strands were burned at 500, 1000, and 1500 psia with the acceleration field directed normal and into the burning surface. Acceleration caused a time-dependent increase of as much as 100% in the burning rate of relatively slow-burning aluminized propellants. The relative amount of burning-rate increase for the various propellants was strongly dependent on the amount of aluminum retained on the propellant surface during burning. The burning rates of two very fast-burning propellants were found to be essentially accelerationindependent. OLID-PROPELLANT rocket motors are currently being used in applications which subject the metallized propellant grains to acceleration fields. The propellant burning rates increase appreciably when the acceleration field is imposed normal and into the burning surface.1'2 Postfire inspections of motors containing metallized propellants have revealed the presence of metal and/or metal oxide residue in the motor cases. The propellant burning-rate increase and the retention of residue appear to be interrelated. The review and abstracting of the literature on the effects of acceleration on solid-propell ant performance are presented in Refs. 3 and 4. Although progress has been made toward an understanding of some aspects of burning-rate augmentation in acceleration fields, it was believed that additional experimental studies with well-controlled propellant parameters would yield valuable insight. A parametric series of aluminized propellants was formulated to establish the importance of some of the propellant parameters that could be controlled to minimize the effects of acceleration. The objectives of this investigation were twofold. The first objective was to obtain the quantitative effect of acceleration on the burning rate of the propellants as a function of propellant composition, acceleration level, and time. The second objective was to obtain quantitative information on the amount of aluminum and/or aluminum oxide residue retained in the inhibitor case as a function of propellant -composition, acceleration level, pressure level, and propellant burning rate.
17 citations
TL;DR: In this article, the phase morphologies and crystal composition of synthesized nano-catalysts were examined using Scanning Electron Microscope (SEM), Energy Dispersive Spectroscopy (EDS) and Fourier Transform Infrared Spectrography (FTIR) methods.
17 citations
TL;DR: In this paper, the authors investigated the performance of RP-1 surrogate fuel (RP-1-s), its constituents, and two novel energetic fuels (1,3-bishomocubane dimer (BHCD) and bis(nitratomethyl)-1-3-bi-mocubanes (DNMBHC) for rocket propulsion.
17 citations
Patent•
09 May 2001
TL;DR: A combustion system for a portable forced air heater having two frusta-conical sections attached to a circular burner tube is described in this article, where each frustaconical section has pre-determined vent hole patterns that allow the gas heater to have a variable burn rate.
Abstract: A combustion system for a portable forced air heater having two frusta-conical sections attached to a circular burner tube, wherein each frusta-conical section has pre-determined vent hole patterns that allow the gas heater to have a variable burn rate.
17 citations
01 Jan 1993
TL;DR: In this article, the authors discuss the solid propellant combustion and internal ballistics of motors, and the burning rate is defined as the distance traveled by the flame front per unit of time, measured normally to the burning surface.
Abstract: Publisher Summary This chapter discusses the solid propellant combustion and internal ballistics of motors. The combustion of a solid propellant is characterized by the way its surface regresses once it begins to burn. The burning rate is the distance traveled by the flame front per unit of time, measured normally to the burning surface. The burning rate is obtained by the strand useful length and the duration of the firing. The latter is determined by monitoring the noise created by the combustion. The advantage of this method is that a preliminary lateral restriction of the strand is not necessary. The introduction during the manufacturing of ballistic catalysts in propellant compositions allows the regulation of the burning-rate level and a significant decrease in the values of temperature coefficients and pressure exponents. Heterogeneous propellants contain a mixture of these ingredients, while decomposition releases gaseous products whose nature is either oxidizing or reducing. The addition of low-particle content, as ingredients in the propellant, is often successful in stabilizing motor combustion. This is particularly true in the case of tangential instabilities.
17 citations