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 paper, the authors reported that the change in the burn-rate pressure index is from 0.2 to 0.65 in one of the propellants and that the same grain can act as boost and sustain grain depending on the combustion chamber pressure.
Abstract: Iron oxide and copper chromite have been used as burn-rate modifiers of composite solid propellants. In recent times, studies have been reported on potassium-doped ammonium perchlorate and on dry activated charcoal. These have shown an increase in composite solid propellant burning rates. The studies on composite solid propellants using dry activated charcoal have also shown a reduction in the burn-rate pressure index for a composite solid propellant. With this knowledge, experiments are conducted to develop compositions that result in both high burning rates and low burn-rate pressure index of the propellant. In addition to these, the study also reports propellants with dual burn-rate pressure index. The change in the burn-rate pressure index is from 0.2 to 0.65 in one of the propellants. These could be very useful in that the same grain can act as boost and sustain grain depending on the combustion chamber pressure. With the addition of different burn-rate modifiers, the pressure at which the change in ...
4 citations
30 Jun 2016
TL;DR: In this paper, the effects of several nano combustion modifiers (nm-DPT, nm-CB and nm-Al) on the combustion properties of DB/Al/CMDB/RDX-CMDB propellants were investigated through a solventless extrusion technique.
Abstract: In order to investigate the effects of several nano combustion modifiers (nm-DPT, nm-CB and nm-Al) on the combustion properties of DB/Al-CMDB/RDX-CMDB propellants, the propellant samples were prepared through a solventless extrusion technique. The burning rates of propellants were measured by the strand burner method. The results showed that the nm-DPT enabled a plateau burning effect to appear for the Al-CMDB propellant in the pressure range of 8~22MPa, and the burning rate at 10MPa to exceed 29mm/s. The additional nm-CB powder increased the burning rates of the propellant, and the propellant burning rate at 10MPa exceeded 35mm/s. The nm-DPT enabled a plateau burning effect to appear for the RDX-CMDB propellant in the pressure range of 8~22MPa and a mesa effect in the pressure range of 12~22MPa, and the burning rate at 10MPa to exceeded 28mm/s. The additional nm-CB increased the burning rate of the propellant, the burning rate at 10MPa exceeded 30mm/s and the pressure exponent in the pressure of 16~22MPa was -0.10.
4 citations
TL;DR: In this paper, the authors derived the burning rate formula and the heat loss rate equation of the constant volume burner method, and the effects of four factors (pressure increasing rate, burning time, ignition, and burning rate) on heat loss during operation were carried out.
Abstract: In this article, the method of the constant volume burner was used to measure the solid propellant burning rate under high pressure. The burning rate formula and the heat loss rate equation of the constant volume burner method were derived, and the effects of four factors (pressure increasing rate, burning time, ignition, and burning rate) on the heat loss of the constant volume burner during operation were carried out. Furthermore, the testing reproducibility on burning rate was analyzed. It was shown that sample size precision, moles per unit mass of propellant, and heat loss were the main factors for the accuracy of the constant volume burner method. The shorter the burning time, the faster the pressure increasing rate and the burning rate; the less the heat loss, the appropriate ignition way was to reduce heat loss ignition. Moreover, for both various burning rates of propellants, the parallel error of the test results obtained by the method was low, and the reproducibility was high. The burning rates...
4 citations
TL;DR: In this article, a method for the determination of burning rates of unknown propellants whose from function is unknown is introduced, which can be applied to any unknown propellant of any shape whose web size can be measured and very large webs also can be used.
Abstract: A method for the determination of burning rates of propellants whose from function is unknown is introduced. The method consists of burning in the closed vessel, a known charge weight of the test propellant alongwith a known pressure which remains nearly constant during the burning of the test propellant whose web size is the only quantity required for the evaluation of its rate of burning. The test propellants burns at near constant pressure conditions just as in the strand burner technique. This method can be applied to any unknown propellant of any shape whose web size can be measured and very large webs also can be used. In addition, the measurement of the records and the computation are very simple.
4 citations
TL;DR: In this paper, a linear regression analysis was used to fit the adaptive Wiebe model to experimental data with an average R2 value of 0.965, and the scaling process was expanded to include oxy-methane combustion for specialized SI applications, e.g., for stationary or mobile power generation in environments such as Mars.
4 citations