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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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Patent
13 Jul 1987
TL;DR: In this paper, a method of making solid rocket propellant that facilitates tailoring of a variable burn rate is presented, which comprises molding binder and fuel and/or oxidizer to produce, for example, a molded strip of solid rocket fuel material.
Abstract: A method of making solid rocket propellant that facilitates tailoring of a variable burn rate. The method comprises molding binder and fuel and/or oxidizer to produce, for example, a molded strip of solid rocket propellant material. The molded solid rocket propellant material is formed into a desired shape by, for example, filament winding. In a preferred aspect, the solid rocket propellant is cured prior to being encased in a rocket motor casing. This improves rocket propellant to rocket engine casing bonding. Yet another aspect of this invention is a method of making solid rocket propellant comprising forming binder and oxidizer into separate strips and combining the binder and oxidizer strips to form solid rocket propellant material.

7 citations

Journal ArticleDOI
TL;DR: In this paper, an engineering model of a solid propellant gas generator was manufactured using the combustion gas properties calculated by a chemical equilibrium code and then hot-fire tests were performed.

7 citations

Proceedings ArticleDOI
14 Jul 2013
TL;DR: In this paper, the authors evaluated the performance of ivyanes relative to paraffin for typical rocket engine scenarios and used the G3MP2/B3LYP method to predict the heats of formation and combustion for gas phase IVyanes.
Abstract: Highly strained hydrocarbons called ivyanes are evaluated as a potential additive to boost the burn rate and Isp for liquefying paraffin hybrid rockets. Ivyanes, which consist of cyclopropane rings bonded together, were first prepared in 2011 and have promise as a High Energy Density Material (HEDM) for propulsion and combustion applications. Differential Scanning Calorimetry (DSC) measurements were carried out on samples of ivyane and an ivyane-paraffin blend to measure phase changes and thermal stability. Quantum chemistry calculations were carried out using the G3MP2//B3LYP method to predict heats of formation and combustion for gas phase ivyanes. For validation purposes, calculations were also carried out for normal alkanes. Chemical equilibrium analysis was used to estimate the performance of ivyanes relative to paraffin for typical rocket engine scenarios. In addition, thermochemical properties of some plausible chemically modified ivyanes were modeled determine if they would improve rocket engine performance.

7 citations

Journal ArticleDOI
TL;DR: In this paper, a series of experiments were conducted using high burning rate composite propellant (burn rate ~20 mm/s at 7,000 kPa), in order to determine the precise effects of such parameters on the results obtained.
Abstract: Dynamic mechanical analysis is a unique technique that measures the modulus and damping of materials as they are deformed under periodic stress. Propellants, which are viscoelastic in nature, are subjected to time, temperature, and frequency effects during the analysis to determine their dynamic and transient properties. The choice of parameters during the experiments like temperature, frequency, strain (%), and stress level is very crucial to the results obtained since the propellant behaves differently under different conditions. A series of experiments like strain and temperature ramp/frequency sweeps, creep, stress relaxation, etc. have been conducted using high burning rate composite propellant (burn rate ~20 mm/s at 7,000 kPa), in order to determine the precise effects of such parameters on the results obtained. The evaluated data revealed that as the temperature increases the storage modulus, loss modulus, and tan delta curves with respect to the frequency shift towards the lower side. Moreover, there is equivalency between the increase in the temperature and the decrease in the frequency, which can be used for the time-temperature superposition principles. Further, in transient tests, the relaxation modulus has been found to decrease when increasing strain levels in the given time range. Also, relaxation modulus versus time curves were found to shift towards the lower side with increasing temperature while creep compliance decreases with the increase in stress and decrease in temperature. The glass transition value of the composite propellant increases when there is an increase in the heating rate.

7 citations

Journal ArticleDOI
TL;DR: In this article, an improved technique for measuring the burning rate of experimental propellants is described by using a thick ¼-in. i.d. Lucite cylinder to hold the propellant grain, none of the usual inhibition problems are encountered.
Abstract: An improved technique for measuring the burning rate of experimental propellants is described. By using a thick ¼‐in. i.d. Lucite cylinder to hold the propellant grain, none of the usual inhibition problems are encountered. In addition, since the Lucite does not char on burning, the technique is ideally suited for high speed window bomb photography. Although this technique was developed for the measurement of the burning rate of solid propellants, also liquids, pastes, gels—hygroscopic materials—can all be handled with equal facility.

6 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202310
202220
202116
202015
201918
201811