scispace - formally typeset
Search or ask a question
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.


Papers
More filters
Journal ArticleDOI
TL;DR: In this article, the authors describe the combustion properties of the amino-substituted guanidinium 4,4',5,5'5'tetranitro-2,2'-biimidazolate (N4BIM) series.
Abstract: This paper describes the combustion properties of the amino-substituted guanidinium 4,4’,5,5’-tetranitro-2,2’-biimidazolate (N4BIM) series, including the bis-mono, di and triaminoguanidinium salts. These salts are of interest as propellant ingredient additives, and in particular, the bis-triaminoguanidinium salt of N4BIM displays excellent burn rate and combustion behavior. Our combustion studies have shown that TAGN4-BIM displays a fast burning rate and has the lowest pressure dependence exponent yet measured for a triaminoguanidinium salt.

6 citations

Proceedings ArticleDOI
08 Jan 2007
TL;DR: In this article, the effects of rapid chamber pressure change on the propellant and motor transient behavior have been studied, and prediction of the level of pressurization rate has been achieved.
Abstract: Solid rocket performance during rapid pressure excursions differs greatly from predictions based on steady state burning rate data. Rapid pressurization following a chamber filling interval produces indicated burning rate overshoots. Transient internal ballistics of a solid propellant rocket motor during rapid pressurization part of chamber filling phase has been considered in this work. Quasi one-dimensional unsteady Euler equations with a transient propellant burning model that accounts for the effects of time rate of change of the chamber pressure on the burning rate have been used to simulate the internal ballistics of rocket motors. The compressible convective flow solver used in this study is based on Roe’s scheme. The effects of rapid chamber pressure change on the propellant and motor transient behavior have been studied. Furthermore, prediction of the level of pressurization rate has been achieved.

6 citations

Patent
21 Dec 1973
TL;DR: In this article, a solid strand burn rate analyzer for measuring solid propellant burn rates, sensing acoustic signals created by thermal fracture or deflagration of the solid oxidizer utilizing a piezoelectric pick-up transducer mounted on the propellant case, a system of signal amplification, a wave form distribution converter and a X, Y strip chart for recording test results.
Abstract: In a solid strand burn rate analyzer for measuring solid propellant burn rates, sensing acoustic signals created by thermal fracture or deflagration of the solid oxidizer utilizing a piezoelectric pick-up transducer mounted on the propellant case, a system of signal amplification, a wave form distribution converter and a X, Y strip chart for recording test results.

5 citations

Journal ArticleDOI
TL;DR: In this article, a technique for measuring the burning rate of solid propellants inside rocket motors is described, which involves measuring the time interval between successive interruptions of the wires caused by the burning surface of the propellant and determining the distance between these wires from an x-ray picture of the specimen prior to placing it in the rocket motor and prior to burning.
Abstract: A technique for measuring the burning rate of solid propellants inside rocket motors is described. The technique consists of embedding wires in a specimen of solid propellant and then casting or bonding the specimen to the propellant in the rocket motor. The wires employed were made of 0.0045‐in.‐diam lead‐antimony which has a low melting point, a low thermal diffusivity, and a moderate electrical resistance. The technique involves measuring the time interval between successive interruptions of the wires caused by the burning surface of the propellant. The distance between these wires is determined from an x‐ray picture of the specimen prior to placing it in the rocket motor and prior to burning. Thus, with both the distance burned and the burning time known, the burning rate can be determined. When this technique is properly employed, it does not influence the burning rate, nor does it affect the flow field. Furthermore, it can be employed to study the influence on the burning rate of the port shape of a propellant grain inside a rocket motor, since the small specimen of solid propellant containing the resistance‐wire network can be cast into the grain of a solid rocket at any position in the port. This will permit measuring burning rates at selected locations and times in the rocket motor.

5 citations


Network Information
Related Topics (5)
Combustion
172.3K papers, 1.9M citations
86% related
Internal combustion engine
130.5K papers, 1M citations
72% related
Heat transfer
181.7K papers, 2.9M citations
71% related
Reynolds number
68.4K papers, 1.6M citations
71% related
Laminar flow
56K papers, 1.2M citations
70% related
Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202310
202220
202116
202015
201918
201811