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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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Journal ArticleDOI
TL;DR: In this article , the effect of initial grain temperature on the combustion response of composite solid propellants (AP/HTPB/RDX/Al) is experimentally investigated using a T-burner.
Abstract: The effect of initial grain temperature on the combustion response of composite solid propellants (AP/HTPB/RDX/Al) is experimentally investigated using a T-burner. Tests were conducted at different frequencies ranging from 200–400 Hz and at different pressures of 1–8 MPa at different initial propellant temperatures using a novel method (303 K, 243 K and 343 K) for two industrial-grade propellants, propellant-A and propellant-B. The test results revealed that the hot and cold temperatures increase the response. The combustion responses of the propellant-B are lower than propellant-A. Pulsed tests are conducted when the propellant showed low or negative response. This work highlights that the initial grain temperature is a crucial factor in determining the stability of solid rocket motors. The negative response compels us to further investigate toward a better understanding about the unsteady combustion behavior since there is no model available which could predict negative responses as of today.

2 citations

01 Jan 1966
TL;DR: In this paper, a nonlinear analysis of transverse mode instability in a solid pro- pellant rocket geometry indicated the relative combustion stability based on three para- metric groupings: burning rate, wall-loss, and viscous-dissipation parameters.
Abstract: SUMMARY OF RESULTS A one-dimensional, nonlinear analysis of transverse mode instability in a solid pro- pellant rocket geometry indicated the relative combustion stability based on three para- metric groupings: burning rate, wall-loss, and viscous-dissipation parameters, of which only the burning rate parameter appeared to be significant in the one-dimensional model with a nonvibrating solid phase. The results of the analysis, presented as the minimum pressure amplitude required to incite instability as a function of the burning rate parameter, showed that erosive burning was an important factor in determining sta- bility. With only a 10-percent contribution to the burning rate due to erosion, the sta- bility boundary was significantly affected so as to reduce the stable region of operation. A two-fold increase in the pressure exponent in the burning rate law also showed a de- crease in the stable operating regime. This effect was not as pronounced as the erosive effect. Increasing the

2 citations

Proceedings ArticleDOI
08 Jul 1985
TL;DR: In this paper, it was shown that coning of the burning propellant surface in end-burning rocket motors arises from an increased burn rate at the side walls of the propellant grain.
Abstract: Coning of the burning propellant surface in end-burning rocket motors arises from an increased burn rate at the side walls of the propellant grain. Causes of this increased burn rate have been investigated, mainly through the use of small scale motor firings. The nature of the propellant inhibitor material is shown to be important, and various possible mechanisms are examined. Mechanisms identified by other workers in previous studies were found to be not involved. Strain in the propellant has been shown to produce coning. Considerable evidence was found that coning also results from migration of curing agent while the propellant is curing during manufacture although the precise mechanism involved has not been established.

2 citations


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