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.

Combustion Characteristics of GIBR Layered Square Flake Gun Propellant

Abstract: In order to study the progressivity of GIBR(gradual increasing burning rate) layered propellant with square flake shape,the physical model about the combustion process was put forward,and the shape function was calculated according to the physical model and the parallel layer burning law.The change of Ψ,σ with Z was calculated and analyzed at different parameters such as X1,K and β.The result by theoretic study was validated by interrupted burning method both in gun chamber and closed bomb.The results show that the gas generating rate of the layered propellant can be controlled by adjusting the burning rate,dimension and thickness ratio of outer-layer to innerlayer.The results also show that the factual combustion law and theoretic model are consistent and the combustion process approximately reflects the parallel layer burning law.

Mesoporous iron oxide energetic composites with slow burn rate, sustained pressure and reduced ESD sensitivity for propellant applications

Abstract: .................................................................................vi LIST OF FIGURES.......................................................................ix LIST OF TABLES........................................................................xi CHAPTER

The effect of a shock wave on a burning solid propellant

Abstract: A burning propellant at the end of a shock tube in the quiescent-gas zone sees a shock wave primarily as a pressure step. The burning rate is assumed to be surface-temperature-dependent. The time-dependent temperature distribution in the propellant is determined numerically. Burning-rate–time plots are presented for the variation of the important parameters. The effect of initial burning rate is discussed and it is suggested that this effect may bound the allowable frequency regions in solid-propellant combustion instability.

A Solid Propellant Charge Design with Negative Effective Pressure Exponent Using Forced Cone Burning

Abstract: : A novel method of making a solid propellant rocket motor or gas generator charge with a negative effective burning rate pressure exponent (negative drb/dP) is presented. The negative exponent characteristic can be obtained independently of burning rate and other bulk propellant properties (specific impulse, flame temperature, signature, mechanical properties, etc) which can be chosen as required. The charge is constructed with a core, (or several cores), of propellant with an intrinsically negative pressure exponent with the bulk of the charge made up of any propellant with a lower burning rate than the core propellant over the pressure range of interest. The core propellant burning rate range can be adjusted to give the desired value by a method of burning rate acceleration. Suitable core materials and burning rate acceleration methods are reported, and the use of such a charge in a rocket motor or gas generator with a variable area nozzle to give controllable thrust is discussed.