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 article, an experimental study of solid propellant extinguishment by rapid depressurization was conducted, which indicated that combustion extinguishment requirements are determined by the binder type, percentage of ammonium perchlorate oxidizer, motor geometry, and exhaust pressure level.
Abstract: Results are presented from an experimental study of solid propellant extinguishment by rapid depressurization. Systematic variations in propellant binder, oxidizer loading level, burning rate catalyst, metal loading, and exhaust pressure level were studied. The effects of motor configuration on extinguishment and reignition are discussed. Results indicate that combustion extinguishment requirements are determined by the binder type, percentage of ammonium perchlorate oxidizer, motor geometry, and exhaust pressure level as well as the pressure and depressurization rate. The von Elbe model with a coefficient of one provides a rough correlation of extinguishment requirements.
12 citations
Patent•
17 Jul 1995TL;DR: In this paper, a bipropellant rocket engine has a vapor pressure sufficiently high under prevailing condition to generate vapor at a pressure sufficient high to pressurize both the volatile component and the second rocket propellant and provide the sole means for forcing the two rocket propellants from their storage to the rocket engine.
Abstract: One of the propellants used in a bipropellant rocket engine has a vapor pressure sufficiently high under prevailing condition to generate vapor at a pressure sufficiently high to pressurize both the volatile component and the second rocket propellant and provide substantially the sole means for forcing the two rocket propellants from their storage to the rocket engine. In the preferred arrangement, both the components will be stored within the same pressure vessel, one preferably being contained within an expandable/collapsible bladder.
12 citations
01 Sep 1997
TL;DR: In this paper, the concept of the propelling charge temperature coefficient and its impact on gun performance is explored, with special emphasis on the utilization of electrothermal chemical (ETC) concepts.
Abstract: : The concept of the propelling charge temperature coefficient and its impact on gun performance is explored. Ballistic factors, in addition to the propellant burn rate dependence on initial temperature that often increases the magnitude of the propelling charge temperature coefficient, are identified and discussed. Techniques for moderating the effects of the propelling charge temperature coefficient are presented, with special emphasis on the utilization of electrothermal- chemical (ETC) concepts.
12 citations
01 Apr 1990
TL;DR: In this paper, an engineering model has been developed to compute the flight performance of the M864 base burn projectile, including the coupled performance of a gas generator, effects of injected mass flow on the aerodynamics, and a modified point mass trajectory simulation.
Abstract: : An engineering model has been developed to compute the flight performance of the M864 base burn projectile. This model includes the coupled performance of the gas generator, effects of injected mass flow on the aerodynamics, and a modified point mass trajectory simulation. The gas generator model is based on measured burn rates and basic fluid dynamics. The discharge rate of the generator is calibrated against laboratory experiments. Effects of spin on burn rate are deduced from comparison of analysis with spin fixture tests. Linear and first order nonlinear effects of mass injection on base pressure are the basis for evaluation of base drag. Navier-Stokes solutions near the base with air injection provides essential data. Correlation equations predict base pressure as a function of Mach number, injection rate, and propellant gas temperature. Temperature effects on base pressure are a unique feature of the analysis. Keywords: Injection of combustion products, Base burn, Base bleed, Spin, Trajectory, Navier-Stokes computations, Solid propellant.
12 citations
Patent•
29 Jul 1999
TL;DR: In this article, an electric energy supply and control device connected to the propellant was used for igniting a large-scale, high-energy-consuming, large-capacity projectile.
Abstract: A propellant system for launching a large-caliber projectile includes a propellant having at least three partial charges. The first partial charge is adapted to acceleration requirements of the projectile; the second partial charge has a higher combustion velocity than that of the first partial charge; and the third partial charge has a lower combustion velocity than that of the first partial charge. The propellant system further includes an electric energy supply and control device connected to the propellant for igniting the propellant. The electric energy supply and control device has a plasma generator for affecting a combustion behavior of the propellant such as to obtain for said first partial charge, after ignition of the propellant, a maximum gas pressure level of always the same magnitude independently from an initial propellant temperature, and to obtain, for the third partial charge, a conversion such as to prolong the maximum gas pressure level in a predeterminable manner.
12 citations