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.

Catalytic behavior in composite solid propellant combustion

Abstract: : The report describes experiments and theoretical analysis concerned with sandwich combustion. The ingredients used in the experiment are compacted polycrystalline ammonium perchlorate as the oxidizer, hydroxyl terminated polybutadiene as the binder and four catalysts: Harshaw catalyst CU-0202, Fe2O3, ferrocene, and iron blue. The pressure range studied is 600-2000 psia. The experimental techniques used are cinephotomacrography for sample observation during burning and burn rate determination, scanning electron microscopy for observation of quenched samples, and electron microprobing for an exploratory study of surface compositon. A theoretical solution to a simple sandwich deflagration problem is attained. The probable sites of catalytic activity are determined, results are compared with actual propellant experience, and the analysis is used to clarify experimental results. (Author)

Propellant burn rate characteristics in closed bomb ignited with plasma

Abstract: The interaction of plasma with propellant is the pivotal factor that influences energy efficiency of electrothermal chemical launch. An experimental system of closed chambeer with plasma igniter is developed. The characteristics of burn rate of single base propellant with the presence of plasma are investigated. Experimental results show that plasma ignition reduces propellant ignition delay markedly. The minimal threshold of ignition energy density is less than 0.05 kJ/g. The propellant exhibits enhanced burn rate with the increase of input electric energy. The enhancement of burn rate of single base propellant is only obvious in the period of electric pulse injection. When high electric energy injects into the chamber, there also exists tendency of regression rate enhancement after the plasma injection.

Transverse thrust flight control arrangement

Abstract: A flight control arrangement for four-quadrant final-phase guidance control of a missile using transverse thrust jets 10 mounted so flow from a dry-fuelled gas generator 13 through the jets 10 can be adjusted by a common final control element 12, 30 rotated to an angular position by actuator 16 and moved linearly to an axial position by actuator 17. In a first embodiment, the common final control element 12 obstructs the flow to three jets 10 while in a second embodiment, three valve elements 38 may be actuated to restrict the flow through three jets 10, in both embodiments this then causes transverse thrust through the forth jet and a higher burn rate in the gas generator 13 due to increased pressure. When no direction change is required, the final control element 12, 30 is moved linearly to allow flow through all thrust jets 10, the lower pressure in the gas generator 13 thus induced causing a low burn rate of fuel.

Development of a miniature solid propellant rocket motor for use in plume simulation studies

Abstract: A miniature solid propellant rocket motor has been developed to be used in a program to determine those parameters which must be duplicated in a cold gas flow to produce aerodynamic effects on an experimental model similar to those produced by hot, particle-laden exhaust plumes. Phenomena encountered during the testing of the miniature solid propellant motors included erosive propellant burning caused by high flow velocities parallel to the propellant surface, regressive propellant burning as a result of exposed propellant edges, the deposition of aluminum oxide on the nozzle surfaces sufficient to cause aerodynamic nozzle throat geometry changes, and thermal erosion of the nozzle throat at high chamber pressures. A series of tests was conducted to establish the stability of the rocket chamber pressure and the repeatibility of test conditions. Data are presented which define the tests selected to represent the final test matrix. Qualitative observations are also presented concerning the phenomena experienced based on the results of a large number or rocket tests not directly applicable to the final test matrix.