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.

Pressure level control system for a solid propellant rocket motor

Abstract: A system for controlling the operating pressure and thrust of a solid propellant rocket motor which includes a propellant cutter that extends through the burning surface of the solid propellant to increase on command the burning surface area and thereby increase the burning rate of the solid propellant.

An optical bomb study of the combustion of solid propellants in high acceleration fields

Abstract: : Under the subject program, an experimental study of the effects of acceleration fields on the burning rate of solid propellant grains is being conducted. The general plan is to investigate a variety of formulations over a range of pressures and acceleration loadings, the results to be used to evaluate theoretical models of the process or to form the basis for improved models. In this report the results for two formulations are presented. The acceleration vector in these tests, produced by spinning a disc-shaped grain, was directed normal to and away from the surface. For one of the propellants, which contained only CTPB binder and AP, the burning rate decreased approximately 20 percent at g-loadings of 500. At higher accelerations levels up to 1600 g's an additional 10 percent decrease appeared to occur, although the changes were too small to be determined with certainty. For a second propellant, similar to the first but containing 12 percent powdered aluminum, the change in burning rate if it existed at all was too small for any consistent trend to be detected at g- levels up to 2000. For both propellants the effects were independent of pressure up to 50 atm.

Effect of radiant energy on the burning rate of a composite solid propellant

Abstract: This paper describes the measured effect of radiant energy flux on the atmospheric pressure burning rate of a solid propellant. It was concluded that the effect is negligible except when the propellant burning rate is very low as, for example, during the quench of a controllable motor. Also, from the experimental data, it was calculated that the PBAN-AP propellant had an apparent surface temperature of 560 °C and an apparent exothermic solid decomposition that liberated 130 cal/g.

Launching Process for Variable-Mass Rockets by Series Solution

Abstract: In this study, the mathematical investigation of rocket motion path is presented using analytical and numerical methods . Differential transform method and fourth-order Runge-Kutta method are used for solving the current problem. A parametric study is performed which includes the effect of exhaust velocity (Ce), burn rate (BR) of fuel and diameter of cylindrical rocket (d) on the motion of a sample rocket. Also a realistic comparison of four on-line and active rockets is presented and the result is discussed. The main results indicate that the present analytical technique has high accuracy in comparison with the numerical solution. It is illustrated that the rocket velocity and altitude are increased with increasing the Ce and BR and decreased with increasing the rocket diameter. Finally it is concluded that Mu-3S-II rocket reaches to higher velocities and altitudes faster in comparison with the other introduced rockets.