Simulating solid propellant rocket motors requires solving an extremely complex, fully coupled multidisciplinary physics problem that spans a wide range of length and time scales. We have taken a staged approach in developing an integrated whole-system rocket simulation package, beginning with relatively simple physical models, geometries, and coupling in our first-generation code (GEN1), and p...

The contribution made by orbiting solid rocket motors (SRMs) to the orbital debris environment is both potentially significant and insufficiently studied. A combination of rocket motor design and the mechanisms of the combustion process can lead to the emission of sufficiently large and numerous by-products to warrant assessment of their contribution to the orbital debris environment. These par...

​ *Corresponding author's address: Physics and Astronomy, Brigham Young University, N283 ESC, Provo, UT 84602, [email protected] Generalized Burgers equation-based predictions of noise propagation are compared with measurements from a static, horizontally-fired solid rocket motor over a range of 76-1220 m during an 80 s burn time. The modeling suggests the nature of the geometric spreading betw...

F. Doisneau1, A. Sibra2, J. Dupays3, A. Murrone4, F. Laurent5, and M. Massot6 DEFA, Département d’Énergétique Fondamentale et Appliquée, ONERA 91120 Palaiseau FRANCE CNRS, UPR 288 “Laboratoire d’Énergétique Moléculaire et Macroscopique, Combustion” ECP, Ecole Centrale Paris, Grande Voie des Vignes 92295 Châtenay-Malabry FRANCE FM, Fédédration de Mathématiques de l’Ecole Centrale Paris, FR CNRS ...

Unlike a liquid propellant stage which allows stopping the thrust at any time during the flight, when a solid rocket motor is used on a Launcher upper stage, the impact zone can be very large due to the atmospheric and propulsive dispersions on the current stage and the previous stages. In this case a stage impact control is required. In this study, an active impact control strategy is presente...

A comprehensive numerical analysis has been conducted to study the combustion of a double-base homogeneous propellant in a rocket motor. Emphasis was placed on the motor internal flow development and its influence on propellant combustion. The formulation is based on the Favre-averaged, filtered equations for the conservation laws and takes into account finite-rate chemical kinetics and variabl...

Simulating solid propellant rocket motors requires solving an extremely complex, fully coupled multidisciplinary physics problem that spans a wide range of length and time scales. We have taken a staged approach in developing an integrated whole-system rocket simulation package, beginning with relatively simple physical models, geometries, and coupling in our first-generation code (GEN1), and p...

Rockets are the only direct anthropogenic emission sources into the upper atmosphere. Gaseous rocket emissions include CO, N2, H2, H2O, and CO2, while solid rocket motors (SRM) additionally inject signi¦cant amounts of aluminum oxide (Al2O3) particles and gaseous chlorine species into the atmosphere. These emissions strongly perturb local atmospheric trace gas and aerosol distributions. Here, t...

In reality all the engineering products are likely to deviate from their expected performance due to the presence of variations. The variations can cause any product optimization to easily fall into sub-optimal regime. In present adopted methodology, the robust design optimization (RDO) of the objective function makes performance insensitive to the variations/uncertainties. A hybrid optimizatio...