Elements of modelling the use of particles in solid-propellant rocket motors

Important elements of the framework for numerically evaluating the usage of reactive aluminum particles in solid-propellant rocket motors are brought forward, and where possible, predicted model results are correlated to established experimental observations. A principal purpose in using inert or reactive particles is for the suppression of axial pressure wave development in the motor. In this study, a primary focus is placed on evaluating the qualitative trends associated with the time-dependent reduction in size of the reactive aluminum particles as they move downstream in the central internal flow. To narrow the scope of this preliminary study, the reactive particle size regression is stipulated to occur at a designated uniform rate for a given simulated firing. Individual transient internal ballistic simulation runs for a reference composite-propellant cylindrical-grain motor show the evolution of the axial pressure wave for a given initiating pressure disturbance, and for particle loading, initial pa...

[1]  Kirk W. Dotson,et al.  Interaction Between Solid Rocket Motor Internal Flow and Structure During Flight , 2007 .

[2]  Fred Blomshield,et al.  Historical perspective of combustion instability in motors - Case studies , 2001 .

[3]  S. Temkin,et al.  Measurements of particulate acoustic attenuation , 1964 .

[4]  Triggering Axial Instabilities in Solid Rockets: Numerical Predictions, , 1973 .

[5]  R. H. Woodward Waesche.  Mechanisms and Methods of Suppression of Combustion Instability by Metallic Additives , 1999 .

[6]  E. W. Price.  Solid Rocket Combustion Instability—An American Historical Account , 2008 .

[7]  Joseph D. Baum,et al.  Modeling of nonlinear longitudinal instability in solid rocket motors , 1986 .

[8]  R GreatrixD.  Parametric analysis of combined acceleration effects on solid-propellant combustion. , 1994 .

[9]  David R. Greatrix.  Dual Particle Loading for Solid Rocket Instability Symptom Suppression , 2011 .

[10]  H. B. Mathes,et al.  Nonlinear Stability Testing of Full-Scale Tactical Motors , 1997 .

[11]  David R. Greatrix.  Inert Particles for Axial-Combustion-Instability Suppression in a Solid Rocket Motor , 2008 .

[12]  H. Krier,et al.  Prediction of the Effects of Acceleration on the Burning of AP/HTPB Solid Propellants , 2001 .

[13]  M. Forde.  Quasi-one-dimensional gas/particle nozzle flows with shock , 1986 .

[14]  Vigor Yang,et al.  Prediction of the stability of unsteady motions in solid-propellant rocket motors , 1992 .

[15]  David R. Greatrix.  Numerical Evaluation of the Use of Aluminum Particles for Enhancing Solid Rocket Motor Combustion Stability , 2015 .

[16]  H. B. Mathes,et al.  Stability Testing of Full-Scale Tactical Motors , 1997 .

[17]  W. G. Brownlee.  Nonlinear axial combustion instability in solid propellant motors , 1964 .

[19]  J. J. Gottlieb,et al.  Numerical Study of the Effects of Longitudinal Acceleration on Solid Rocket Motor Internal Ballistics , 1992 .

[20]  J. Majdalani,et al.  Acoustic Instability of the Slab Rocket Motor , 2004 .

[21]  David R. Greatrix,et al.  Star-grain rocket motor – nonsteady internal ballistics , 2004 .

[22]  Kamran Behdinan,et al.  Structural Oscillation Considerations for Solid Rocket Internal Ballistics Modeling , 2000 .

[23]  L. Luca,et al.  Technologies and Techniques for Instability Suppression in Motors , 1992 .

[24]  David R. Greatrix,et al.  Model for Prediction of Negative and Positive Erosive Burning , 2006 .

[25]  Kamran Behdinan,et al.  Internal chamber modeling of a solid rocket motor: Effects of coupled structural and acoustic oscillations on combustion , 2008 .

[26]  David R. Greatrix.  Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations , 2008 .