Model-based diagnostics and prognostics for solid rocket motors

Progress in development of the physics model based diagnostic and prognostic system for solid rocket motors (SRMs) of the new generation of the crew exploration vehicles is reported. The performance model (PM) of the internal ballistics of large segmented SRMs in the regime of steady burning in the presence of the case breach fault is presented. This model takes into account propellant regression, erosive burning, surface friction, nozzle ablation, and also processes describing specific faults. The performance of the model is verified by comparison with the results of 2D high-fidelity simulations. Importantly, the PM allows for the simulation of a number of faults observed earlier in large segmented SRMs including nozzle blocking, bore choking, propellant debonding, and case breach fault. The developed model of the case breach allows calculations of the side thrust at a given location along the rocket axis. The model takes into account the effect of mass addition along the rocket axis, erosive burning, and surface friction. In this paper we illustrate to use the developed PM for analysis of the case breach fault. The model of the internal ballistics is combined with the model of dynamics of burning-through case at a given location along the motor axis. The case breach fault diagnostic is developed via inference of the case breach area in a quasi-steady approximation. Prognosis of the case breach fault is achieved using a scaling algorithm. The diagnostic and prognostic algorithms were verified using the results of a ground firing test of a sub-scale motor.

[1]  Michael P. Iverson,et al.  Automated Fluid-Structure Interaction Analysis , 2003 .

[2]  D. R. Bartz.  Turbulent Boundary-Layer Heat Transfer from Rapidly Accelerating Flow of Rocket Combustion Gases and of Heated Air , 1965 .

[3]  Mark Salita.  Modern SRM ignition transient modeling. I - Introduction and physical models , 2001 .

[4]  Fred E. C. Culick,et al.  Combustion Instabilities in Propulsion Systems , 1996 .

[5]  Mark Salita.  Verification of spatial and temporal pressure distributions in segmented solid rocket motors , 1989 .

[6]  J. Santiago,et al.  An experimental study of the velocity field of a transverse jet injected into a supersonic crossflow , 1995 .

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

[8]  Dogan A. Timucin,et al.  In-Flight Failure Decision and Prognostic for the Solid Rocket Buster , 2007 .

[9]  Gary A. Flandro,et al.  Nonlinear Rocket Motor Stability Prediction: Limit Amplitude, Triggering, and Mean Pressure Shift , 2007 .

[10]  Michael T. Heath,et al.  Advanced Simulation of Solid Propellant Rockets from First Principles , 2005 .

[11]  Sun Hwan Lee,et al.  Bayesian Framework for In-Flight SRM Data Management and Decision Support , 2007, 2007 IEEE Aerospace Conference.

[12]  C. R. Peterson,et al.  Mechanics And Thermodynamics Of Propulsion , 1965 .

[13]  Dmitry G. Luchinsky,et al.  Data management and decision support for the in-flight SRM , 2007 .

[14]  S. Uckun,et al.  Model Based IVHM System for the Solid Rocket Booster , 2008, 2008 IEEE Aerospace Conference.

[15]  Y. Jaluria,et al.  An Introduction to Heat Transfer , 1950 .

[16]  D. Rubenstein,et al.  Introduction to heat transfer , 2022 .

[17]  Joshua McMillin,et al.  Fault diagnostics and prognostics for large segmented SRMs , 2009, 2009 IEEE Aerospace conference.

[18]  W. Wilson,et al.  Titan IV SRMU PQM-1 overview , 1992 .

[19]  Dogan A. Timucin,et al.  Development of an On-Board Failure Diagnostics and Prognostics System for Solid Rocket Booster , 2008 .

[20]  L. Margolin,et al.  On balanced approximations for time integration of multiple time scale systems , 2003 .

[21]  D. Scott Stewart,et al.  Multiscale modeling of solid rocket motors: Computational aerodynamics methods for quasi-steady burning , 2006 .

[22]  Mark Salita,et al.  Closed-form analytical solutions for fluid mechanical, thermochemical, and thermal processes in solid rocket motors , 1998 .