Advanced Simulation of Solid Propellant Rockets from First Principles

Dick, William A.; Heath, Michael T.; Fiedler, Robert; Brandyberry, Mark

doi:10.2514/6.2005-3990

Cited by 14 publications

(5 citation statements)

References 12 publications

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“…The later objective can only be achieved by incorporating expert knowledge about characteristic dynamical features of various off-nominal regimes and by utilizing deep physical understanding of the underlying physical processes. Examples of the most probable faults in SRBs include: (i) combustion instabilities [1][2][3] , (ii) bore chocking [4][5][6] , and (iii) case breach [7][8][9] . Clearly the development of the FD&P that incorporates physics models of the faults has to verified and validated in a multi-stage procedure involving highfidelity modeling, ground and flying tests.…”

Section: Imentioning

confidence: 99%

Development of an On-Board Failure Diagnostics and Prognostics System for Solid Rocket Booster

Smelyanskiy¹,

Luchinsky²,

Osipov³

et al. 2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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We develop a case breach model for the on-board fault diagnostics and prognostics system for subscale solid-rocket boosters (SRBs). The model development was motivated by recent ground firing tests, in which a deviation of measured time-traces from the predicted time-series was observed. A modified model takes into account the nozzle ablation, including the effect of roughness of the nozzle surface, the geometry of the fault, and erosion and burning of the walls of the hole in the metal case. The derived low-dimensional performance model (LDPM) of the fault can reproduce the observed time-series data very well. To verify the performance of the LDPM we build a FLUENT model of the case breach fault and demonstrate a good agreement between theoretical predictions based on the analytical solution of the model equations and the results of the FLUENT simulations. We then incorporate the derived LDPM into an inferential Bayesian framework and verify performance of the Bayesian algorithm for the diagnostics and prognostics of the case breach fault. It is shown that the obtained LDPM allows one to track parameters of the SRB during the flight in real time, to diagnose case breach fault, and to predict its values in the future. The application of the method to fault diagnostics and prognostics (FD&P) of other SRB faults modes is discussed.

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Section: Imentioning

confidence: 99%

Development of an On-Board Failure Diagnostics and Prognostics System for Solid Rocket Booster

Smelyanskiy¹,

Luchinsky²,

Osipov³

et al. 2008

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Here it is sufficient to note that the fastest physical time scale is of the order of 10 À6 s while the slowest physical time scale is the time to burn-out of the solid propellant, which is about 120 s for the RSRM. The wide range of length and time scales makes detailed first-principle simulations of SRMs from ignition to burn-out, such as those undertaken at the Center for Simulation of Advanced Rockets (CSAR, see Dick et al [4]), very challenging. In such simulations, evolution equations are solved for the mass, momentum, and energy of the mixture of gaseous species and aluminum-oxide smoke and for the aluminum droplet position, mass, momentum, energy, and composition (see, e.g., Najjar et al [13] and Haselbacher and Najjar [8]).…”

Section: Introductionmentioning

confidence: 99%

Slow-time acceleration for modeling multiple-time-scale problems

Haselbacher

Najjar

Massa

et al. 2010

Journal of Computational Physics

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“…Indeed, theoretical analysis shows that many fault modes leading to the SRBs failures [5]- [7], including combustion instabilities [8]- [10], bore choking [11]- [13], and case breach [5], [14], have unique dynamical features in the time-traces of pressure and thrust. The corresponding expert knowledge can be incorporated into on-board FD&P within the novel Bayesian inferential framework [1]- [4] allowing for faster and more reliable identification of the nominal and off-nominal regimes of SRB operation in real time.…”

Section: Introductionmentioning

confidence: 99%

Model Based IVHM System for the Solid Rocket Booster

Luchinsky

Осипов

Smelyanskiy

et al. 2008

2008 IEEE Aerospace Conference

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We report progress in the development of a model-based hybrid probabilistic approach to an on-board IVHM for solid rocket boosters (SRBs) that can accommodate the abrupt changes of the model parameters in various nonlinear dynamical off-nominal regimes. The work is related to the ORION mission program. Specifically, a case breach fault for SRBs is considered that takes into account burning a hole through the rocket case, as well as ablation of the nozzle throat under the action of hot gas flow. A high-fidelity model (HFM) of the fault is developed in FLUENT in cylindrical symmetry. The results of the FLUENT simulations are shown to be in good agreement with quasi-stationary approximation and analytical solution of a system of one-dimensional partial differential equations (PDEs) for the gas flow in the combustion chamber and in the hole through the rocket case.The low-dimensional performance model (LDPM) of the fault is derived by integrating a set of one-dimensional PDEs along the axis of the rocket. The LDPM is used to build a model-based fault diagnostic and prognostic (FD&P) algorithm for the case breach fault. In particular, two algorithms are introduced. The first algorithm is based on the self-consistent algorithm that solves the LDPM in a quasi-adiabatic approximation, when the pressure and density follow adiabatically dynamics of the propellant burning, melting and burning of the metal case, ablation and erosion of nozzle and insulator. The second algorithm is based on the dynamical inference method [1]-[3] of the system of stochastic differential equations of the LDPM.The parameters of the HFM model and of the LDPM are tuned to reproduce the results of recent experiments of the rocket firing with the case breach fault in the forward closure. The FD&P is then applied to illustrate real-time diagnostics of the model parameters and prognostics of the SRB internal ballistics. All the algorithms discussed in this paper were verified using experimental data as will be discussed elsewhere.The accuracy of the algorithm and the possibility of its application to FD&P for other SRB fault modes are discussed.

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Advanced Simulation of Solid Propellant Rockets from First Principles

Cited by 14 publications

References 12 publications

Development of an On-Board Failure Diagnostics and Prognostics System for Solid Rocket Booster

Development of an On-Board Failure Diagnostics and Prognostics System for Solid Rocket Booster

Slow-time acceleration for modeling multiple-time-scale problems

Model Based IVHM System for the Solid Rocket Booster

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