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Fault diagnostics and prognostics for large segmented SRMs

Research output: Contribution in Book/Report/Proceedings - With ISBN/ISSN › Conference contribution/Paper › peer-review

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Fault diagnostics and prognostics for large segmented SRMs. / Luchinsky, Dmitry G.; Osipov, Viatcheslav V.; Smelyanskiy, Vadim N. et al.
2009 IEEE Aerospace Conference. 2009. 4839622 (IEEE Aerospace Conference Proceedings).

Research output: Contribution in Book/Report/Proceedings - With ISBN/ISSN › Conference contribution/Paper › peer-review

Harvard

Luchinsky, DG, Osipov, VV, Smelyanskiy, VN, Timucin, DA, Uckun, S, Hayashida, B, Watson, M, McMillin, J, Shook, D, Johnson, M & Hyde, S 2009, Fault diagnostics and prognostics for large segmented SRMs. in 2009 IEEE Aerospace Conference., 4839622, IEEE Aerospace Conference Proceedings, 2009 IEEE Aerospace Conference, Big Sky, MT, United States, 7/03/09. https://doi.org/10.1109/AERO.2009.4839622

APA

Luchinsky, D. G., Osipov, V. V., Smelyanskiy, V. N., Timucin, D. A., Uckun, S., Hayashida, B., Watson, M., McMillin, J., Shook, D., Johnson, M., & Hyde, S. (2009). Fault diagnostics and prognostics for large segmented SRMs. In 2009 IEEE Aerospace Conference Article 4839622 (IEEE Aerospace Conference Proceedings). https://doi.org/10.1109/AERO.2009.4839622

Vancouver

Luchinsky DG, Osipov VV, Smelyanskiy VN, Timucin DA, Uckun S, Hayashida B et al. Fault diagnostics and prognostics for large segmented SRMs. In 2009 IEEE Aerospace Conference. 2009. 4839622. (IEEE Aerospace Conference Proceedings). doi: 10.1109/AERO.2009.4839622

Author

Luchinsky, Dmitry G. ; Osipov, Viatcheslav V. ; Smelyanskiy, Vadim N. et al. / Fault diagnostics and prognostics for large segmented SRMs. 2009 IEEE Aerospace Conference. 2009. (IEEE Aerospace Conference Proceedings).

Bibtex

@inproceedings{8d06bc69148a4a7588e664dd61d7241f,
title = "Fault diagnostics and prognostics for large segmented SRMs",
abstract = "We report progress in development of the fault diagnostic and prognostic (FD&P) system for large segmented solid rocket motors (SRMs). The model includes the following main components: (i) 1D dynamical model of internal ballistics of SRMs; (ii) surface regression model for the propellant taking into account erosive burning; (iii) model of the propellant geometry; (iv) model of the nozzle ablation; (v) model of a hole burning through in the SRM steel case. The model is verified by comparison of the spatially resolved time traces of the flow parameters obtained in simulations with the results of the simulations obtained using high-fidelity 2D FLUENT model (developed by the third party). To develop FD&P system of a case breach fault for a large segmented rocket we notice [1] that the stationary zero-dimensional approximation for the nozzle stagnation pressure is surprisingly accurate even when stagnation pressure varies significantly in time during burning tail-off. This was also found to be true for the case breach fault [2]. These results allow us to use the FD&P developed in our earlier research [3]-[6] by substituting head stagnation pressure with nozzle stagnation pressure. The axial corrections to the value of the side thrust due to the mass addition are taken into account by solving a system of ODEs in spatial dimension.",
author = "Luchinsky, {Dmitry G.} and Osipov, {Viatcheslav V.} and Smelyanskiy, {Vadim N.} and Timucin, {Dogan A.} and Serdar Uckun and Ben Hayashida and Michael Watson and Joshua McMillin and David Shook and Mont Johnson and Scott Hyde",
year = "2009",
month = sep,
day = "21",
doi = "10.1109/AERO.2009.4839622",
language = "English",
isbn = "9781424426225",
series = "IEEE Aerospace Conference Proceedings",
booktitle = "2009 IEEE Aerospace Conference",
note = "2009 IEEE Aerospace Conference ; Conference date: 07-03-2009 Through 14-03-2009",

}

RIS

TY - GEN

T1 - Fault diagnostics and prognostics for large segmented SRMs

AU - Luchinsky, Dmitry G.

AU - Osipov, Viatcheslav V.

AU - Smelyanskiy, Vadim N.

AU - Timucin, Dogan A.

AU - Uckun, Serdar

AU - Hayashida, Ben

AU - Watson, Michael

AU - McMillin, Joshua

AU - Shook, David

AU - Johnson, Mont

AU - Hyde, Scott

PY - 2009/9/21

Y1 - 2009/9/21

N2 - We report progress in development of the fault diagnostic and prognostic (FD&P) system for large segmented solid rocket motors (SRMs). The model includes the following main components: (i) 1D dynamical model of internal ballistics of SRMs; (ii) surface regression model for the propellant taking into account erosive burning; (iii) model of the propellant geometry; (iv) model of the nozzle ablation; (v) model of a hole burning through in the SRM steel case. The model is verified by comparison of the spatially resolved time traces of the flow parameters obtained in simulations with the results of the simulations obtained using high-fidelity 2D FLUENT model (developed by the third party). To develop FD&P system of a case breach fault for a large segmented rocket we notice [1] that the stationary zero-dimensional approximation for the nozzle stagnation pressure is surprisingly accurate even when stagnation pressure varies significantly in time during burning tail-off. This was also found to be true for the case breach fault [2]. These results allow us to use the FD&P developed in our earlier research [3]-[6] by substituting head stagnation pressure with nozzle stagnation pressure. The axial corrections to the value of the side thrust due to the mass addition are taken into account by solving a system of ODEs in spatial dimension.

AB - We report progress in development of the fault diagnostic and prognostic (FD&P) system for large segmented solid rocket motors (SRMs). The model includes the following main components: (i) 1D dynamical model of internal ballistics of SRMs; (ii) surface regression model for the propellant taking into account erosive burning; (iii) model of the propellant geometry; (iv) model of the nozzle ablation; (v) model of a hole burning through in the SRM steel case. The model is verified by comparison of the spatially resolved time traces of the flow parameters obtained in simulations with the results of the simulations obtained using high-fidelity 2D FLUENT model (developed by the third party). To develop FD&P system of a case breach fault for a large segmented rocket we notice [1] that the stationary zero-dimensional approximation for the nozzle stagnation pressure is surprisingly accurate even when stagnation pressure varies significantly in time during burning tail-off. This was also found to be true for the case breach fault [2]. These results allow us to use the FD&P developed in our earlier research [3]-[6] by substituting head stagnation pressure with nozzle stagnation pressure. The axial corrections to the value of the side thrust due to the mass addition are taken into account by solving a system of ODEs in spatial dimension.

U2 - 10.1109/AERO.2009.4839622

DO - 10.1109/AERO.2009.4839622

M3 - Conference contribution/Paper

AN - SCOPUS:70349131218

SN - 9781424426225

T3 - IEEE Aerospace Conference Proceedings

BT - 2009 IEEE Aerospace Conference

T2 - 2009 IEEE Aerospace Conference

Y2 - 7 March 2009 through 14 March 2009

ER -