Internal Ballistics and Dynamics of VEGA Launcher Solid Rocket Motors During Ignition Transient: Firing Test Predictions and Post Firing Analysis

Giacinto, M. Di; Favini, Bernardo; Attili, Antonio; Serraglia, Ferruccio; Scoccimarro, Dario; Trapani, Claudia Di; Preve, Andrea; Bonnet, Michel

doi:10.2514/6.2007-5814

Cited by 10 publications

(12 citation statements)

References 8 publications

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“…This kind of model has shown to work very well in characterizing the cavity response in case of pressure oscillations during the ignition transient, being successfully applied to the ignition transient analysis of VEGA SRM ignition transients [28][29][30][31][32][33][34][35][36][37] and, then has been applied also to the pressure oscillations due to aeroacoustic phenomena of P80 SRM [2][3][4][5] . For the application to the pressure oscillations of the P80 during the quasi-steady state, a sensitivity analysis performed on the semi-empirical parameter of the cavity model, for the results presented in section III, shows that in a large range of variation, the model has almost negligible effects on the coupling frequency of the aeroacoustic feedback loop of the P80 blows, as expected, but also on the time windows and amplitude of the blows themselves.…”

Section: B Cavity Model Of Submergence Regionmentioning

confidence: 99%

Q1D Modelling of Vortex-Driven Pressure Oscillations in Aft-Finocyl SRMs with Submerged Nozzle Cavity

Cavallini¹,

Favini²,

Neri³

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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This paper has the aim to investigate the aero-acoustic coupling that occurs typically in large aft-finocyl SRMs with submerged nozzle configurations, leading the onset of sustained pressure and thrust oscillations during the motor firing, by means of a Q1D model of the SRM aero-acoustic and vortex sound generation. The model has been applied successfully for the characterization of the pressure oscillations due to angle vortex shedding and the aero-acoustic coupling of P80 SRM, first stage of the VEGA launcher. The P80 pressure oscillations phases are characterized with a good correlation with the experimental data, identifying the different characteristics of the flowfield conditions for the first two blows (that occur when the aft-region of the SRM burns), with respect to the other two blows (which occur when the aft-region of the SRM is completely burnt out). In particular, the effect of the submergence cavity within the Q1D vortex sound generation model is investigated by means of proposed closures for the characterization of the cavity behaviour and compared by means of a parametric analysis with a benchmark numerical solution and the experimental data of the firings.Results show that for the first two blows, occurring when the submergence cavity burns and is active in terms of mass addition, the role of the cavity model is almost negligible, or very small, and well correlated with the dispersion of the experimental data of the P80 pressure oscillations. Instead, for the third and fourth blows, that occur when the cavity is empty of propellant grain, the cavity model plays a role on the aeroacoustic coupling, showing that the the feedback loop between the angle vortex shedding and the chamber acoustics is influenced by the cavity response.

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Section: B Cavity Model Of Submergence Regionmentioning

confidence: 99%

Q1D Modelling of Vortex-Driven Pressure Oscillations in Aft-Finocyl SRMs with Submerged Nozzle Cavity

Cavallini¹,

Favini²,

Neri³

2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

Self Cite

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“…The model for the ignition transient simulations is named SPIT -Solid Propellant rocket motor Ignition Transient -and has been successfully validated against all the European SRMs (Ariane 4, Ariane 5, Zefiro 9, Zefiro 16, Zefiro 23 and P80) and officially adopted in the frame of the VEGA programme, for the predictions and reconstructions analyses of the solid stages ignition transient [3][4][5][8][9][10][11][12][13][14][15][16][17][18][19] .…”

Section: Mathematical and Numerical Modelsmentioning

confidence: 99%

Analysis of Pressure Oscillations during Ignition Transient and Steady-State of an Overloaded VEGA First Stage

Cavallini¹,

Favini²,

Neri³

2014

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The dynamic environment of a solid rocket motor may bring about severe impacts on the launch vehicle performance suited to the payload requirements, and therefore, especially in the early phase of its design, it has to be carefully evaluated in order to correctly assess the design configuration of the SRM and the launcher.\ud \ud This paper provides a first assessment of the ignition transient phase and the steady state phase of a tentative configuration of the VEGA upgraded first stage SRM, with particular attention on the characterization of the onset of pressure oscillations that are responsible for the dynamic environment experienced by the SRM during its operative life.\ud This tentative configuration has been designed as a P80 XL stretched SRM, waiting for the VECEP first state configuration that will be consolidated in the summer of 2014.\ud This first assessment is performed with the use of numerical models of the ignition transient (SPIT) and of the aeroacoustic phenomena in solid rocket motors (AGAR), which set-up is consolidated and validated against the P80 firings (DM and QM) and flights (VV01 and VV02) data.\ud \ud Results of this first assessment indicate that, as for the VEGA solid stages, the use of helium as pressurizing gas is mandatory in order to control the dynamic environment generated during the motor start-up by the P80 XL.\ud For the pressure oscillations during the steady state of the P80 XL stretched, the first numerical simulations indicate that, as the P80, this motor is characterized by the presence of pressure oscillation blows, which maximum amplitude is slightly higher than P80 ones.\ud The occurrence of the pressure blows appears during the steady state in similar motor phases, when compared to the P80 ones, and related to the activation of the first longitudinal acoustic mode of the combustion chamber

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“…This model was successfully validated against all the European SRMs (Ariane 4, Ariane 5, Zefiro 9, Zefiro 16, Zefiro 23, and P80FW) and largely adopted in the frame of the Vega program for the predictions and reconstruction analyses of the solid stages ignition transient [16][17][18][19][20][21][22][23][24][25][26][27].…”

Section: Solid Rocket Motor Ignition Transient Modelmentioning

confidence: 99%

“…In particular, the major efforts have been done from the 1980s up to the recent past for the space shuttle reusable solid rocket motor (RSRM) and the Titan solid rocket motor upgrade (SRMU) [7][8][9][10][11][12][13][14][15], by U.S. researchers, and from 2001 up to the recent past for the Vega solid rocket motors [16][17][18][19][20][21][22][23][24][25][26][27] by European researchers. A very good description of SRM ignition transient phenomena and review of the state of the art of modeling efforts and approaches to the SRM startup phase is described in [14,28].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Parametric Study on Solid Rocket Motor Ignition Transient and Pressure Oscillations Onset

Giacinto

Cavallini

Favini

et al. 2015

Journal of Propulsion and Power

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The startup represents a very critical phase during the whole operational life of solid rocket motors. This paper provides a detailed study of the effects on the ignition transient of the main design parameters of solid-propellant motors. The analysis is made with the use of a quasi-one-dimensional unsteady model of solid rocket ignition transient, extensively validated, and used in the frame of the Vega program, for ignition transient predictions, reconstructions, and analyses. Two baseline solid rocket motor configurations are selected for the parametric analysis: a big booster with a three-segment propellant grain shape, similar to Ariane 5, and a small booster/solid stage with an aft-finocyl grain shape, similar to Vega solid rocket motors. The discussion of the results is particularly addressed on the possible onset of the pressure oscillations during the startup of the two solid rocket motor configurations, pointing out the design parameters that affect them in terms of occurrence and amplitude.

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Internal Ballistics and Dynamics of VEGA Launcher Solid Rocket Motors During Ignition Transient: Firing Test Predictions and Post Firing Analysis

Cited by 10 publications

References 8 publications

Q1D Modelling of Vortex-Driven Pressure Oscillations in Aft-Finocyl SRMs with Submerged Nozzle Cavity

Q1D Modelling of Vortex-Driven Pressure Oscillations in Aft-Finocyl SRMs with Submerged Nozzle Cavity

Analysis of Pressure Oscillations during Ignition Transient and Steady-State of an Overloaded VEGA First Stage

Parametric Study on Solid Rocket Motor Ignition Transient and Pressure Oscillations Onset

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