Numerical simulations of acoustic resonance of Solid Rocket Motor

Ferretti, V.; Favini, Bernardo; Cavallini, Enrico; Serraglia, Ferruccio; Giacinto, M. Di

doi:10.2514/6.2010-6996

Cited by 18 publications

(6 citation statements)

References 62 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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

Self Cite

View full text Add to dashboard Cite

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.

show abstract

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

View full text Add to dashboard Cite

show abstract

“…The model for the simulation of the aeroacoustic phenomena during the steady state is named AGAR and it has been developing in the recent past [20][21][22] . The purpose is to develop an Aerodynamically Generated Acoustic Resonance model (in the spirit of the models presented in the past for the analysis of the aeroacoustic phenomena in Ref.…”

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

Self Cite

View full text Add to dashboard Cite

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

show abstract

“…Fig. 1.1 shows the appearance of pressure oscillation occurred from a propellant grain: Angular Vortex Shedding (VSA), Obstacle Vortex Shedding (VSO) and Parietal Vortex Shedding (VSP) (Mastrangelo et al, 2011;Ferretti et al, 2010). The principle of generation of pressure oscillation is the following five steps.…”

Section: Introductionmentioning

confidence: 99%

“…Finally, the transfer of energy from the acoustic mode to the shear flow instability. Therefore, this mechanism is a feedback loop (Ferretti et al, 2010;Anthoine, 2000). The payloads such as a satellite and others can be damaged, because the SRM oscillates by the pressure oscillation.…”

Section: Introductionmentioning

confidence: 99%

Two-dimensional computational fluid dynamics analysis of internal flow in a simplified solid rocket motor combustion chamber

Ogawa

Sasaki

2017

JFST

View full text Add to dashboard Cite

Many countries in recent year have focused on small satellite launch. Therefore, Solid Rocket Motor (SRM) plays an important role in the development of small satellites. However, vortical flows sometimes occur from an inhibitor in the propellant, which causes the pressure oscillation. The basic research was carried out to compute various types of simplified SRM model. In this study, Cartesian mesh-based CFD solver, Building-Cube Method (BCM), was employed with the implementation of internal flow boundary condition, and applied for two Taylor Flow models, CDV nozzle and Simple SRM model with/without an inhibitor. According to two Taylor flow model result, the BCM was able to analyze the internal flow in the simplified SRM combustion chamber. The BCM is proved to be valid for nozzle model because the result of CDV nozzle was qualitatively agreed with theoretical solution. According to the result of the simple SRM model, the BCM was able to predict flowfield in the SRM combustion chamber, even with the existence of an inhibitor. Throughout the computations, BCM solver was able to reproduce flows in the SRM combustion chamber, thus it is expected the approach has a great potential to apply for the internal flows in the complicated SRM combustion chamber.

show abstract

Numerical simulations of acoustic resonance of Solid Rocket Motor

Cited by 18 publications

References 62 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

Two-dimensional computational fluid dynamics analysis of internal flow in a simplified solid rocket motor combustion chamber

Contact Info

Product

Resources

About