Propellant Trade-off Analysis for Upper Stage Solid Rocket Motors Performance

Cavallini, Enrico; Bianchi, Daniele; Favini, Bernardo; Giacinto, M. Di

doi:10.2514/6.2013-4010

Cited by 8 publications

(3 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For the analysis of the flight, however, no direct measure of the final nozzle throat can be performed, and therefore, we assumed the semi-empirical correlations gained from the SFTs analysis as a functional dependence of the nozzle throat erosion rate (or mass flow rate per unit area) as a function of the SRM operating pressure, since in the typical regime of diffusion limited erosion of the throat insert, its is known [13][14][15] that this is the main functional dependence of the nozzle throat erosion. This means that each SFT provides a nozzle throat erosion correlation for the analysis of the SRM flight data.…”

Section: Srm Static Firing Test Reconstruction Modelmentioning

confidence: 99%

Analysis and Performance Reconstruction of VEGA Solid Rocket Motors Qualification Flights

Cavallini¹,

Favini²,

Neri³

2014

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

Self Cite

View full text Add to dashboard Cite

VEGA is the launch vehicle developed by the European Space Agency, qualified with its first two maiden flights on February, 13rd 2012 and on May, 7th 2013 and recently delivered to the commercial market with the third flight held on April, 30th 2014.\ud During the launcher development, a total of eight static firing tests have been performed for the three solid stages, which compose the launcher: the first stage P80, the second stage Zefiro 23 and the third stage Z9.\ud In this work, the analysis and performance reconstruction of the solid rocket motors of the VEGA launch vehicle for the two qualification flights is carried out with a post-firing reconstruction model, developed for the purpose.\ud The aim is to use the measures acquired during the flights and the experience gained from the static firing tests analysis, in order to evaluate the actual behavior of the VEGA solid stages, through the non-ideal parameters: combustion efficiency, thrust efficiency, hump, scale factor and nozzle throat erosion law, which define the actual performance parameters of the solid rocket motors.\ud The purpose of the work is to assess the SRMs performance parameters from the flight data, comparing the outcomes of the flight data analysis with the ones provided by the static firing test data analysis.\ud The final aim is to consolidate the methodology for the analysis and reconstruction of the solid stage flight data, in order to define/characterize the scattering of the motor performance, reducing the uncertainties for the prediction methodologies in the upcoming and following VEGA flights

show abstract

Section: Srm Static Firing Test Reconstruction Modelmentioning

confidence: 99%

Analysis and Performance Reconstruction of VEGA Solid Rocket Motors Qualification Flights

Cavallini¹,

Favini²,

Neri³

2014

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

Self Cite

View full text Add to dashboard Cite

show abstract

“…The governing equation are discretized by a Godunov-type scheme, accurate at first or second order in space and time. The main model is completed by different sub-models in order to describe the SRM ignition transient and nozzle throat ablation phenomena 20,25,26 . The grain burnback model is a 3D numerical simulation of the propellant grain burning surface evolution in time, name GREG 24,27 , based on a level set technique properly tailored to the evolution of the combustion surface of SRMs.…”

Section: Internal Ballistics Q1d Model Of Srms Acoustic Resonancementioning

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

“…The governing equation are discretized by a Godunov-type scheme, first or second order (ENO) accurate in space and time. The main model is completed by different sub-models in order to describe the SRM ignition transient and nozzle throat ablation phenomena 39,44,45 .…”

Section: B Internal Ballistics Q1d Model Of Srms Acoustic Resonancementioning

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

Propellant Trade-off Analysis for Upper Stage Solid Rocket Motors Performance

Cited by 8 publications

References 11 publications

Analysis and Performance Reconstruction of VEGA Solid Rocket Motors Qualification Flights

Analysis and Performance Reconstruction of VEGA Solid Rocket Motors Qualification Flights

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

Contact Info

Product

Resources

About