On the Effects of Igniter Jets during Pre-Ignition Transient of SRMs

Favini, Bernardo; Zaghi, Stefano; DiMascio, A.; Cavallini, Enrico; Ferretti, V.; Serraglia, Ferruccio; Giacinto, M. Di

doi:10.2514/6.2010-6583

Cited by 7 publications

(14 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Remanding the detailed discussion to [2], the root cause for the thrust negative peak registered by the bench axial load cell was found to be due directly to the experienced pressure unbalance inside the combustion chamber (NDP) registered during the SFT. The 3D numerical simulations performed with Xaer allowed explaining and analyzing the root cause of the NDP onset.…”

Section: Xaer Codementioning

confidence: 98%

“…The prediction presented in [2], here reported in Fig. 5 for clarity and on comparison purpose, was based on the first AVIO predictions on the new igniter operational conditions, because of the unavailability of any experimental data.…”

Section: Z9a Vt2 Predictionmentioning

confidence: 99%

“…Consequently also the experimental NDP parameter, defined as the difference between the head and the aft pressure inside the SRM, was successfully captured by the Xaer numerical simulation [2].…”

Section: Xaer Codementioning

confidence: 99%

“…5 for clarity and on comparison purpose, was based on the first AVIO predictions on the new igniter operational conditions, because of the unavailability of any experimental data. After the VT2 SFT, as presented in [2], the Xaer predicted head and aft end pressure were compared with the experimental data, showing an over-estimation of both the head and aft pressurization rates and an under-estimation of the time delay between the two (see Fig. 5).…”

Section: Z9a Vt2 Predictionmentioning

confidence: 99%

“…Therefore, in order to investigate and characterize the root cause of the negative force peak for Z9A QM2 and VT, unsteady 3D Computational Fluid Dynamics simulations (Xaer code) were performed using the main igniter reconstruction provided by AVIO. With the Xaer code, the SFT data coming from the forward and aft pressure transducers were successfully simulated [2].…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

On the NDP onset in pre-ignition transient of high performance SRMs: VEGA Z9A experience

Favini

Cavallini

Rossi

et al. 2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

View full text Add to dashboard Cite

This paper discusses the early phase of the ignition transient of the VEGA Launcher's third stage solid rocket motor, Zefiro 9A. During the first two firing tests of the Z9A SRM (QM2 and VT1) a peculiar unexpected negative force peak and a significant pressure unbalance in the motor chamber were measured during the very first phase of the ignition transient. In order to fix the unexpected negative force, out of the system specifications, a modification of the igniter re-design was decided for the Z9A SRM and a third static firing test was successfully carried out (VT2), with a reduction of the negative differential pressure of at least around a factor 3, followed by a reduction of the negative thrust by around the same factor. This paper wants to analyze the scenario outlined by the VT2 static firing test by means of three dimensional unsteady multi-component numerical simulations of the SRM pre-ignition transient. © 2011 IEEE

show abstract

Section: Xaer Codementioning

confidence: 98%

Section: Z9a Vt2 Predictionmentioning

confidence: 99%

Section: Xaer Codementioning

confidence: 99%

Section: Z9a Vt2 Predictionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

On the NDP onset in pre-ignition transient of high performance SRMs: VEGA Z9A experience

Favini

Cavallini

Rossi

et al. 2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

View full text Add to dashboard Cite

show abstract

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

Giacinto

Cavallini

Favini

et al. 2015

Journal of Propulsion and Power

View full text Add to dashboard Cite

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.

show abstract