Characterization of SRM plumes with alumina particulate in subscale testing

Saile, Dominik; Allofs, Dirk; Kühl, Viktor; Steffens, Lars; Gülhan, Ali; Beversdorff, Manfred; Förster, Wolfgang; Willert, Christian; Carlotti, Stefania; Maggi, F.; Liljedahl, Mattias; Wingborg, Niklas; Langener, Tobias; Eynde, Jeroen Van den

doi:10.1007/s12567-020-00338-0

Cited by 6 publications

(8 citation statements)

References 17 publications

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“…Without any aim of generalities, the present discussion will focus only on the influence of the divergent part as a function of the expansion ratios tested during the experimental campaign. Hints supporting its influence were found by post-fire collection of solidified metal deposits on the divergent part of the nozzle [21], as shown in Fig. 7a.…”

Section: Physical Characterizationmentioning

confidence: 89%

“…The experiments addressed in this work were executed in the EMAP (Experimental Modelling of Alumina Particulate in Solid Boosters) framework, an ESA-TRP project pursuing activities concerning the characterization of the condensed particles contained in the exhaust plume of a sub-scale SRM, under different operating conditions. A complete overview of the project and more details about the measurement systems are provided in Saile et al [21].…”

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confidence: 99%

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Experimental techniques for characterization of particles in plumes of sub-scale solid rocket motors

Carlotti¹,

Maggi²

2021

Acta Astronautica

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Section: Physical Characterizationmentioning

confidence: 89%

mentioning

confidence: 99%

Experimental techniques for characterization of particles in plumes of sub-scale solid rocket motors

Carlotti¹,

Maggi²

2021

Acta Astronautica

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“…In conclusion, spectroscopy allows one to precisely define the intensity as a function of the wavelength, and it provided the results in the study of the temperature of gases and particles. The "overview to the ESA-EMAP project: characterization of SRM plumes with alumina particulate in subscale testing" of Saile et al [28] deals with the experimental study of alumina particulates in solid rocket engines. In this work, the focus is on those particles that remain in the atmosphere after a solid rocket vehicle has passed.…”

Section: Fourier Transform Infrared Spectroscopymentioning

confidence: 99%

“…Overall, with the laboratory scale hybrid motor, plume spectroscopy can be easily used; therefore, it can be used to characterize the hybrid motor and solid rocket motors. Another work in which FTIR spectroscopy was used in conjunction with UV-VIS emission spectroscopy was the work of Saile et al [28]. The Ocean Optics USB2000 spectrometer working in a spectral range of 200-850 nm was used for UV-VIS spectroscopy.…”

Section: Uv-vis Spectroscopymentioning

confidence: 99%

Optical Diagnostics for Solid Rocket Plumes Characterization: A Review

et al. 2022

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In recent decades, solid fuel combustion propulsion of spacecraft has become one of the most popular choices for rocket propulsion systems. The reasons for this success are a wide range of applications, lower production costs, simplicity, and safety. The rocket’s plumes leave the nozzle at high temperatures; hence, the knowledge of produced infrared (IR) emissions is a crucial aspect during the design and tests of the rocket motors. Furthermore, rocket plume composition is given by N2, H2, H2O, CO and CO2, while solid rocket motors (SRM) additionally inject some solid particles, given by metal fuel additives in the propellant grain, i.e., aluminum oxide (Al2O3) particles. The main issue is the detection of the particles remaining in the atmosphere due to the exhaust gas of the solid rocket propulsion system that could have effects on ozone depletion. The experimental characterization of SRM plumes in the presence of alumina particles can be conducted using different optical techniques. The present study aims to review the most promising ones with a description of the optics system and their potential applications for SRM plume measurements. The most common measurement techniques are infrared spectroscopy imaging, IR imaging. UV–VIS measurements, shadowgraph, and Schlieren optical methods. The choice of these techniques among many others is due to the ability to study the plume without influencing the physical conditions existing in and around the study object. This paper presents technical results concerning the study of rocket engines plumes with the above-mentioned methods and reveals the feasibility of the measurement techniques applied.

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“…The integrated setup of the EMAP project is visible in Fig. 2 and a detailed discussion can be found in a recent paper by Saile and co-authors [25]. During the hot flow tests, the RPC was placed at 180 mm from the nozzle exit section because of DLR internal safety requirement and to grant free optical path to the other non-intrusive techniques.…”

Section: Analysis Technique a Concept Description And Implementationmentioning

confidence: 99%

Experiments for Collection and Characterization of Particles Exiting from Solid Propellant Rocket Nozzles

Maggi

Carlotti

Saile

et al. 2020

AIAA Propulsion and Energy 2020 Forum

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Metals in solid propellants are used to improve specific impulse and increment the energy density. Their combustion generates condensed products that move along the motor chamber and are expelled through the nozzle. The discharge of liquid or solid particles across the gas dynamic nozzle of large boosters is not only a matter of specific impulse loss. Recent climatological studies are addressing possible short and long term environmental effects that may be attributed to space launch activity by large launchers. In this respect, the knowledge of plume content and, specifically, of physical, chemical, and morphological properties of the exhausted particulate is needed. In the frame of the EMAP (Experimental Modelling of Alumina Particulate in Solid Booster) project, an activity financed by the European Space Agency, the Space Propulsion Laboratory (SPLab) of Politecnico di Milano developed a collection method and an analysis protocol for the characterization of the particles contained in the rocket plume. The collection is performed by an intrusive probe capable of capturing the particles directly from the nozzle exit and quenching them. The post-collection protocol enables size measurement, chemical characterization, and morphology observation. In this paper an overview of the collection and analysis activity is presented, along with the final results that were achieved by analyzing the plume of different rocket motors. I. Nomenclature D(3, 2) = surface-mean diameter D(4, 3) = volume-mean diameter d(0.x) = diameter at the given percentile p cc = chamber pressure

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Characterization of SRM plumes with alumina particulate in subscale testing

Cited by 6 publications

References 17 publications

Experimental techniques for characterization of particles in plumes of sub-scale solid rocket motors

Experimental techniques for characterization of particles in plumes of sub-scale solid rocket motors

Optical Diagnostics for Solid Rocket Plumes Characterization: A Review

Experiments for Collection and Characterization of Particles Exiting from Solid Propellant Rocket Nozzles

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