Aggregation and Incipient Agglomeration in Metallized Solid Propellants and Solid Fuels for Rocket Propulsion

DeLuca, Luigi T.; Paravan, Christian; Reina, A.; Marchesi, Elisa; Maggi, F.; Bandera, A.; Colombo, G.; Kosowski, B. M.

doi:10.2514/6.2010-6752

Cited by 13 publications

(10 citation statements)

References 7 publications

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“…Many studies of burning aluminum particles have been conducted [1][2][3][4]. Furthermore, many studies of burning time [5], ignition delay time [6], mechanism of agglomeration, and diameter of agglomerate of aluminum particles [7][8][9][10][11][12][13][14] have been conducted using various procedures, mostly experimental, but also analytical, to clarify the mechanism of agglomeration [15][16][17][18].…”

Section: Introductionmentioning

confidence: 99%

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Agglomeration Characteristics of Aluminum Particles in AP/AN Composite Propellants

Takahashi

Oide

Kuwahara

2013

Propellants Explo Pyrotec

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Most solid rockets are powered by ammonium perchlorate (AP) composite propellant including aluminum particles. As aluminized composite propellant burns, aluminum particles agglomerate as large as above 100 μm diameter on the burning surface, which in turn affects propellant combustion characteristics. The development of composite propellants has a long history. Many studies of aluminum particle combustion have been conducted. Optical observations indicate that aluminum particles form agglomerates on the burning surface of aluminized composite propellant. They ignite on leaving the burning surface. Because the temperature gradient in the reaction zone near a burning surface influences the burning rate of a composite propellant, details of aluminum particle agglomeration, agglomerate ignition, and their effects on the temperature gradient must be investigated. In our previous studies, we measured the aluminum particle agglomerate diameter by optical observation and collecting particles. We observed particles on the burning surface, the reaction zone, and the luminous flame zone of an ammonium perchlorate (AP)/ammonium nitrate (AN) composite propellant. We confirmed that agglomeration occurred in the reaction zone and that the agglomerate diameter decreased with increasing the burning rate. In this study, observing aluminum particles in the reaction zone near the burning surface, we investigated the relation between the agglomerates and the burning rate. A decreased burning rate and increased added amount of aluminum particles caused a larger agglomerate diameter. Defining the extent of the distributed aluminum particles before they agglomerate as an agglomerate range, we found that the agglomerate range was constant irrespective of the added amount of aluminum particles. Furthermore, the agglomerate diameter was ascertained from the density of the added amount of aluminum particles in the agglomerate range. We concluded from the heat balance around the burning surface that the product of the agglomerate range and the burning rate was nearly constant irrespective of the added amount of aluminum particles. Moreover, the reduced burning rate increased the agglomerate range.

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Section: Introductionmentioning

confidence: 99%

“…Collection of agglomerated aluminum particles emitted from burning propellant has been done under different pressures. Their particle diameters have been reported [7][8][9][10][11][12][13][14]. Aluminum particles added to AP composite propellant are known to form agglomerates on the burning surface during melting [1,2].…”

Section: Introductionmentioning

confidence: 99%

Agglomeration Characteristics of Aluminum Particles in AP/AN Composite Propellants

Takahashi

Oide

Kuwahara

2013

Propellants Explo Pyrotec

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“…Other fuels are also presently under investigation because of the current limitations of these solid reducers (low regression rate). Indeed, the addition of metal particles (Al, Li, Mg, Be) and of metal hydrides (AlH 3 and others) is investigated [5]. This generally increases the regression rate by about 10 % (due to higher combustion heat release, up to 60 MJ kg -1 ).…”

Section: /41mentioning

confidence: 99%

Literature survey for a first choice of a fuel-oxidiser couple for hybrid propulsion based on kinetic justifications

Gascoin

Gillard

Mangeot

et al. 2012

Journal of Analytical and Applied Pyrolysis

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“…(6). The observed low values of n r can be related to radiation heat transfer and fragmentation e¨ects of the solid fuel grain [34]. In fact, toward the end of the combustion process (low G Ox ), fuel fragments are seen to detach from the fuel grain (Figs.…”

Section: Htpb Fuelmentioning

confidence: 99%

Time-resolved regression rate of innovative hybrid solid fuel formulations

Paravan

Reina

Sossi

et al. 2013

Progress in Propulsion Physics

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Low regression rates limit application of hybrid rocket engines (HREs). In this paper, combustion of HTPB-and solid para©n wax-based fuels is investigated in a lab-scale burner by a time-resolved optical technique. The e¨ects of pressure are explored over the range 7 to 16 bar. Nanosized (ALEX TM , 100 nm, uncoated) and micronsized (MgB composite, 5 µm) metal additives are tested. For all runs, the instantaneous regression rate is not constant but higher at the beginning of tests. Overall, MgB performance and relatively ease of manufacturing enable to consider this additive as an interesting novel candidate to enhance hybrid rocket engines performance. NOMENCLATUREA space-averaged value (of parameter A) A time-averaged value (of parameter A) 2D two-dimensional a multiplicative factor [Eqs. (1) and (5)

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Aggregation and Incipient Agglomeration in Metallized Solid Propellants and Solid Fuels for Rocket Propulsion

Cited by 13 publications

References 7 publications

Agglomeration Characteristics of Aluminum Particles in AP/AN Composite Propellants

Agglomeration Characteristics of Aluminum Particles in AP/AN Composite Propellants

Literature survey for a first choice of a fuel-oxidiser couple for hybrid propulsion based on kinetic justifications

Time-resolved regression rate of innovative hybrid solid fuel formulations

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