Efficient solid rocket propulsion for access to space

Maggi, F.; Bandera, A.; Galfetti, L.; Luca, L.T. De; Jackson, T. L.

doi:10.1016/j.actaastro.2009.10.012

Cited by 61 publications

(35 citation statements)

References 14 publications

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“…When the shutter (3) was opened, exposure time ~5 ms, the heat flux was directed to the investigated HEM sample (5). The signals from the photodiodes (7) were transmitted through the L-card E-14-440 ADC (10) and recorded using personal computer (11), and then processed using the LGraph2 software. The ignition delay time tign of HEM was defined as a difference between the times of signal from photodiodes (7), one of which registered the occurrence of flame on the flat end surface of the sample.…”

Section: Methodsmentioning

confidence: 99%

“…Numerous studies presented in literature on the characteristics of boron propellants ignition and combustion with different particle size [11], binder (most commonly used NH4ClO4, KNO3) and the ratio of fuel to oxidizer [12]. In studies aimed at studying ignition and combustion at high pressures [13] or under conditions close to real ones [1,13] the conductive initiation (for example, heating with nichrome filament or hot gases in TGA chamber) was used.…”

Section: Matec Web Of Conferencesmentioning

confidence: 99%

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Ignition and combustion of high-energy materials containing aluminum, boron and aluminum diboride

2018

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Abstract. Boron and its compounds are among the most promising metal fuel components to be used in solid propellants for solid fuel rocket engine and ramjet engine. Papers studying boron oxidation mostly focus on two areas: oxidation of single particles and powders of boron, as well as boroncontaining composite solid propellants. This paper presents the results of an experimental study of the ignition and combustion of the high-energy material samples based on ammonium perchlorate, ammonium nitrate, and an energetic combustible binder. Powders of aluminum, amorphous boron and aluminum diboride, obtained by the SHS method, were used as the metallic fuels. It was found that the use of aluminum diboride in the solid propellant composition makes it possible to reduce the ignition delay time by 1.7-2.2 times and significantly increase the burning rate of the sample (by 4.8 times) as compared to the solid propellant containing aluminum powder. The use of amorphous boron in the solid propellant composition leads to a decrease in the ignition delay time of the sample by a factor of 2.2-2.8 due to high chemical activity and a difference in the oxidation mechanism of boron particles. The burning rate of this sample does not increase significantly.

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Section: Methodsmentioning

confidence: 99%

Section: Matec Web Of Conferencesmentioning

confidence: 99%

Ignition and combustion of high-energy materials containing aluminum, boron and aluminum diboride

2018

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“…The use of packing codes overcomes these problems. Some novel theoretical works can be found in the literature by Bandera et al [17], Maggi et al [18] as well as by Gallier et al [19]. All of these references include experimental data used for the validation of agglomeration models.…”

Section: Investigation On Microstructurementioning

confidence: 99%

Agglomeration in solid rocket propellants: novel experimental and modeling methods

Maggi

Bandera

Luca

et al. 2011

Progress in Propulsion Physics

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Metal agglomeration is a key factor a¨ecting the performance of metalized solid propellant rockets since many of the mechanisms that degrade speci¦c impulse can be ascribed to metal powder aggregation and agglomeration. Condensed combustion products are generated at or near the burning surface of the propellant and then released in the gas phase where they are shaped by the core §ow viscous forces and oxidized by the reactive environment. On this basis, detailed information about the size of agglomerates as they are generated from the propellant may improve the knowledge of the core §ow and, thus, the prediction of its e¨ects (namely, two-phase §ow losses). This topic entails both modeling and experimental activities, and the aim of this work is to present some recent developments achieved at the Space Propulsion Laboratory in cooperation with other international institutions. The experimental part shows the application of high-speed and high-resolution imaging of propellant combustion for automated measurement of particle size exploited by means of an ad-hoc image processing tool. The modeling part demonstrates how heterogeneity can explain the agglomeration by means of a pocket model using spatial statistics and two-(2D) or threedimensional (3D) virtual propellants. A de¦nition of a characteristic time that ¦ts the agglomeration data for tested propellants is suggested, and a method for predicting the agglomerate size is given. Both activities are still a matter of research but the maturity level reached so far permits the application in some practical cases. Progress in Propulsion Physics2 (2011) 81-98

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“…Last 15 years the intense research on new generation of solid and gel-like high energetic systems with aluminium powders of different dispersity [1,2]. These research is coordinated array of fundamental and applied studies in sphere of development of perspective solid propellants (SP) based on aluminum ultrafine powder (UFP) [3].…”

Section: Introductionmentioning

confidence: 99%

Study on thermal oxidation and combustion of aluminum ultrafine powder in high-energy material

et al. 2017

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Abstract. Aluminum is a promising metal fuel for solid propellants due to the high heat of combustion and propulsion specific impulse values. In current study the results of aluminum-containing high-energy material oxidation and combustion processes were received by means of the thermogravimetry and a constant pressure bomb. Ammonium perchloratebased high-energy materials with aluminium powder with different particles size and genesis (produced by methods of electrical explosion of wire is ultrafine Alex and spraying is micron ASD) were studied. The oxidation process mechanism and activation energy were obtained using Freidman and Kissinger methods. It was found that the average activation energy values for tested HEM samples were in the range of 120-160 kJ/mole and the burning rate for HEM sample with Alex was 2.5-3.0 times higher than HEM sample with ASD-1.

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Efficient solid rocket propulsion for access to space

Cited by 61 publications

References 14 publications

Ignition and combustion of high-energy materials containing aluminum, boron and aluminum diboride

Ignition and combustion of high-energy materials containing aluminum, boron and aluminum diboride

Agglomeration in solid rocket propellants: novel experimental and modeling methods

Study on thermal oxidation and combustion of aluminum ultrafine powder in high-energy material

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