Role of Binders in Solid Propellant Combustion

Cohen, N.; Fleming, R. W.; Derr, R. L.

doi:10.2514/3.49195

Cited by 139 publications

(20 citation statements)

References 8 publications

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“…where _ r ref 0:5 mm=s is given at a surface reference temperature T s;ref 780 K. The activation energy E F for isophorone diisocyanate crosslinked HTPB is of a controversial value; it was concluded by Esker and Brewster [41] that, at high heating rates (10 2 -10 4 K=s by laser radiation [39] and simultaneous mass and temperature change/Fourier transform infrared [42] spectroscopy methods), the activation energy is around E F 11 kcal=mol, whereas the values that have been obtained by lower heating rate methods (0:1-1 K=s with thermogravimetric analysis [40], differential scanning calorimeter [43], and arc-image [44] methods) are much higher. The model adopts the value of E F 11 kcal=mol based on the high heating rates typical to rocket applications.…”

Section: A Mass Conservationmentioning

confidence: 99%

Modeling the Combustion of a Solid Fuel Containing a Liquid Oxidizer Droplet

Pelosi

Gany

2012

Journal of Propulsion and Power

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This work presents a physical model of the combustion behavior of a liquid oxidizer droplet with adjacent solid fuel. It is the first modeling attempt related to a proposed new potential class of liquid-oxidizer-enhanced solid propellants, where liquid oxidizer units/capsules are embedded in a solid fuel/propellant, revealing a theoretical specific impulse increase of up to 12%. A one-dimensional mathematical model is formulated, which describes the main characteristics of the microscale flamelet formed by a volatile (typically polymeric) fuel component and an adjacent endothermically evaporating oxidizer droplet. The model predicts fuel and oxidizer surface temperatures, fluxes, and flame height as functions of operating pressure and droplet size. The transient nature of the combustion process is emphasized, revealing a combustion cycle at the individual droplet scale, with pressure-dependent average burning rates typical to solid propellants.

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Section: A Mass Conservationmentioning

confidence: 99%

Modeling the Combustion of a Solid Fuel Containing a Liquid Oxidizer Droplet

Pelosi

Gany

2012

Journal of Propulsion and Power

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“…alors le taux de production s'écrit : [27] et Arisawa et Brill [8,9], les coefficients d'Arrhenius étant donnés par plusieurs auteurs en fonction des différents paramètres. Cette expression ne fait pas intervenir la pression de manière explicite bien que celle-ci puisse avoir un effet non négligeable pour certaines configurations à faibles flux massiques d'oxydant [83].…”

Section: Modèles 2d Et 3dunclassified

Hydrodynamic Instabilities Modeling in Hybrid Rocket Engines

Messineo

Lestrade

Hijlkema

et al. 2019

Journal of Spacecraft and Rockets

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Table des matières Liste des figures xii Liste des tableaux xiii Nomenclature xv A Récapitulatif du modèle d'instabilités hydrodynamiques Bibliographie viii Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides xviii Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides 1. Une partie de ce chapitre a fait l'objet d'un article dans le Journal of Propulsion and Power : « Vortex shedding influence on hybrid rocket pressure oscillations and combustion efficiency » [62]. Modélisation des instabilités hydrodynamiques dans les moteurs-fusées hybrides

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“…Many foundational research has been published about HTPB shortly after its introduction [7][8][9]. However, very few reviews were specifically devoted to HTPB general features during that time [10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Properties of Hydroxyl‐Terminal Polybutadiene (HTPB) and Its Use as a Liner and Binder for Composite Propellants: A Review of Recent Advances

Amado

Ross

Murakami

et al. 2022

Propellants Explo Pyrotec

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This paper reviews hydroxyl-terminal polybutadiene (HTPB) used as liner and binder for composite propellants, applied in rocket motors studied throughout the last decades, emphasizing the recent advances. The contribution aims to show the importance of HTPB in the propellant composition and on the liner coating of the rocket motor, which is in contact with the propellant grain. This paper also shows that many researchers have thoroughly studied several properties of HTPB, which are rele-vant to its role in liners and propellants. We have also reviewed analytical techniques such as Fourier Transform Infrared Spectroscopy (FTIR) as a characterization technique for HTPB and HTPB-based polyurethanes. Reflection and transfectants FTIR may be a future trend in studies about polymeric matrices for liners and propellants, and in the area of propellant formulations that use energetic binders, graphene and nanomaterials.

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Role of Binders in Solid Propellant Combustion

Cited by 139 publications

References 8 publications

Modeling the Combustion of a Solid Fuel Containing a Liquid Oxidizer Droplet

Modeling the Combustion of a Solid Fuel Containing a Liquid Oxidizer Droplet

Hydrodynamic Instabilities Modeling in Hybrid Rocket Engines

Properties of Hydroxyl‐Terminal Polybutadiene (HTPB) and Its Use as a Liner and Binder for Composite Propellants: A Review of Recent Advances

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