Modeling of normal and erosive burning rate of a hot double-base homogeneous propellant

Joulain, P.; Lengellé, G.; Godon, J.

doi:10.1016/0010-2180(95)00192-1

Cited by 9 publications

(4 citation statements)

References 19 publications

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“…[ 12 ] Typically, high burning rates are often accompanied by a high value of the pressure exponent, which could potentially lead to catastrophic consequences. [ 20 ] Unexpected, the pressure exponent of RDX@PDA‐Pb sample on each pressure point is consistently lower than 0.3 and the average value of n in the pressure range from 2 to 20 MPa is only 0.17, which is significantly important for the development of more stable and safe rocket engines. Such a wide combustion plateau indicates that the combustion process in the whole pressure range is under reaction control rather than the diffusion control, [ 21 ] which is intrinsically attributed to the high catalytic activity of the PDA‐Pb and thus enables stable combustion in such broad pressure range.…”

Section: Resultsmentioning

confidence: 99%

Pb Single Atoms Enable Unprecedented Catalytic Behavior for the Combustion of Energetic Materials

Qu¹,

Niu

Sun

et al. 2021

Advanced Science

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Manipulating the thermal decomposition behavior of energetic materials is the key to further pushing the combustion performance of solid rocket propellants. Herein, atomically dispersed Pb single atoms on polydopamine (PDA‐Pb) are demonstrated, which display unprecedented catalytic activity toward the thermal decomposition of cyclotrimethylenetrinitramine (RDX). Impressively, RDX‐based propellants with the addition of PDA‐Pb catalyst exhibit substantially enhanced burning rates (14.98 mm s−1 at 2 MPa), which is 4.8 times faster than that without PDA‐Pb and represents the best catalytic performance among Pb‐based catalysts. Moreover, it also possesses low‐pressure exponents in broad pressure ranges, which can enable more stable and safer combustion in solid rocket engines. Theoretical calculation unravels the efficient catalytic activity is stemmed from the enhanced interfacial electronic coupling between RDX and PDA‐Pb via orbital level engineering. More importantly, PDA‐Pb also presents similar catalytic behavior toward the decomposition of nitrocellulose, suggesting its broad catalytic generality. This work can open up new opportunities in the field of energetic compound combustion by exploring Pb‐based single atom catalysts and beyond.

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Section: Resultsmentioning

confidence: 99%

Pb Single Atoms Enable Unprecedented Catalytic Behavior for the Combustion of Energetic Materials

Qu¹,

Niu

Sun

et al. 2021

Advanced Science

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“…It can be seen from the law that the burning rate can increase with the increase of the pressure. The value of n represents the pressure sensitivity of the propellant, and high value of n (greater than 0.6) is not wanted and even cause the propellant combustion process to get out of control [6, 7].…”

Section: Introductionmentioning

confidence: 99%

Preparation of Nano‐Spherical Cu‐en and Its Catalytic Study on the Performance of Solid Propellant

Song

Liu

Yang

et al. 2020

Propellants Explo Pyrotec

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This paper mainly describes a nano‐spherical energetic catalyst Cu‐en. The result of particle size distribution shows that the D50 value of Cu‐en is 80.18 nm. The thermal decomposition process of RDX, AP, and NC is improved obviously after mixed with Cu‐en. Among them, the change of AP is the most significant, and its peaks of high‐temperature decomposition and low‐temperature decomposition degenerate into one decomposition peak. The thermal decomposition temperature of NC also decreased from 214.5 °C to 191.6 °C. In the range of 3–9 MPa, Cu‐en can significantly increase the burning rate of HTPB propellant and reduce the pressure exponent n from 0.684 to 0.459. According to the test data results of the CMDB propellant, the nano‐spherical Cu‐en prepared by the spray drying method has a stronger catalytic ability than the micro‐nano Cu‐en prepared by the high‐energy ball milling method.

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“…Rocket propellants may be divided into two general classes, double-base propellants and composite propellants. The principle components of the double base propellants are nitrocellulose and an explosive plasticizer, usually nitroglycerin, [6][7][8][9], while the composite propellants are made by embedding a finely divided solid oxidizing agent in a binder. Regarding the latter composite propellant, oxidizing agents which have been used extensively include ammonium nitrate, sodium nitrate, potassium nitrate, ammonium perchlorate, and potassium perchlorate.…”

Section: Introductory Remarksmentioning

confidence: 99%

“…AP, NH 4 ClO 4 , based composite propellants are widely used in a variety of rocket motor systems ranging from small tactical missiles to the large boosters that propel the space shuttle into orbit. The properties used for AP come from Tanaka and Beckstead [12,13] and Guirao and Williams [14 10] and the JANNAF tables, [ 8 ]. Most of the thermodynamic and transport properties used for HTPB come from the work of Parr and Hanson-Parr [ adapted from 12], Jeppson et.al.…”

Section: Introductory Remarksmentioning

confidence: 99%

An Overview of Solid Propellant Combustion Modeling

Hegab

2007

International Conference on Aerospace Sciences and Aviation Tec

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An overview of theoretical and experimental work concerning the burning process in rocket propellant is presented. The current study has emphasized Ammonium Perchlorate (AP) / Hydroxyl Terminated Poly-Butadiance, (HTPB) composites rocket propellant. These propellants are widely used in a variety of rocket systems ranging from small tactical missiles to the large boosters that propel the space shuttle into orbit. A detailed review for the chemical kinetics, numerical and experimental models for the burning of the monomodal, bimodal, and multimodal propellants is introduced. Effects of propellant compositions, time-dependent pressure fluctuations, temperature, fuel-binder types, on the burning rate are reviewed and discussed. The result of the current study shows the effect of pressure and the AP particle sizes on the burning rate, the complex flame structure, and the morphology of the combustion surface.

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Modeling of normal and erosive burning rate of a hot double-base homogeneous propellant

Cited by 9 publications

References 19 publications

Pb Single Atoms Enable Unprecedented Catalytic Behavior for the Combustion of Energetic Materials

Pb Single Atoms Enable Unprecedented Catalytic Behavior for the Combustion of Energetic Materials

Preparation of Nano‐Spherical Cu‐en and Its Catalytic Study on the Performance of Solid Propellant

An Overview of Solid Propellant Combustion Modeling

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