Relevant bibliographies by topics / HTPB propellants

Academic literature on the topic 'HTPB propellants'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "HTPB propellants"

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Kohga, Makoto, Tomoki Naya, and Kayoko Okamoto. "Burning Characteristics of Ammonium-Nitrate-Based Composite Propellants with a Hydroxyl-Terminated Polybutadiene/Polytetrahydrofuran Blend Binder." International Journal of Aerospace Engineering 2012 (2012): 1–9. http://dx.doi.org/10.1155/2012/378483.

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Ammonium-nitrate-(AN-) based composite propellants prepared with a hydroxyl-terminated polybutadiene (HTPB)/polytetrahydrofuran (PTHF) blend binder have unique thermal decomposition characteristics. In this study, the burning characteristics of AN/HTPB/PTHF propellants are investigated. The specific impulse and adiabatic flame temperature of an AN-based propellant theoretically increases with an increase in the proportion of PTHF in the HTPB/PTHF blend. With an AN/HTPB propellant, a solid residue is left on the burning surface of the propellant, and the shape of this residue is similar to that of the propellant. On the other hand, an AN/HTPB/PTHF propellant does not leave a solid residue. The burning rates of the AN/HTPB/PTHF propellant are not markedly different from those of the AN/HTPB propellant because some of the liquefied HTPB/PTHF binder cover the burning surface and impede decomposition and combustion. The burning rates of an AN/HTPB/PTHF propellant with a burning catalyst are higher than those of an AN/HTPB propellant supplemented with a catalyst. The beneficial effect of the blend binder on the burning characteristics is clarified upon the addition of a catalyst. The catalyst suppresses the negative influence of the liquefied binder that covers the burning surface. Thus, HTPB/PTHF blend binders are useful in improving the performance of AN-based propellants.
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Lin, Yi-Hsien, Tsung-Mao Yang, Jin-Shuh Li, Kai-Tai Lu, and Tsao-Fa Yeh. "Preliminary Study on Characteristics of NC/HTPB-Based High-Energy Gun Propellants." ChemEngineering 6, no. 5 (October 10, 2022): 80. http://dx.doi.org/10.3390/chemengineering6050080.

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This study mainly explored the characteristics of NC/HTPB-based high-energy gun propellants with RDX, CL-20 or TKX-50 by experimental method. Three series of test samples were prepared referring to the formulation of M1 single-base gun propellant (M1 SBP). The thermochemical characteristics, chemical stability, explosion heat, impact and friction sensitivities of prepared samples were determined by simultaneous differential scanning calorimetry–thermogravimetric analysis (STA DSC–TGA), vacuum stability tester (VST), bomb calorimeter (BC), BAM fallhammer and BAM friction tester, respectively, and compared with those of the reference sample M1. The experimental results indicated that the thermochemical characteristics of NC/HTPB-based high-energy gun propellants were similar to those of M1 SBP. The NC/HTPB-based high-energy gun propellants had good chemical stability and were superior to M1 SBP. The explosion heat of NC/HTPB-based high-energy gun propellants was close to and slightly larger than that of M1 SBP. In addition, the NC/HTPB-based high-energy gun propellants had lower impact and friction sensitivities than the M1 SBP. Therefore, the NC/HTPB-based high-energy gun propellants have the potential to replace the M1 SBP. The combustion performances of NC/HTPB-based high-energy gun propellants will be continuously studied and verified in the future.
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Dong, Ge, Hengzhi Liu, Lei Deng, Haiyang Yu, Xing Zhou, Xianqiong Tang, and Wei Li. "Study on the interfacial interaction between ammonium perchlorate and hydroxyl-terminated polybutadiene in solid propellants by molecular dynamics simulation." e-Polymers 22, no. 1 (January 1, 2022): 264–75. http://dx.doi.org/10.1515/epoly-2022-0016.

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Abstract The interfacial interaction between the main oxidant filler ammonium perchlorate (AP) and hydroxyl-terminated polybutadiene (HTPB) matrix in AP/HTPB propellants were studied via an all-atom molecular dynamics simulation. The results of the simulation showed the effects of the microscopic cross-linked structure of the matrix, stretching rate during uniaxial stretching, and contact area between the filler and matrix on the mechanical properties, such as the stress and strain of the composite solid propellant. Among the aforementioned factors, the stretching rate considerably affects the mechanical properties of the solid propellant, and the maximum stress of the solid propellant proportionally increases with the stretching rate. When defects were introduced on the surface of the AP filler, the contact area between the filler and matrix affected the strain type of the matrix molecules. Owing to the interaction between the molecules and atoms, the strain behaviour of the matrix molecule changed with the change in its microscopic cross-linked structure during uniaxial stretching. Molecular dynamics simulations were used to explore the characteristics at the AP–HTPB interface in AP/HTPB propellants. The aforementioned simulation results further revealed the interfacial interaction mechanism of the AP–HTPB matrix and provided a theoretical basis for the design of high-performance propellants.
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Wu, Xinzhou, Jun Li, Hui Ren, and Qingjie Jiao. "Comparative Study on Thermal Response Mechanism of Two Binders during Slow Cook-Off." Polymers 14, no. 17 (September 5, 2022): 3699. http://dx.doi.org/10.3390/polym14173699.

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The HTPE (hydroxyl-terminated polyether) propellant had a lower ignition temperature (150 °C vs. 240 °C) than the HTPB (hydroxy-terminated polybutadiene) propellant in the slow cook-off test. The reactions of the two propellants were combustion and explosion, respectively. A series of experiments including the changes of colors and the intensity of infrared characteristic peaks were designed to characterize the differences in the thermal response mechanisms of the HTPB and HTPE binder systems. As a solid phase filler to accidental ignition, the weight loss and microscopic morphology of AP (30~230 °C) were observed by TG and SEM. The defects of the propellant caused by the cook-off were quantitatively analyzed by the box counting method. Above 120 °C, the HTPE propellant began to melt and disperse in the holes, filling the cracks, which generated during the decomposition of AP at a low temperature. Melting products were called the “high-temperature self-repair body”. A series of analyses proved that the different thermal responses of the two binders were the main cause of the slow cook-off results, which were likewise verified in the propellant mechanical properties and gel fraction test. From the microscopic point of view, the mechanism of HTPE’s slow cook-off performance superior to HTPB was revealed in this article.
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Ji, Yongchao, Liang Cao, Zhuo Li, Guoqing Chen, Peng Cao, and Tong Liu. "Numerical Conversion Method for the Dynamic Storage Modulus and Relaxation Modulus of Hydroxy-Terminated Polybutadiene (HTPB) Propellants." Polymers 15, no. 1 (December 20, 2022): 3. http://dx.doi.org/10.3390/polym15010003.

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As a typical viscoelastic material, solid propellants have a large difference in mechanical properties under static and dynamic loading. This variability is manifested in the difference in values of the relaxation modulus and dynamic modulus, which serve as the entry point for studying the dynamic and static mechanical properties of propellants. The relaxation modulus and dynamic modulus have a clear integral relationship in theory, but their consistency in engineering practice has never been verified. In this paper, by introducing the “catch-up factor λ” and “waiting factor γ”, a method for the inter-conversion of the dynamic storage modulus and relaxation modulus of HTPB propellant is established, and the consistency between them is verified. The results show that the time region of the calculated conversion values of the relaxation modulus obtained by this method covers 10−8–104 s, spanning twelve orders of magnitude. Compared to that of the relaxation modulus (10−4–104 s, spanning eight orders of magnitude), an expansion of four orders of magnitude is achieved. This enhances the expression ability of the relaxation modulus on the mechanical properties of the propellant. Furthermore, when the conversion method is applied to the dynamic–static modulus conversion of the other two HTPB propellants, the results show that the correlation coefficient between the calculated and measured conversion values is R2 > 0.933. This proves the applicability of this method to the dynamic–static modulus conversion of other types of HTPB propellants. It was also found that λ and γ have the same universal optimal value for different HTPB propellants. As a bridge for static and dynamic modulus conversion, this method greatly expands the expression ability of the relaxation modulus and dynamic storage modulus on the mechanical properties of the HTPB propellant, which is of great significance in the research into the mechanical properties of the propellant.
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Pang, W. Q., F. Q. Zhao, L. T. DeLuca, C. Kappenstein, H. X. Xu, and X. Z. Fan. "Effects of Nano-Sized Al on the Combustion Performance of Fuel Rich Solid Rocket Propellants." Eurasian Chemico-Technological Journal 18, no. 3 (November 5, 2016): 197. http://dx.doi.org/10.18321/ectj425.

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Several industrial- and research – type fuel rich solid rocket propellants containing nano-metric aluminum metal particles, featuring the same nominal composition, were prepared and experimentally analyzed. The effects of nano-sized aluminum (nAl) on the rheological properties of metal/HTPB slurries and fuel rich solid propellant slurries were investigated. The energetic properties (heat of combustion and density) and the hazardous properties (impact sensitivity and friction sensitivity) of propellants prepared were analyzed and the properties mentioned above compared to those of a conventional aluminized (micro-Al, mAl) propellant. The strand burning rate and the associated combustion fl ame structure of propellants were also determined. The results show that nAl powder is nearly “round” or “ellipse” shaped, which is different from the tested micrometric Al used as a reference metal fuel. Two kinds of Al (nAl and mAl) powder can be dispersed in HTPB binder suffi ciently. The density of propellant decreases with increasing mass fraction of nAl powder; the measured heat of combustion, friction sensitivity, and impact sensitivity of propellants increase with increasing mass fraction of nAl powder in the formulation. The burning rates of fuel rich propellant increase with increasing pressure, and the burning rate of the propellant loaded with 20% mass fraction of nAl powder increases 77.2% at 1 MPa, the pressure exponent of propellant increase a little with increasing mass fraction of nAl powder in the explored pressure ranges.
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Dewi, Wiwiek Utami. "EVALUASI KINETIKA DEKOMPOSISI TERMAL PROPELAN KOMPOSIT AP/HTPB DENGAN METODE KISSINGER, FLYNN WALL OZAWA DAN COATS - REDFREN." Jurnal Teknologi Dirgantara 15, no. 2 (February 27, 2018): 115. http://dx.doi.org/10.30536/j.jtd.2017.v0.a2635.

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Decomposition of propellant Mechanism and kinetics have been investigated by using DTG/TA with three different methods: Kissinger, Flynn Wall Ozawa and Coats & Redfern. This research aims to determine decomposition kinetic parameters of LAPAN’s propellant. The propellants have different composition of Al and AP modal. RUM propellant consist of AP/HTPB. 450 propellant consists AP/HTPB/Al (bimodal). Meanwhile 1220 propellant consists of AP/HTPB/Al (trimoda). Thermal analysis takes place at 30 – 400oC and nitrogen atmosphere flow rate is 50 ml/min. The result according showed that propellant was decomposed by F1 mechanism (random nucleation with one nucleus on the individual particles). Activation energy of propellants are in range between 100.876 – 155.156 kJ/mol meanwhile pre-exponential factor are in range between 4.57 x 107 – 3.46 x 1012/min. Activation energy (E) as well as pre-exponential factor for 1220 propellant is the lowest among the others. AP trimodal application generates catalytic effect which decreases activation energy. 1220 propellant is easier to decompose (easier to react) than RUM and 450 propellant. AbstrakMekanisme dan kinetika dekomposisi propelan telah diinvestigasi menggunakan DTG/TA dengan tiga jenis metode yang berbeda yaitu Kissinger, Flynn Wall Ozawa dan Coats & Redfern. Penelitian ini bertujuan untuk mengetahui parameter kinetika dekomposisi propelan LAPAN. Propelan yang digunakan memiliki perbedaan komposisi Al dan jenis moda AP. Propelan RUM adalah propelan AP/HTPB. RX 450 adalah AP/HTPB/ Al (bimoda). Sementara itu, RX 1220 adalah AP/HTPB/ Al (trimoda). Pengujian termal berlangsung pada suhu 30 - 400oC dan atmosfer nitrogen berlaju alir 50 ml/menit. Hasil penelitian mengungkapkan bahwa semua jenis propelan terdekomposisi dengan mekanisme F1 (nukleasi acak dengan satu nukleus pada partikel individu). Energi aktivasi propelan berkisar antara 100,876 – 155,156 kJ/mol sementara faktor pre-eksponensial berkisar antara 4,57 x 107 – 3,46 x 1012/min. Energi aktivasi (E) dan faktor pre-eksponensial (A) RX 1220 adalah terendah dari ketiga sampel. Penggunaan jenis AP trimodul menciptakan efek katalitik yang menurunkan besarnya energi aktivasi. Propelan RX 1220 lebih mudah terdekomposisi (lebih mudah bereaksi) daripada propelan RUM dan RX 450.
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Wang, Qizhou, Guang Wang, Zhejun Wang, Hongfu Qiang, Xueren Wang, and Shudi Pei. "Strain-rate correlation of biaxial tension and compression mechanical properties of HTPB and NEPE propellants." AIP Advances 12, no. 5 (May 1, 2022): 055005. http://dx.doi.org/10.1063/5.0083205.

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An effective biaxial tension and compression test method is proposed based on the shortcomings of current research for the mechanical properties of solid propellants under complex stress states. The equal proportion biaxial tension and compression test of HTPB (Hydroxyl-terminated polybutadiene) and NEPE (NitrateEster Plasticized Polyether) solid propellants is performed at different rates while at room temperature, and the damage morphology of the tension–compression zone is analyzed using micro-CT. The results show that the failure mode of the solid propellant under biaxial tension and compression loading is similar to that under uniaxial tension. Meanwhile, the compressive strength is much greater than the tensile strength, which will eventually cause tensile failure. With an increased loading rate, the growth trend of the initial modulus, ultimate strength, and maximum elongation of the propellant is gradually flattened, and the damage degree is gradually reduced. Additionally, damage that forms in the HTPB propellant is from dewetting and particle fracture while that for the NEPE propellant is from matrix tearing. The porosity can be used as the meso-damage parameter of the propellant.
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Chaturvedi, Shalini, and Pragnesh N. Dave. "Solid propellants: AP/HTPB composite propellants." Arabian Journal of Chemistry 12, no. 8 (December 2019): 2061–68. http://dx.doi.org/10.1016/j.arabjc.2014.12.033.

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Xie, Zhi Min, Si Chi Chen, and You Shan Wang. "Relaxation Properties of the Solid Propellant Based on Hydroxyl-Terminated Polybutadiene." Advanced Materials Research 989-994 (July 2014): 172–76. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.172.

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The polymer-based propellant is a typical viscoelastic material. Better understanding of the relaxation properties of the propellant in the storage conditions is of great importance for predicting the lifetime. Due to the component complexity of the composite propellants, the transformation relation between the relaxation modulus and the complex modulus may not be suitable for all kinds of propellants. In the present work, we focused on the transformation of the relaxation modulus and complex modulus for the HTPB propellant. The master curves for the relaxation modulus and the storage modulus of the aged/unaged HTPB propellants were obtained by performing the stress relaxation tests and DMA tests, respectively. It was found that there existed a great difference in the double logarithmic plot between relaxation modulus and storage modulus master curves. Moreover, the testing results for the relaxation modulus and the storage modulus were well fitted by an empirical transformation relation with three segment-related coefficients. These three coefficients were determined by using the unaged samples, and then were applied to estimate the relaxation modulus of the aged samples. A good agreement between the calculation and the experimental results was also found, revealing that the three coefficients were insensitive to the aging time.
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Dissertations / Theses on the topic "HTPB propellants"

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Rossetti, Edoardo. "Evaluation of the ballistic properties of a solid propellant from its granulometric composition." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021.

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This work is aimed at evaluating the effect of a solid propellant’s granulometric composition on its burning rate and, more in general, on its ballistic properties, as packing, density, or specific impulse. To evaluate the burning rate, a combustion model is developed in MatLab. To conclude, a model predicting the viscosity of a bimodal propellant is introduced. The obtained results show a significant agreement between experimental data, used as references, and the predicted ones. This work is the starting point from which other works can arise, improving the combustion model and expanding the viscosity estimation also for trimodal propellants.
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Smyth, Daniel A. "Modeling Solid Propellant Ignition Events." BYU ScholarsArchive, 2011. https://scholarsarchive.byu.edu/etd/3125.

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This dissertation documents the building of computational propellant/ingredient models toward predicting AP/HTPB/Al cookoff events. Two computer codes were used to complete this work; a steady-state code and a transient ignition code Numerous levels of verification resulted in a robust set of codes to which several propellant/ingredient models were applied. To validate the final cookoff predictions, several levels of validation were completed, including the comparison of model predictions to experimental data for: AP steady-state combustion, fine-AP/HTPB steady-state combustion, AP laser ignition, fine-AP/HTPB laser ignition, AP/HTPB/Al ignition, and AP/HTPB/Al cookoff. A previous AP steady-state model was updated, and then a new AP steady-state model was developed, to predict steady-state combustion. Burning rate, temperature sensitivity, surface temperature, melt-layer thickness, surface species at low pressure and high initial temperature, final flame temperature, final species fractions, and laser-augmented burning rate were all predicted accurately by the new model. AP ignition predictions gave accurate times to ignition for the limited experimental data available. A previous fine-AP/HTPB steady-state model was improved to predict a melt layer consistent with observation and avoid numerical divergence in the ignition code. The current fine-AP/HTPB model predicts burning rate, surface temperature, final flame temperature, and final species fractions for several different propellant formulations with decent success. Results indicate that the modeled condensed-phase decomposition should be exothermic, instead of endothermic, as currently formulated. Changing the model in this way would allow for accurate predictions of temperature sensitivity, laser-augmented burning rate, and surface temperature trends. AP/HTPB ignition predictions bounded the data across a wide range of heat fluxes. The AP/HTPB/Al model was based upon the kinetics of the AP/HTPB model, with the inclusion of aluminum being inert in both the solid and gas phases. AP/HTPB/Al ignition predictions bound the data for all but one source. AP/HTPB/Al cookoff predictions were accurate when compared to the limited data, being slightly low (shorter time) in general. Comparisons of AP/HTPB/Al ignition and cookoff data showed that the experimental data might be igniting earlier than expected.
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Styborski, Jeremy A. "Effects of aluminum and iron nanoparticle additives on composite AP/HTPB solid propellant regression rate." Thesis, Rensselaer Polytechnic Institute, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=1561975.

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This project was started in the interest of supplementing existing data on additives to composite solid propellants. The study on the addition of iron and aluminum nanoparticles to composite AP/HTPB propellants was conducted at the Combustion and Energy Systems Laboratory at RPI in the new strand-burner experiment setup. For this study, a large literature review was conducted on history of solid propellant combustion modeling and the empirical results of tests on binders, plasticizers, AP particle size, and additives.

The study focused on the addition of nano-scale aluminum and iron in small concentrations to AP/HTPB solid propellants with an average AP particle size of 200 microns. Replacing 1% of the propellant's AP with 40-60 nm aluminum particles produced no change in combustive behavior. The addition of 1% 60-80 nm iron particles produced a significant increase in burn rate, although the increase was lesser at higher pressures. These results are summarized in Table 2. The increase in the burn rate at all pressures due to the addition of iron nanoparticles warranted further study on the effect of concentration of iron. Tests conducted at 10 atm showed that the mean regression rate varied with iron concentration, peaking at 1% and 3%. Regardless of the iron concentration, the regression rate was higher than the baseline AP/HTPB propellants. These results are summarized in Table 3.

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Ruffilli, Davide. "Simulation of the casting process of an Al-AP-HTPB propellant with an open source solver." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021.

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The purpose of this work is to understand and evaluate the phenomena that influence the burning rate. In particular it focuses on the separation between solid and liquid phase during the casting process. To evaluate it an open source solver is used (OpenFOAM) with the addition of formulas that allow to evaluate the difference in concentration of solid particles. The obtained results show a significant agreement between experimental data and previous studies, used as references, and the predicted ones. This work is the starting point from which other future studies can draw inspiration to continue the analysis in more detail.
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Tanner, Matthew Wilder. "Multidimensional Modeling of Solid Propellant Burning Rates and Aluminum Agglomeration and One-Dimensional Modeling of RDX/GAP and AP/HTPB." Diss., CLICK HERE for online access, 2008. http://contentdm.lib.byu.edu/ETD/image/etd2706.pdf.

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Gross, Matthew L. "Two-Dimensional Modeling of AP/HTPB Utilizing a Vorticity Formulation and One-Dimensional Modeling of AP and ADN." Diss., CLICK HERE for online access, 2007. http://contentdm.lib.byu.edu/ETD/image/etd2077.pdf.

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Mateille, Pierre. "Analyse multi-échelle des phénomènes d'endommagement d'un matériau composite de type propergol, soumis à un impact de faible intensité." Phd thesis, Université Montpellier II - Sciences et Techniques du Languedoc, 2010. http://tel.archives-ouvertes.fr/tel-00797604.

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Les explosifs sont des matériaux qui, bien que potentiellement sensibles, sont conçus pour être stables en conditions normales, ainsi que lors de sollicitations mécaniques, chimiques ou thermiques " faibles ". Pourtant, sous sollicitations mécaniques de faible intensité, comme les impacts basse vitesse, ils peuvent réagir de manière intempestive. Les propergols, et plus particulièrement la butalite, objet de notre étude, présentent ce caractère : on observe des " réactions " pour des vitesses d'impacts inférieures à 100 m.s-1, dont l'origine est probablement liée à l'endommagement microstructural du matériau. Dans ce contexte, le but ultime du CEA Gramat est d'obtenir un outil de prédiction de la vulnérabilité des matériaux énergétiques pour les impacts à basse vitesse de type " tour de chute ". Pour ce faire, il est essentiel de disposer de données sur la morphologie et le comportement (thermo)mécanique macroscopique du matériau considéré, de ses phases constitutives à l'échelle mésoscopique et de ses interfaces. Ainsi l'objectif de la thèse est de déterminer le type et le niveau de(s) endommagement(s) apparaissant(s) dans une " butalite inerte " suite à un impact mécanique dit " à basse vitesse " (i.e., inférieure à 100 m.s-1) réalisé à l'aide d'un dispositif de type tour de chute modifié, associant un suivi par vidéo numérique rapide et une analyse microtomographique ante- et post-essai, en étudiant le ou les phénomènes physiques à l'origine des réactions sous " faibles " sollicitations, leur évolution et leur(s) origine(s) physique(s). Les grains sont modélisés par une loi de comportement purement élastique et la matrice en PBHT est décrite par une loi visco-hyper-élastique (couplage d'une série de Prony et du modèle de Mooney-Rivlin).
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Sekkar, V. "Studies On HTPB Based Copolyurethanes As Solid Propellant Binders : Characterization And Modeling Of Network Parameters." Thesis, 1996. http://etd.iisc.ernet.in/handle/2005/1569.

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Stephens, Matthew. "TAILORING THE PLATEAU BURNING RATES OF COMPOSITE PROPELLANTS BY THE USE OF NANOSCALE ADDITIVES." 2009. http://hdl.handle.net/1969.1/ETD-TAMU-2009-05-418.

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Composite propellants are composed of a solid oxidizer that is mixed into a hydrocarbon binder that when polymerized results in a solid mass capable of selfsustained combustion after ignition. Plateau propellants exhibit burning rate curves that do not follow the typical linear relationship between burning rate and pressure when plotted on a log-log scale, and because of this deviation their burning behavior is classified as anomalous burning. It is not unusual for solid-particle additives to be added to propellants in order to enhance burning rate or other properties. However, the effect of nano-size solid additives in these propellants is not fully understood or agreed upon within the research community. The current project set out to explore what possible variables were creating this result and to explore new additives. This thesis contains a literature review chronicling the last half-century of research to better understand the mechanisms that govern anomalous burning and to shed light on current research into plateau and related propellants. In addition to the review, a series of experiments investigating the use of nanoscale TiO2-based additives in AP-HTPB composite propellants was performed. The baseline propellant consisted of either 70% or 80% monomodal AP (223 μm) and 30% or 20% binder composed of IPDI-cured HTPB with Tepanol. Propellants’ burning rates were tested using a strand bomb between 500 and 2500 psi (34.0-170.1 atm). Analysis of the burning rate data shows that the crystal phase and synthesis method of the TiO2 additive are influential to plateau tailoring and to the apparent effectiveness of the additive in altering the burning rate of the composite propellant. Some of the discrepancy in the literature regarding the effectiveness of TiO2 as a tailoring additive may be due to differences in how the additive was produced. Doping the TiO2 with small amounts of metallic elements (Al, Fe, or Gd) showed additional effects on the burning rate that depend on the doping material and the amount of the dopant.
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ZHU, JUN-JI, and 朱俊吉. "Aging studies on HTPB/Ap/Al composite propellant." Thesis, 1990. http://ndltd.ncl.edu.tw/handle/02356588642215623369.

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Book chapters on the topic "HTPB propellants"

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Zhao, Xitong, Xiaolong Fu, Zhengming Gao, Liping Jiang, Jizhen Li, and Xuezhong Fan. "Molecular Dynamics Study on Aging Mechanism of HTPB Propellants." In Springer Proceedings in Physics, 595–609. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-1774-5_44.

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Dubey, Vanchhit Kumar, Sri Nithya Mahottamananda, Afreen Abdul Khaleel, P. N. Kadiresh, and M. Thirumurugan. "Mechanical Characteristics of Paraffin Wax, Beeswax and HTPB as Rocket Propellant—A Comparative Study." In Advances in Design and Thermal Systems, 243–52. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-6428-8_18.

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Rocha, Roberta Jachura. "Accelerated Aging Tests of HTPB-Based Propellants." In Energetic Materials Research, Applications, and New Technologies, 246–71. IGI Global, 2018. http://dx.doi.org/10.4018/978-1-5225-2903-3.ch012.

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In the late twentieth century, liquid and solid propulsion technologies have been integrated into hybrid engines currently apllied in propulsion launch vehicles and missiles. The reaction of polyol (HTPB) and diisocyanate (IPDI) provides the most versatile of the binders in the production of solid propellants due to its ability to withstand high loads combined with low cost and ease of processing. A propellant based on HTPB obtained in this study was submitted to natural and accelerated aging tests, seeking to evaluate the modifications of mechanical properties as tensile strength, elongation and hardness up to 360 days. The mechanism considered in the aging process is the increase of crosslink density by breaking the double bond contained in the HTPB molecule, which causes the instability of the propellant, increasing its handling risk. Samples of these propellants subjected to aging presented variations in their properties that match the values available in the literature.
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"Combustion Characteristics of Aluminized HTPB/AP Propellants in Acceleration Fields." In Solid Propellant Chemistry, Combustion, and Motor Interior Ballistics, 907–20. Reston ,VA: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/5.9781600866562.0907.0920.

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Almeida, Luis Eduardo Nunes, Aureomar F. Martins, Susane R. Gomes, and Flavio A. L. Cunha. "Thermal Decomposition Kinetics Studies of HTPB/Al/AP Solid Propellants Formulated With Iron Oxide Burning Rate Catalyst in Nano and Micro Scale." In Energetic Materials Research, Applications, and New Technologies, 211–33. IGI Global, 2018. http://dx.doi.org/10.4018/978-1-5225-2903-3.ch010.

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The thermal decomposition kinetics of ammonium perchlorate (AP)/hydroxyl-terminated-polybutadiene (HTPB) samples, with Iron Oxide catalyst at nano and micro scale were studied by thermal analysis techniques at different heating rates in dynamic nitrogen atmosphere. The exothermic reaction kinetics was studied by differential scanning calorimetry (DSC) in isothermal conditions. The Arrhenius kinetic parameters were obtained by Flynn-Wall and Ozawa Kissinger and Starink methods. The propellant samples thermal decomposition was studied simultaneously by TG-DTA. For this purpose, solid propellant grains containing nano and micro scale iron oxide were formulated. The effect of catalysts on the propellant burning rate and the propellant initiation sensitivity were also evaluated by friction and impact. The effect of the catalyst in the propellant binder reaction was evaluated by viscosity and mechanical properties. SEM/EDS technique was used to evaluate the iron oxide morphology. Three bench firing tests were performed with rockets motor in order to know the ballistics parameters.
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K., Abhay, and Devendra D. "HTPB-Polyurethane: A Versatile Fuel Binder for Composite Solid Propellant." In Polyurethane. InTech, 2012. http://dx.doi.org/10.5772/47995.

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B. Goncalves, R. F., J. A. F. F. Rocco, and K. Ih. "Thermal Decomposition Kinetics of Aged Solid Propellant Based on Ammonium Perchlorate – AP/HTPB Binder." In Applications of Calorimetry in a Wide Context - Differential Scanning Calorimetry, Isothermal Titration Calorimetry and Microcalorimetry. InTech, 2013. http://dx.doi.org/10.5772/52109.

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Conference papers on the topic "HTPB propellants"

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Brewster, M., G. Knott, and B. Chorpening. "Combustion of AP/HTPB laminate propellants." In 37th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-4501.

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de Flon, John, Sten Andreasson, Mattias Liljedahl, Carl Oscarson, Marita Wanhatalo, and Niklas Wingborg. "Solid Propellants based on ADN and HTPB." In 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6136.

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Hickman, S., and M. Brewster. "Oscillatory combustion of fine-AP/HTPB propellants." In 36th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-557.

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BAKER, P., A. MELLOR, and C. COFFEY. "Critical impact initiation energies for three HTPB propellants." In 26th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2196.

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Boteler, J. M., and A. J. Lindfors. "Shock Loading Studies of AP/AL/HTPB Based Propellants." In 42ND ANNUAL REVIEW OF PROGRESS IN QUANTITATIVE NONDESTRUCTIVE EVALUATION: Incorporating the 6th European-American Workshop on Reliability of NDE. AIP Publishing LLC, 1996. http://dx.doi.org/10.1063/1.50832.

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Mullen, J., and M. Brewster. "Investigation of Aluminum Agglomeration in AP/HTPB Composite Propellants." In 44th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-280.

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Thomas, James C., Felix A. Rodriguez, Thomas Sammet, Catherine A. Dillier, Erica D. Petersen, and Eric L. Petersen. "Manufacturing and Burning of Composite AP/HTPB/AP Laminate Propellants." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-4365.

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Thomas, James C., Felix A. Rodriguez, and Eric L. Petersen. "Strand Burner Experiments with Metal-Loaded AP/HTPB Laminate Propellants." In AIAA Scitech 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-1429.

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John, Henry J., Frank E. Hudson, and Rodney Robbs. "High strain rate testing of AP/Al/HTPB solid propellants." In The tenth American Physical Society topical conference on shock compression of condensed matter. AIP, 1998. http://dx.doi.org/10.1063/1.55554.

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de Almeida, Luiz Eduardo N., Rene F. Goncalves, Jose A. Rocco, Fabio L. Calciolari, and Koshun Iha. "Evaluation of Plateau Burning Behavior in HTPB-AP-Al Composite Propellants." In AIAA Propulsion and Energy 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3901.

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