Relevant bibliographies by topics / Propellants

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Propellants'

Author: Grafiati
Published: 4 June 2021
Last updated: 15 June 2025

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Journal articles on the topic "Propellants"

1

Chen, Xingquan, Weihua Zhang, An’yong Wang, Luping Xu, Yang Xiao, and Yuling Gao. "CT Scan Characterization of Thermally Tested Hollow Cylindrical Propellant." Journal of Physics: Conference Series 2891, no. 4 (2024): 042002. https://doi.org/10.1088/1742-6596/2891/4/042002.

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Abstract In order to study microscopic characteristics of thermally tested hollow cylindrical propellant, BT-400 industrial CT equipment was used to scan the heights of 50mm, 150mm and 250mm from the bottom of the propellants. 1 DR image and 12 CT images obtained. The propellant’s external diameter, inner hollow diameter, CT value and density difference of each CT scan region were measured with these CT images. The results show that, compared with normal temperature (25°C) experiment, the outside diameter and inner hollow diameter of thermally tested propellant at low temperature (−45°C) decreased, and its density increased; The outside diameter and inner hollow diameter of thermally tested propellant at high temperature (+70°C) increased, and its density decreased. Although no thermal damage forms such as inclusions, cracks and debonding were found in all CT scan images of thermally tested propellants, some low-density shrinkage pores were found in some CT scan images of thermally tested propellants, but these low density pores had no effect on the density distribution and uniformity of thermally tested propellants. CT scan microscopic characterization of thermally tested hollow cylindrical propellant is of great significance to evaluate propellant quality.
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Jain, Prakhar, Vineet Kumar Rathi, and Shelly Biswas. "Study of Aging Characteristics for Metalized HTPB Based Composite Solid Propellants Stored in Ambient Conditions." Defence Science Journal 74, no. 5 (2024): 615–26. http://dx.doi.org/10.14429/dsj.74.19786.

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The aging of any propellant is defined as the change in the physical, chemical, and performance parameters of solid rocket propellants. The propellant’s service life and aging properties are important parameters of the study, especially for missiles and other defense applications. Hydroxyl-terminated polybutadiene (HTPB) based composite solid propellants with ammonium perchlorate (AP) are the most prominently used propellants in the operations of solid rocket motors in the defense and space sectors. Thus, studying this composite solid propellant is of essential when determining ambient service life. Performance parameters studied in this research are burn rate under high-pressure conditions in Crawford bomb setup, Thermogravimetric Analysis, and Fourier Transform Infrared Spectroscopy (FTIR). SEM and X-ray diffraction (XRD) analysis of the aged sample were also conducted to ascertain the chemical composition and morphological changes in the samples. Naturally aged propellant strands manufactured in different years have been compared with freshly prepared ones to establish a trend for deriving conclusions. The results from different analysis techniques, FTIR, XRD, and FESEM, depicted that oxidation of metals happens while aging of propellant due to atmospheric moisture, and the metal oxides prominently affect the propellant chemical composition and decomposition process of the propellant samples. The ballistic properties of the aluminium added samples showed an increment in burn rate. In contrast, the bimetal addition of aluminium and magnesium combined as an additive decreased the ballistic burn rate.
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Trębiński, Radosław, Jacek Janiszewski, Zbigniew Leciejewski, Zbigniew Surma, and Kinga Kamińska. "On Influence of Mechanical Properties of Gun Propellants on Their Ballistic Characteristics Determined in Closed Vessel Tests." Materials 13, no. 14 (2020): 3243. http://dx.doi.org/10.3390/ma13143243.

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The geometric burning law of gun propellants is widely used in computer codes used for the simulations of the internal ballistics of guns. However, the results of closed vessel tests prove that the burning process of some propellants deviates from the geometric law. Validation of the hypothesis that observed deviations can be attributed to the cracking of propellant grains was the aim of this work. In order to verify the hypothesis, three types of gun propellants were chosen with considerably differing mechanical strengths: a single-base propellant, a double-base propellant, and a composite propellant. The mechanical properties of the gun propellants were tested using a quasi-static compression method with strain rate values of the order of 0.001 s−1 and the Split Hopkinson Pressure Bar technique with the strain rate in the range of 1000–6000 s−1. The mechanical responses of the propellants were assessed on the basis of the true stress–strain curves obtained and from the point of view of the occurrence of cracks in the propellant grains specimens. Moreover, closed vessel tests were performed to determine experimental shape functions for the considered gun propellants. Juxtaposition of the stress‒strain curves with the experimental shape functions proved that the observed deviations from the geometrical burning law can be attributed mainly to the cracking of propellant grains. The results obtained showed that the rheological properties of propellants are important not only from the point of view of logistical issues but also for the properly controlled burning process of propellants during the shot.
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Zou, Pangangjing, Shichun Li, Shiliang Huang, et al. "Study on the Co-crystal Transition Process and Mechanism of CL-20 and HMX in Propellant Formulation." Journal of Physics: Conference Series 2891, no. 2 (2024): 022015. https://doi.org/10.1088/1742-6596/2891/2/022015.

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Abstract The integration of CL-20 into solid propellants to enhance their energy levels has emerged as a focal point in the research of high-energy solid propellants and the use of CL-20 as a partial substitute for traditional oxidizers in propellant formulations has emerged as a viable method for propellant modification. However, research indicates that the microstructure and crystal form of CL-20 and HMX may undergo changes due to external stimuli and energy induction, resulting in significant deterioration of the propellant’s mechanical and combustion properties, as well as its safety. We were surprised to find that CL-20 and HMX can form co-crystal not only in the nitric ester plasticizer like DOS but also in some specific binders, such as GAP and HTPE, and revealed that the solvent’s capacity to dissolve two explosives is the key determinant in the formation of co-crystal.
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Li, Manman, Yuchen Gao, Qionglin Wang, Weitao Yang, Guo-Lin Gao, and Zaixing Jiang. "UV-Assisted Material Extrusion Additive Manufacturing of Double-Base Propellant." Polymers 17, no. 6 (2025): 808. https://doi.org/10.3390/polym17060808.

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Double-base (DB) propellants, renowned for their superior performance and cost-effectiveness, are extensively utilized in both rocketry and artillery applications. During the 3D printing process of double-base propellants, auxiliary solvents play a crucial role in plasticizing the DB propellant mixtures. Consequently, the printed propellants are prone to significant shrinkage and dimensional instability as a result of solvent evaporation post-printing. To address these challenges, we have innovated a UV-assisted material extrusion 3D printing technique that preserves the intended geometries of the DB propellant. The results of our printing trials indicate that incorporating an energetic UV-curable resin as a modifier into the DB propellant paste is highly effective. Ultimately, we successfully fabricated a porous propellant cylinder featuring a periodic woodpile structure. Additionally, the internal structure, mechanical properties, combustion characteristics, and in-barrel ballistic performance of the printed propellants have been thoroughly characterized. Our findings underscore that the UV-assisted material extrusion additive manufacturing process confers exceptional properties to the DB propellant.
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Gou, Yong-liang, Lun Wei, Yao Yue-juan, Bo Liu, and Jia-peng Wang. "Combustion performance of surface-deterred gun propellants with varied deterrent contents." Journal of Physics: Conference Series 2478, no. 3 (2023): 032004. http://dx.doi.org/10.1088/1742-6596/2478/3/032004.

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Abstract This paper explores how the combustion performance of surface-deterred granular gun propellants relates to the deterrent content to further improve combustion progressivity and low temperature sensitivity. Five types of propellants with different deterrent contents are prepared with the surface deterring technology. Through the analysis of explosion heat and experimental data from closed bomb tests, we investigate the energetic and static combustion properties of the propellants. Results show that the deterred propellants have a higher combustion progressivity than the blank propellant, and as the deterrent content increases, the progressive index increases gradually. In addition, the maximum pressure measured by closed bomb tests is linearly related to the deterrent content. At high temperatures, the average absolute values of the temperature coefficients of relative activity for surface-deterred propellants are lower than that for the blank propellant, indicating better low temperature sensitivity of surface-deterred gun propellants at high and normal temperatures.
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Sun, Qili, Xiao-Mei Yang, and Guang-Zhong Yin. "Mechanical Properties and Thermal Decomposition Mechanism of Glycidyl Azide Polyol Energetic Thermoplastic Elastomer Binder with RDX Composite." Polymers 16, no. 18 (2024): 2626. http://dx.doi.org/10.3390/polym16182626.

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To improve the reinforcement effect between a binder and high solid filler in a propellant formula, grafting the bonding group into the binder to form a neutral polymeric is a practically novel approach to improving the interface properties of the propellant. In this work, a glycidyl azide polyol energetic thermoplastic elastomer binder with a –CN bonding group (GAP–ETPE) was synthesized, and the mechanical and thermal decomposition mechanism of GAP–ETPE with Hexogeon (RDX) model propellants were studied. The stress–strain results indicated that the tensile strength and strain of GAP–ETPE/RDX model propellants were 6.43 MPa and 32.1%, respectively. DMA data showed that the storage modulus (E’) of the GAP–ETPE/RDX model propellants could increase the glass transition temperature (Tg) values, those were shifted to higher temperature with the increase in filler RDX percentages. TG/DTG showed the four decomposition stages of the decomposition process of the GAP–ETPE/RDX model propellants, and the thermal decomposition equation was constructed. These efforts provide a novel method to improve GAP–ETPE/RDX propellants mechanical property, and the thermal decomposition behavior of GAP–ETPE/RDX propellants also provided technical support for the study of propellant combustion characteristics.
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Paraschiv, Titi, Tudor Viorel Tiganescu, George Ovidiu Iorga, Raluca Elena Ginghina, and Octavian Constantin Grigoroiu. "Experimental and Theoretical Study on Three Combustion Models for the Determination of the Performance Parameters of Nitrocellulose - Based Propellants." Revista de Chimie 71, no. 9 (2020): 87–97. http://dx.doi.org/10.37358/rc.20.9.8320.

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Nitrocellulose based propellants are the main materials used for ballistic and rocket applications. The chemical composition of the propellants, the loading density and propellant grain geometry are the decisive parameters that influence the performance parameters in ballistic application. In this paper the authors evaluate three models of combustion for energetic materials for the determination of heat of explosion and specific volume together with the adiabatic flame temperature. The authors select six types of propellant (two simple base propellants, two double base propellants based on nitroglycerine and two triple base propellants based on nitroguanidine) and the authors determined the heat of explosion and specific volume using a bomb calorimeter and a Julius-Peters device. The results obtained from the combustion models were compared to the experimental results and assumptions were done on the influence of pressure and temperature on the chemical composition of combustion gases produced by the confined deflagration of nitrocellulose-based propellants.
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Li, Manman, Zhigang Guo, Yuchen Gao, Qionglin Wang, and Weitao Yang. "Preparation and ballistic performance of super porous photocurable gun propellant." Journal of Physics: Conference Series 2891, no. 2 (2024): 022014. https://doi.org/10.1088/1742-6596/2891/2/022014.

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Abstract Porous propellants were fabricated using an extrusion 3D printer. A novel formulation was developed, containing terminated acrylate-based poly (3-nitrilomethyl-3-methyloxetane) (APNIMMO) as the prepolymer and hexanitrohexaazaisowoodzane (CL-20) as the high-energy solid filler. Photocurable gun propellant slurries were prepared utilizing the acoustic resonance mixier, and subsequently, gun propellants with a core-shell structure were fabricated via extrusion 3D printing technology. The combustion performance and interior ballistic performance of these propellants were tested and analyzed by closed bomb and 12.7mm test gun. The results demonstrated that the propellant grain with shell-core structure possesses better combustion progressivity. Meanwhile, the incorporation of lattice structures in photocurable gun propellants led to increased chamber pressure and muzzle velocity. Conversely, the addition of shell-core structured propellant grains resulted in comparable muzzle velocity but decreased chamber pressure. These findings underscore the significant role of rational structural design in optimizing ballistic performance.
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Abdullah, Mohamed, F. Gholamian, and A. R. Zarei. "Noncrystalline Binder Based Composite Propellant." ISRN Aerospace Engineering 2013 (September 24, 2013): 1–6. http://dx.doi.org/10.1155/2013/679710.

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This study reports on propellants based on cross-linked HTPE binder plasticized with butyl nitroxyethylnitramine (BuNENA) as energetic material and HP 4000D as noncrystalline prepolymer. This binder was conducted with solid loading in the 85%. The results showed an improvement in processability, mechanical properties and burning rate. In addition, its propellant delivers (about 6 seconds) higher performance (specific impulse) than the best existing composite solid rocket propellant. Thermal analyses have performed by (DSC, TGA). The thermal curves have showed a low glass transition temperature () of propellant samples, and there was no sign of binder polymer crystallization at low temperatures (−50°C). Due to its high molecular weight and unsymmetrical or random molecule distributions, the polyether (HP 4000D) has been enhanced the mechanical properties of propellants binder polymer over a large range of temperatures [−50, 50°C]. The propellants described in this paper have presented high volumetric specific impulse (>500 s·gr·cc−1). These factors combined make BuNENA based composite propellant a potentially attractive alternative for a number of missions demanding composite solid propellants.
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Dissertations / Theses on the topic "Propellants"

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Rahm, Martin. "Green Propellants." Doctoral thesis, KTH, Fysikalisk kemi, 2010. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-25835.

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To enable future environmentally friendly access to space by means of solid rocket propulsion a viable replacement to the hazardous ammonium perchlorate oxidizer is needed. Ammonium dinitramide (ADN) is one of few such compounds currently known. Unfortunately compatibility issues with many polymer binder systems and unexplained solid-state behavior have thus far hampered the development of ADN-based propellants. Chapters one, two and three offer a general introduction to the thesis, and into relevant aspects of quantum chemistry and polymer chemistry. Chapter four of this thesis presents extensive quantum chemical and spectroscopic studies that explain much of ADN’s anomalous reactivity, solid-state behavior and thermal stability. Polarization of surface dinitramide anions has been identified as the main reason for the decreased stability of solid ADN, and theoretical models have been developed to explain and predict the solid-state stability of general dinitramide salts. Experimental decomposition characteristics for ADN, such as activation energy and decomposition products, have been explained for different physical conditions. The reactivity of ADN towards many chemical groups is explained by ammonium-mediated conjugate addition reactions. It is predicted that ADN can be stabilized by changing the surface chemistry with additives, for example by using hydrogen bond donors, and by trapping radical intermediates using suitable amine-functionalities. Chapter five presents several conceptual green energetic materials (GEMs), including different pentazolate derivatives, which have been subjected to thorough theoretical studies. One of these, trinitramide (TNA), has been synthesized and characterized by vibrational and nuclear magnetic resonance spectroscopy. Finally, chapter six covers the synthesis of several polymeric materials based on polyoxetanes, which have been tested for compatibility with ADN. Successful formation of polymer matrices based on the ADN-compatible polyglycidyl azide polymer (GAP) has been demonstrated using a novel type of macromolecular curing agent. In light of these results further work towards ADN-propellants is strongly encouraged.<br>QC 20101103
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Ridder, Kristin Barbara. "Nanoparticle formulations in HFA propellants." Thesis, University College London (University of London), 2004. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.412545.

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Lee, Sung-Taick. "Multidimensional effects in composite propellant combustion." Diss., Georgia Institute of Technology, 1991. http://hdl.handle.net/1853/12111.

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Deur, John Mark. "A surface coupled flamelet approach to dynamic response in heterogeneous propellant combustion." Diss., Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/12418.

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Mouille, Hervé. "Influence of strain rate and temperature upon the mechanical and fracture behavior of a simulated solid propellant /." This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-07212009-040252/.

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Fernandez, Margaret Mary. "Propellant tank pressurization modeling for a hybrid rocket /." Online version of thesis, 2009. http://hdl.handle.net/1850/10631.

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Worrell, William J. "Nitrocellulose literature review characterization and application to modern gun propellants." Master's thesis, This resource online, 1990. http://scholar.lib.vt.edu/theses/available/etd-01122010-020032/.

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Hasanoglu, Mehmet Sinan. "Storage Reliability Analysis Of Solid Rocket Propellants." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/2/12609897/index.pdf.

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Solid propellant rocket motor is the primary propulsion technology used for short and medium range missiles. It is also commonly used as boost motor in many di_erent applications. Its wide spread usage gives rise to diversity of environments in which it is handled and stored. Ability to predict the storage life of solid propellants plays an important role in the design and selection of correct protective environments. In this study a methodology for the prediction of solid propellant storage life using cumulative damage concepts is introduced. Finite element mesh of the solid propellant grain is created with the developed parametric grain geometry generator. Finite element analyses are carried out to obtain the temperature and stress response of the propellant to the environmental thermal loads. Daily thermal cycles are assumed to be sinusoidal cycles represented by their means and amplitudes. With the cumulative damage analyses, daily damage accumulated in the critical locations of the solid propellant grain are investigated. Meta-models relating the daily damage amount with the daily temperature cycles are constructed in order to compute probability of failure. The results obtained in this study imply that it is possible to make numerical predictions for the storage life of solid propellants even in the early design phases. The methodology presented in this study provides a basis for storage life predictions.
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Baglar, Emrah. "Artificial Aging Of Crosslinked Double Base Propellants." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12612853/index.pdf.

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In this study, shelf life of three different crosslinked double base (XLDB) propellants stabilized with 2-nitrodiphenylamine (2-NDPA) and n-methyl-4-nitroaniline (MNA) were determined by using the stabilizer depletion method. Depletions of the stabilizers were monitored at different aging temperatures using High Performance Liquid Chromatography (HPLC). Kinetic models of pseudo zero, pseudo first, pseudo second and shifting order were used to find the best model equation that fits the experimental data. The rates of depletion of stabilizers were calculated at 45, 55 and 65&deg<br>C based on the best fit kinetic models. Using the rate constants at different temperatures, rate constants at room temperature were calculated by Arrhenius equation. The activation energies and frequency factors for the depletion of 2-NDPA and MNA were obtained for all XLDB propellants. Moreover, the results were evaluated based on the NATO standard<br>STANAG 4117 and the propellants were found stable according to the standard. Vacuum thermal stability (VTS) tests were also conducted to evaluate the stability of XLDB propellants. The propellant that includes the stabilizer mixture of MNA and 2-NDPA was found to have less stability than the propellants that include 2-NDPA only. However, there were rejection (puking) and migration of stabilizer derivatives for the aged samples of propellants that were stabilized with only 2-NDPA. Moreover, formation of voids and cracks were observed in block propellant samples due to excess gas generation.
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Taylor, M. J. "Plasma propellant interactions in an electrothermal-chemical gun." Thesis, Department of Environmental and Ordnance Systems, 2009. http://hdl.handle.net/1826/4010.

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This Thesis covers work conducted to understand the mechanisms underpinning the operation of the electrothermal-chemical gun. The initial formation of plasma from electrically exploding wires, through to the development of plasma venting from the capillary and interacting with a densely packed energetic propellant bed is included. The prime purpose of the work has been the development and validation of computer codes designed for the predictive modelling of the elect rothe rmal-ch em ical (ETC) gun. Two main discussions in this Thesis are: a proposed electrically insulating vapour barrier located around condensed exploding conductors and the deposition of metallic vapour resulting in a high energy flux to the surface of propellant, leading to propellant ignition. The vapour barrier hypothesis is important in a number of fields where the passage of current through condensed material or through plasma is significant. The importance may arise from the need to disrupt the fragments by applying strong magnetic fields (as in the disruption of metallic shaped charge jets); in the requirement to generate a metallic vapour efficiently from electrically exploding wires (as per ETC ignition systems); or in the necessity to re-use the condensed material after a discharge (as with lightning divertor strips). The ignition by metallic vapour deposition hypothesis relies on the transfer of latent heat during condensation. It is important for the efficient transfer of energy from an exploded wire (or other such metallic vapour generating device) to the surface of energetic material. This flux is obtained far more efficiently through condensation than from radiative energy transfer, because the energy required to evaporate copper is far less than that required to heat it to temperatures at which significant radiative flux would be emitted
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Books on the topic "Propellants"

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Smokeless Propellants. s.n, 1985.

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Kubota, Naminosuke. Propellants and Explosives. Wiley-VCH Verlag GmbH & Co. KGaA, 2015. http://dx.doi.org/10.1002/9783527693481.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Performance of rocket motors with metallized propellants: Report of the Propulsion and Energetics Panel Working Group 17. AGARD, 1986.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Performance of Rocket Motors with Metallized Propellants: Report of the Propulsion and Energetics Panel : Working Group 17. s.n, 1986.

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Advisory Group for Aerospace Research and Development. Propulsion and Energetics Panel. and Advisory Group for Aerospace Research and Development. Consultantand Exchange Programme., eds. Combustion of solid propellants. Agard, 1991.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion of solid propellants. AGARD, 1991.

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Bailey, A. Explosives, propellants, and pyrotechnics. Brassey's (UK), 1989.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combustion of solid propellants. AGARD, 1991.

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Kishore, K. Solid propellant chemistry: Condensed phase behaviour of ammonium perchlorate-based solid propellants. Defence Research & Development Organisation, Ministry of Defence, 1999.

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S, Ianovski Leonid, Carrick Patrick, and Lewis Research Center, eds. Propellant technologies: A persuasive wave of future propulsion benefits. National Aeronautics and Space Administration, Lewis Research Center, 1997.

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Book chapters on the topic "Propellants"

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Wu, Jianjun, Jian Li, Yuanzheng Zhao, and Yu Zhang. "Numerical Simulation of the Nanosecond Laser Ablation of Al Propellant." In Numerical Simulation of Pulsed Plasma Thruster. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-7958-1_4.

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AbstractPulsed plasma thrusters (PPTs) using gaseous propellants (Ziemer and Choueiri in Is the gas-fed PPT an electromagnetic accelerator an investigation using measured performance. AIAA 99–2289, 1999; Ziemer et al. in Performance characterization of a high efficiency gas-fed pulsed plasma thruster. AIAA-97–2925, 1997; Ziemer in Performance scaling of gas-fed pulsed plasma thrusters. Princeton University, 2001; Ziemer and Petr in Performance of gas fed pulsed plasma thrusters using water vapour propellant. AIAA 2002–4273, 2002) typically far outperform those using solid propellants in terms of parameters such as specific impulse and propulsion efficiency.(Porneala and Willis in J Phys D Appl Phys 42:1–7, 2009) Therefore, during the PPT operation, first, the propellant is transformed from a solid state to a gaseous or plasma state to ensure that what is actually ionized in the discharge channel or discharge chamber of the thruster is not the solid propellant but rather the gaseous or plasma propellant. In general, the solid propellant cannot be completely converted to a gaseous or plasma state during the laser ablation process. To increase the gas and plasma components in the discharge channel, an intense laser with a nanosecond pulse width is used as the energy source for propellant ablation. This approach is important for improving the PPT propulsion performance.
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de Iaco Veris, Alessandro. "Tanks for Propellants." In Fundamental Concepts of Liquid-Propellant Rocket Engines. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-54704-2_6.

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Mishra, D. P. "Chemical Rocket Propellants." In Fundamentals of Rocket Propulsion. CRC Press, 2017. http://dx.doi.org/10.1201/9781315175997-6.

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Hazell, Paul J. "Propellants and Explosives." In The Story of the Gun. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-73652-1_6.

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Gindin, James. "Background Themes: The Propellants." In Macmillan Modern Novelists: William Golding. Palgrave Macmillan UK, 1988. http://dx.doi.org/10.1007/978-1-349-18987-8_2.

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Shoemaker, R. L., J. A. Stark, L. G. Koshigoe, and R. E. Taylor. "Thermophysical Properties of Propellants." In Thermal Conductivity 18. Springer US, 1985. http://dx.doi.org/10.1007/978-1-4684-4916-7_22.

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Cardarelli, François. "Fuels, Propellants, and Explosives." In Materials Handbook. Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-38925-7_17.

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Novozhilov, Boris V., Toru Shimada, Masahiro Kohno, and Haruki Maruizumi. "Solid propellant burning rate response function of highly metalized propellants." In Transport Phenomena In Combustion. Routledge, 2024. https://doi.org/10.1201/9780203735138-145.

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"Special Topics in Rocketry." In Solid Rocket Propellants: Science and Technology Challenges. The Royal Society of Chemistry, 2016. http://dx.doi.org/10.1039/9781782620969-00158.

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This chapter includes special topics including thrust vector control, structural integrity of propellants, rocket motor casing materials, life extension/prediction, catalysis and platonization, advanced solid propellants and nanosized ingredients in propellant formulations etc. Generally, these topics are not covered in one place in the literature. The chapter concludes with some remarks on the future of rocketry, propulsion and propellants.
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"The Combustion Mechanism of Solid Rocket Propellants." In Solid Rocket Propellants: Science and Technology Challenges. The Royal Society of Chemistry, 2016. http://dx.doi.org/10.1039/9781782620969-00132.

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This chapter presents the combustion aspects of solid rocket propellants. After initiation by the ignition system, the solid propellant’s surface is subjected to a stable, self-sustained flame or combustion wave structure. The chemistry and combustion wave structure for double base, composite propellants and advanced propellants containing nitramines (RDX, HMX) are discussed in detail in this chapter and important combustion models are also included.
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Conference papers on the topic "Propellants"

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Vázquez, Angel, Moises Tolentino Angeles, Julio Morales, Alejandro Jiménez Gómez, and Joshua Anastacio. ""Chaac": Harnessing Machine Learning for Intelligent Combustion Control and Sustainable Propellants in Liquid Propellant Rocketry." In IAF Space Propulsion Symposium, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078371-0213.

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Jang, Jin-Sung, Hyung-Gun Sung, Seung-Young Yoo, Tae-Seong Roh, and Dong-Whan Choi. "Numerical Study on Properties of Interior Ballistics According to Solid Propellant Position in Chamber." In ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajk2011-12005.

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Analysis of the interior ballistics is essential for the development of gun or propellant configurations. The granular solid propellants with high energy and fast burning rate produce a large thrust in extremely short time intervals. For the study of these, therefore, it is necessary of a numerical code for the two-phase flow of the interior ballistics. Recently, an interior ballistics code (IBcode) for the two-phase flow using the Eulerian-Lagrangian approach has been developed. The SIMPLE algorithm and the SMART scheme have been used for the IBcode. The ghost-cell extrapolation method has been used for the moving boundary with the projectile movement. In this study, a performance of the interior ballistics according to the position of the solid propellant in the chamber has been investigated using the IBcode. In previous researches, propellants had been evenly distributed in the chamber. In this study, however, three cases of the existence of empty space in the chamber at which the propellants are not evenly distributed have been considered; Propellants are located in the region near the base, propellants in the region near the breech, and propellants in the center of the chamber, respectively. The 7-perforated configuration of the solid propellant has been used in this research. The results have shown the performance variations of the interior ballistics according to solid propellant position in the chamber. The cases of the propellants located in the region near the base and breech have shown that the value of the negative differential pressure and the difference between the breech pressure and the base pressure are much higher than those of the propellants located in the center of the chamber. The case of the propellants in the center of the chamber is, therefore, more profitable to improve the performance of the interior ballistics.
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3

Chen, F., Q. Chen, and Z. Liu. "EFFECT OF TEMPERATURE, CONTENT OF PLASTICIZER AND NITROGEN CONTENT OF NITROCELLULOSE ON THE IMPACT SENSITIVITY OF GUN PROPELLANTS." In 34th International Symposium on Ballistics. Destech Publications, Inc., 2025. https://doi.org/10.12783/ballistics25/37131.

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The development of modern gun weapons requires high energy, low sensitivity and wide temperature range gun propellants. In order to improve the formulation of gun propellant, the effects of initial temperature of gun propellants, content of energetic plasticizers and nitrogen content of nitrocellulose on the impact sensitivity of gun propellants was evaluated comprehensively. The results indicate that with the increase of initial temperature, the impact sensitivity of gun propellants increased. When the temperature rises to 80°C, in 25 parallel tests of two gun propellants, the explosion probabilities increased from 5/25 and 2/25 to 24/25, respectively. When the nitroglycerin (NG) content was increased from 30% to 50%, the drop hammer height at which the explosion probability reached 50% (H50) decreased from 14.96 cm to 4.49 cm. When the content of diethyleneglycol dinitrate (DEGDN) increased from 30% to 40%, the H50 value of the gun propellants decreases from 5.21 cm to 3.49 cm. When the nitrogen content of nitrocellulose increases from 12.0% to 13.5%, the impact sensitivity of the gun propellants increases significantly. Overall, this study might provide theoretical basis and data support for the design of gun propellant formulations
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Martinez-Pastor, Juan, Patricio Franco, and F. Javier Ramirez-Fernandez. "Rheological Characterization of Energetic Materials by Rotational Testing Techniques." In ASME 2014 12th Biennial Conference on Engineering Systems Design and Analysis. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/esda2014-20400.

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In production of energetic materials, the rheological behavior of propellant doughs is a key factor to identify optimum and safe conditions for processing these special compounds. The analysis of their rheological properties during mixing and extrusion stages is needed to clarify the complex interrelations between the different process parameters and the expected performance of these products, providing essential information for the possible increase of system productivity and overall product quality. In this study, the rheological analysis of triple-base propellants and a propellant simulant was carried out by a DHR-2 rotational rheometer of TA Instruments. Furthermore, different testing techniques were evaluated for appropriate characterization of these propellants. According to the results of rheological measurements, these triple-base propellants were found to correspond to shear-thinning materials (pseudo-plastic behavior). Finally, the results obtained from these experimental observations were matched to well-known constitutive empirical models to describe the mathematical relation between viscosity and shear strain rate.
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5

Streifel, Benjamin, Amy Courtney, and Michael Courtney. "THERMOCHEMICAL ANALYSIS AND FIELD PERFORMANCE OF SMALL ARMS PROPELLANTS FROM 1953 (30-06 M2 AP) AND 2012 (M55A1) AMMUNITION." In 34th International Symposium on Ballistics. Destech Publications, Inc., 2025. https://doi.org/10.12783/ballistics25/37118.

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When older stocks of ammunition are fielded for use, propellant degradation may alter chamber pressures, or in the worst-case scenario, may present risk for auto-ignition. Propellants harvested from U.S military cartridges—1953 30-06 M2 AP and 2012 M855A1 were evaluated using thermochemical techniques and field testing. Thermal analysis demonstrated similar energy densities between 1953, 2012, and 2022-era propellants with similar morphology. Minor changes in activation energy and stabilizer content suggested slightly decreased propellant thermal stability in the 1953 propellant. A novel application of modified thermogravimetric analysis (mTGA) is introduced and shows promise for more rapidly determining the properties of older stocks of ammunition being considered for use. In field testing, the 1953-era propellant demonstrated comparable standard deviations in velocity and on-target precision to the 2012 propellant, and both resulted in similar standard deviations in velocity and on-target performance to a modern extruded commercial reloading powder.
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6

Chen, Yang, Vahid Morovati, and Roozbeh Dargazany. "A Directional Damage Constitutive Model for Stress-Softening in Solid Propellant." In ASME 2020 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/imece2020-24285.

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Abstract Solid propellants are particulate composite with a light cross-linked elastomeric binder filled with a high concentration of energetic, solid aggregates. Solid propellants are often considered as highly nonlinear elastomeric materials, with elastic behavior resulted from its binder and plastic behavior from its energetic particles. The study of the micro-structure and mechanical properties of solid propellant is crucial for its design, safety evaluation, and lifetime prediction of solid fuel carriers. The constitutive model proposed for rubber-like material can often be generalized to predict the nonlinear behavior of solid propellant due to the dependency on the mechanical behavior of solid propellant on its elastomeric binder material. This paper focuses on developing a model that predicts the stress softening and strain-residual mechanism of the solid propellant. This micro-mechanical model for solid propellant was proposed based on the network evolution theory. The motivation of this study is the lack of a micro-mechanical model that can describe both the stress softening effect and strain residual in the quasi-static behavior of propellants. The simplified network-evolution model with only five parameters is a simple micro-mechanical model that captures both the stress softening effect and strain residual. Besides the simplicity and reduced fitting procedure, the model was validated against several experimental data and illustrated good agreement in small and large deformations, making the proposed model a suitable option for commercial and other applications.
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Reich, Alton. "System for the Automated Mitigation of Hypergolic Propellant Leaks." In ASME 2012 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/pvp2012-78495.

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Hypergolic liquid rocket propellants consist of fuel and oxidizer liquids stored in separate tanks that ignite when mixed. They are favored for propulsion systems where precise pulsing or throttling is required. High reliability is also insured because the liquid chemicals are stable for long periods of time, and no ignition system is required — the fuel and oxidizer simply need to be brought together. These propellants have relatively high vapor pressures, are toxic, and may be carcinogenic. A pool of the liquid will pose a health, fire, or explosion hazard. Therefore, missiles containing these propellants are stored and shipped in canisters that contain a sensor to detect the leakage of these propellants that will sound an alarm at a set concentration. This paper discusses the development of an automated system that is designed to mitigate a leak of the fuel or oxidizer within the canister in order to render the system safe enough to allow access to the missile. The mitigation system neutralizes the leaked propellant. The design and testing of the system with representative propellants is discussed.
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Notardonato, W., G. Haddad, K. V. Krishna-Murty, J. Zhu, J. S. Kapat, and L. C. Chow. "Miniature Joule–Thomson (JT) Cryocoolers for Propellant Management." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-61545.

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Boil-off of cryogenic propellants is an issue of concern in any space mission. There could be boil-off of liquid propellants in the cryogenic storage tank, transfer line or in the space vehicle external tank itself due to heat leak. The current insulation technology uses a multilayered thermal protective coating of 304 Stainless Steel and Welded Invar, which allows the propellant to withstand the extreme internal and external temperature variations generated during pre-launch, launch, and flight operations, which does not provide for zero boil-off (ZBO). Usage of a cryocooler to prevent propellant boil-off would potentially reduce the launch costs. Owing to its attractive features like simplicity, compactness and rapid cool-down characteristics, an innovative concept of using Joule-Thomson (JT) cryocoolers for prechilling, densification and ZBO applications of cryogenic propellants is focused upon. The liquid oxygen propellant transfer line at NASA Kennedy Space Center is considered for demonstration of the above concept. Various thermodynamic cycle parameters are optimized for the cryocooler to make the demonstration possible. Cycle optimization is done also taking into account the feasibility to develop some crucial components for the JT cryocooler like a micro channel heat recuperator and cold heads. Current state of developments in the heat exchanger is briefly described. Some advantages of using miniaturized cryocoolers in launch vehicle operations are also discussed.
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Du, J., C. Pu, and Z. Xiao. "STUDY ON INFLUENCE OF MATCHING BETWEEN COMBUSTIBLE CARTRIDGE CASE AND GUN PROPELLANT BURNING RATE ON INTERNAL BALLISTIC PERFORMANCE." In 34th International Symposium on Ballistics. Destech Publications, Inc., 2025. https://doi.org/10.12783/ballistics25/37121.

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The matching between the combustible cartridge case (CCC) and gun propellant burning rate plays an important role in interior ballistic performance of charge since there is a large difference between their burning rate coefficients. This paper investigated the burning process and determined the burning rate coefficients of CCC and gun propellants using closed bomb test. The characteristic parameter, such as composition, thickness, and porosity of the CCC significantly affected the burning rate coefficient. The relationship between the burning rate coefficient of the CCC, maximum chamber pressure and muzzle velocity of 105mm tank gun propellant charge can be calculated through interior ballistic code. For a certain gun propellant, the expected interior ballistic performance can be obtained through a good match between the CCC and gun propellant burning rate coefficient. Compared to CCC with higher burning rate coefficient, the coefficient in the range of 5 to 6 mm·MPa⁻¹·s⁻¹ of CCC exhibits better matching property with 14/19 TEGDN gun propellants in 105mm gun firing and its suitable characteristic parameters are determined by an established model further. This study demonstrated the significance and strategy of match between CCC and gun propellant burning rate coefficient.
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10

Petrović, Vesna, Slaviša Stojiljković, and Jelena Šultans. "Calculation of safe diametar of propellants using heat flow measurements." In 11th International Scientific Conference on Defensive Technologies - OTEX 2024. Military Technical Institute, Belgrade, 2024. http://dx.doi.org/10.5937/oteh24044p.

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By using experimental and theorethical work, it has been made procedure in order to use microcalorimetar heat flow data to calculate safe diametar. For calculation of safe diametar two equations have been used. Calculated results were compared. If calculated value of safe diametar is comparated with diametar of ammunition loading charge, one can make assessment whether ammunition storage is safe or not. This propellant testing has great importance for chemical stability evaluation of propellants. Microcalorimetric system, whether "TAM III" or "TAM IV" is used, gives heat flow data in terms of released heat quantityat elevated temperaturesr. Calculation of safe diameter is important in preventing accidents due to selfignition of propellants.
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Reports on the topic "Propellants"

1

Nelson, H. H. NRL Boron Propellants Combustion Program. Defense Technical Information Center, 1988. http://dx.doi.org/10.21236/ada201242.

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2

Cramer, Michael, Jeff Akester, and William Fawcett. Environmentally Friendly Advanced Gun Propellants. Defense Technical Information Center, 2004. http://dx.doi.org/10.21236/ada447212.

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3

Field, J. E., N. K. Bourne, and S. M. Walley. Impact Ignition of Liquid Propellants. Defense Technical Information Center, 1992. http://dx.doi.org/10.21236/ada252299.

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4

Strakovskiy, Leonid, Arthur Cohen, Robert Fifer, Richard Beyer, and Brad Forch. Laser Ignition of Propellants and Explosives. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada348616.

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Ravi-Chandar, K. Mixed-Mode Fracture of Solid Propellants. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada351742.

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Herrera, W., G. Grelecki, and W. Seals. Hazard Classification Testing of Liquid Propellants. Defense Technical Information Center, 1990. http://dx.doi.org/10.21236/ada222070.

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Law, Chung K. Ignition and Combustion of Liquid Propellants. Defense Technical Information Center, 1990. http://dx.doi.org/10.21236/ada224150.

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8

Hoffman, Harry J. High-Strain Rate Testing of Gun Propellants. Defense Technical Information Center, 1988. http://dx.doi.org/10.21236/ada208826.

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9

Branch, Melvyn C. Nonsteady Combustion Mechanisms of Advanced Solid Propellants. Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada329767.

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Bartlett, Rodney J. Identification and Synthesis of High Nitrogen Propellants. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada415159.

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