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Relevant bibliographies by topics / Composite propellants

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Academic literature on the topic 'Composite propellants'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 June 2024

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Journal articles on the topic "Composite propellants"

1

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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2

Poryazov, V. A., K. M. Moiseeva, and A. Yu Krainov. "NUMERICAL SIMULATION OF COMBUSTION OF THE COMPOSITE SOLID PROPELLANT CONTAINING BIDISPERSED BORON POWDER." Vestnik Tomskogo gosudarstvennogo universiteta. Matematika i mekhanika, no. 72 (2021): 131–39. http://dx.doi.org/10.17223/19988621/72/11.

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A problem of combustion of the composite solid propellants containing various powders of metals and non-metals is relevant in terms of studying the effect of various compositions of powders on the linear rate of propellant combustion. One of the lines of research is to determine the effect of the addition of a boron powder on the burning rate of a composite solid propellant. This work presents the results of numerical simulation of combustion of the composite solid propellant containing bidispersed boron powder. Physical and mathematical formulation of the problem is based on the approaches of the mechanics of two-phase reactive media. To determine the linear burning rate, the Hermance model of combustion of composite solid propellants is used, based on the assumption that the burning rate is determined by mass fluxes of the components outgoing from the propellant surface. The solution is performed numerically using the breakdown of an arbitrary discontinuity algorithm. The dependences of the linear burning rate of the composite solid propellant on the dispersion of the boron particles and gas pressure above the propellant surface are obtained. It is shown that the burning rate of the composite solid propellant with bidispersed boron powder changes in contrast to that of the composite solid propellant with monodispersed powder. This fact proves that the powder dispersion should be taken into account when solving the problems of combustion of the composite solid propellants containing reactive particles.

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Jayaraman, Kandasamy, Ponnurengam Malliappan Sivakumar, Ali Zarrabi, R. Sivakumar, and S. Jeyakumar. "Combustion Characteristics of Nanoaluminium-Based Composite Solid Propellants: An Overview." Journal of Chemistry 2021 (May 19, 2021): 1–12. http://dx.doi.org/10.1155/2021/5520430.

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The nanosized powders have gained attention to produce materials exhibiting novel properties and for developing advanced technologies as well. Nanosized materials exhibit substantially favourable qualities such as improved catalytic activity, augmentation in reactivity, and reduction in melting temperature. Several researchers have pointed out the influence of ultrafine aluminium (∼100 nm) and nanoaluminium (<100 nm) on burning rates of the composite solid propellants comprising AP as the oxidizer. The inclusion of ultrafine aluminium augments the burning rate of the composite propellants by means of aluminium particle’s ignition through the leading edge flames (LEFs) anchoring above the interfaces of coarse AP/binder and the binder/fine AP matrix flames as well. The sandwiches containing 15% of nanoaluminium solid loading in the binder lamina exhibit the burning rate increment of about 20–30%. It was noticed that the burning rate increment with nanoaluminium is around 1.6–2 times with respect to the propellant compositions without aluminium for various pressure ranges and also for different micron-sized aluminium particles in the composition. The addition of nano-Al in the composite propellants washes out the plateaus in burning rate trends that are perceived from non-Al and microaluminized propellants; however, the burning rates of nanoaluminized propellants demonstrate low-pressure exponents at the higher pressure level. The contribution of catalysts towards the burning rate in the nanoaluminized propellants is reduced and is apparent only with nanosized catalysts. The near-surface nanoaluminium ignition and diffusion-limited nano-Al particle combustion contribute heat to the propellant-regressing surface that dominates the burning rate. Quench-collected nanoaluminized propellant residues display notable agglomeration, although a minor percentage of the agglomerates are in the 1–3 µm range; however, these are within 5 µm in size. Percentage of elongation and initial modulus of the propellant are decreased when the coarse AP particles are replaced by aluminium in the propellant composition.

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Aziz, Amir, Rizalman Mamat, Wan Khairuddin Wan Ali, and Mohd Rozi Mohd Perang. "Review on Typical Ingredients for Ammonium Perchlorate Based Solid Propellant." Applied Mechanics and Materials 773-774 (July 2015): 470–75. http://dx.doi.org/10.4028/www.scientific.net/amm.773-774.470.

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Ammonium perchlorate (AP) based solid propellant is a modern solid rocket propellant used in various applications. The combustion characteristics of AP based composite propellants were extensively studied by many research scholars to gain higher thrust. The amount of thrust and the thrust profile, which may be obtained from a specific grain design, is mainly determined by the propellant composition and the manufacturing process that produces the solid propellant. This article is intended to review and discuss several aspects of the composition and preparation of the solid rocket propellant. The analysis covers the main ingredients of AP based propellants such as the binder, oxidizer, metal fuel, and plasticizers. The main conclusions are derived from each of its components with specific methods of good manufacturing practices. In conclusion, the AP based solid propellant, like other composite propellants is highly influenced by its composition. However, the quality of the finished grain is mainly due to the manufacturing process.

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Hu, Zhenyuan, Kaining Zhang, Qiqi Liu, and Chunguang Wang. "NEPE Propellant Mesoscopic Modeling and Damage Mechanism Study Based on Inversion Algorithm." Materials 17, no. 6 (2024): 1289. http://dx.doi.org/10.3390/ma17061289.

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To accurately characterize the mesoscopic properties of NEPE (Nitrate Ester Plasticized Polyether) propellant, the mechanical contraction method was used to construct a representative volume element (RVE) model. Based on this model, the macroscopic mechanical response of NEPE propellant at a strain rate of 0.0047575 s−1 was simulated and calculated, and the parameters of the cohesive zone model (CZM) were inversely optimized using the Hooke–Jeeves algorithm by comparing the simulation results with the results of the uniaxial tensile test of NEPE propellants. Additionally, the macroscopic mechanical behavior of NEPE composite solid propellants at strain rates of 0.00023776 s−1 and 0.023776 s−1 was also predicted. The mesoscopic damage evolution process of NEPE propellants was investigated by the established model. The study results indicate that the predicted curves are relatively consistent with the basic features and change trends of the test curves. Therefore, the established model can effectively simulate the mesoscopic damage process of NEPE composite solid propellants and their macroscopic mechanical properties.

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Liu, Ya Hao, Jian Zheng, Gui Bo Yu, et al. "Graphene-based Composites for the Thermal Decomposition of Energetic Materials." Materials Science Forum 1027 (April 2021): 123–29. http://dx.doi.org/10.4028/www.scientific.net/msf.1027.123.

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Owing to its remarkable mechanical, electrical and thermal properties, graphene has been a hot area of composites research in the past decade, including the field of energetic materials. Graphene has been widely applied in enhancing the physical properties of energetic materials, such as solid composite propellants. Through the way of adding different forms of graphene into the matrix of solid propellants, their thermal decomposition performance can be effectively improved. In this paper, we reviewed the status and challenges of the application of graphene in the thermal decomposition of composite solid propellant. Moreover, the main preparation methods and material structures of graphene are reviewed. We can conclude that graphene and its derivatives can enhance the catalytic effect remarkably, which can be attributed to the large specific surface area of graphene that makes the uniformly dispersed catalyst particles and the more catalyst active sites. Meanwhile, graphene possesses the high thermal conductivity, making the rapider heat diffusion, which can promote the decomposition reactions of the energetic components in solid propellants. Graphene and catalyst work synergistically in their thermal decomposition. More than this, the main methods to improve the thermal decomposition of energetic components of composite propellants and their effects on decomposition temperature reduction are systematically summarized, respectively.

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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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Lin, Guomin, Yixue Chang, Yu Chen, et al. "Synthesis of a Series of Dual-Functional Chelated Titanate Bonding Agents and Their Application Performances in Composite Solid Propellants." Molecules 25, no. 22 (2020): 5353. http://dx.doi.org/10.3390/molecules25225353.

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Titanate-based bonding agents are a class of efficient bonding agents for improving the mechanical properties of composite solid propellants, a kind of special composite material. However, high solid contents often deteriorate the rheological properties of propellant slurry, which limits the application of bonding agents. To solve this problem, a series of long-chain alkyl chelated titanate binders, N-n-octyl-N, N-dihydroxyethyl-lactic acid-titanate (DLT-8), N-n-dodecyl-N, N-dihydroxyethyl-lactic acid-titanate (DLT-12), N-n-hexadecyl-N, N-Dihydroxyethyl-lactic acid-titanate (DLT-16), were designed and synthesized in the present work. The infrared absorption spectral changes of solid propellants caused by binder coating and adhesion degrees of the bonding agents on the oxidant surface were determined by micro-infrared microscopy (MIR) and X-ray photoelectron spectroscopy (XPS), respectively, to characterize the interaction properties of the bonding agents with oxidants, ammonium perchlorate (AP) and hexogen (RDX), in solid propellants. The further application tests suggest that the bonding agents can effectively interact with the oxidants and effectively improve the mechanical and rheological properties of the four-component hydroxyl-terminated polybutadiene (HTPB) composite solid propellants containing AP and RDX. The agent with longer bond chain length can improve the rheological properties of the propellant slurry more significantly, and the propellant of the best mechanical properties was obtained with DLT-12, consistent with the conclusion obtained in the interfacial interaction study. Our work has provided a new method for simultaneously improving the processing performance and rheological properties of propellants and offered an important guidance for the bonding agent design.

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Hoque, Ehtasimul, Chandra Shekhar Pant, and Sushanta Das. "Study on Friction Sensitivity of Passive and Active Binder based Composite Solid Propellants and Correlation with Burning Rate." Defence Science Journal 70, no. 2 (2020): 159–65. http://dx.doi.org/10.14429/dsj.70.14802.

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 Friction sensitivity of composite propellants and their ingredients is of significant interest to mitigate the risk associated with the accidental initiation while processing, handling, and transportation. In this work, attempts were made to examine the friction sensitivity of passive binder: Hydroxy Terminated Polybutadiene/Aluminium/Ammonium Perchlorate and active binder: (Polymer + Nitrate Esters)/Ammonium Perchlorate/Aluminium/Nitramine based composite propellants by using BAM Friction Apparatus. As per the recommendation of NATO standard STANAG–4487, the friction sensitivity was assessed by two methods: Limiting Frictional load and Frictional load for 50% probability of initiation (F50). The test results showed that the active binder based formulations were more vulnerable to frictional load as compared to the formulations with passive binders. Examination of a comprehensive set of propellant compositions revealed that the particle size distribution of Ammonium Perchlorate and burn rate catalysts were the most influential factors in dictating the friction sensitivity for HTPB/Al/AP composite propellants. For active binder/AP/Al/Nitramine composite propellants, the formulation with RDX was found more friction sensitive with a sensitivity value of 44 N as compared to its HMX analog (61 N). The correlation studies of friction sensitivity, burning rate, and thermal decomposition characteristics of HTPB/Al/AP composite propellants is described.

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Junqueira Pimont, Lia, Paula Cristina Gomes Fernandes, Luiz Fernando de Araujo Ferrão, Marcio Yuji Nagamachi, and Kamila Pereira Cardoso. "Study on the Mechanical Properties of Solid Composite Propellant Used as a Gas Generator." Journal of Aerospace Technology and Management, no. 1 (January 21, 2020): 7–10. http://dx.doi.org/10.5028/jatm.etmq.65.

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A gas generating propellants are used as initiators of liquid rocket propellants turbopumps and have as desired characteristic a high-volume production of low-temperature gas. In this context, some formulations of composite propellant containing polyurethane (based on liquid hydroxyl-terminated polybutadiene), guanidine nitrate, ammonium perchlorate, and additives were evaluated and characterized in order to verify their potential as gas generator propellant, as well as to evaluate the influence of additives on mechanical properties. The formulations were prepared, analyzed, and tested for mechanical properties.

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Dissertations / Theses on the topic "Composite propellants"

1

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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Wingborg, Niklas. "Improving the Mechanical Properties of Composite Rocket Propellants." Licentiate thesis, KTH, Fibre and Polymer Technology, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-1794.

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<p>Solid composite rocket propellants usually contain ammoniumperchlorate embedded in an elastic polymer binder. The bindercan be based on a liquid prepolymer such as hydroxyl-terminatedpolybutadiene, HTPB, or poly(3-nitratomethyl-3-methyl oxetane,PolyNIMMO. HTPB is today widely used for this purpose whereasPolyNIMMO has not yet found its way to an application. Bothprepolymers can be cured with diisocyanates to formpolyurethane rubber, yielding solid and elastic rocketpropellants. It is essential that the solid propellant has goodmechanical properties to ensure that the rocket will perform asintended. The propellant must also retain its elasticproperties down to the minimum service temperature and thus alow glass transition temperature is important. In fact, themajor cause of failure of solid rocket motors is linked to themechanical properties of the propellants. HTPB has a very lowglass transition temperature but in some applications itstensile strength is insufficient. PolyNIMMO, on the other hand,has too high a glass transition temperature and a suitableplasticizer is needed. The purpose of this work is to increasethe knowledge of the mechanical properties of polymers bystudying how to increase the tensile strength of HTPB and howto decrease the glass transition temperature of PolyNIMMO.</p><p>The tensile strength of HTPB was studied by increasing thehard segment content, 1,4-butanediol and 1,4-cyclohexanedimethanol being used as chain extenders. The materials werecrosslinked with either isophorone diisocyanate,1,6-hexamethylene diisocyanate or dicyclohexylmethane4,4'-diisocyanate. The results show that the tensile strengthincrease strongly with the addition of up to two moles of diolper mole HTPB. The highest tensile strength was obtained byusing dicyclohexylmethane 4,4'-diisocyanate and1,4-butanediol.</p><p>The depression of the glass transition temperature ofPolyNIMMO was studied by using a new energetic plasticizer,2,2-dinitro-1,3-bis-nitrooxy-propane. Two commercial energeticplasticizers, namely bis(2,2-dinitropropyl) acetal/formal andN-N-butyl-N-(2-nitroxy-etyl)nitramine were used for comparison.2,2-Dinitro-1,3-bis-nitrooxy-propane andN-N-butyl-N-(2-nitroxy-etyl)nitramine were found to interactstrongly with PolyNIMMOand they were thus very effective inlowering the glass transition temperature.Bis(2,2-dinitropropyl) acetal/formal on the other hand was noteffective, and the depression of the glass transitiontemperature in this case was due only to dilution of thesample.</p>

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3

Caro, Rodrigo. "Hydroxy-terminated polyether binders for composite rocket propellants." Thesis, Cranfield University, 2007. http://dspace.lib.cranfield.ac.uk/handle/1826/1637.

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Propellants based on cross-linked Hydroxy Terminated PolyEther (HTPE) binders are being used as alternatives to Hydroxy Terminated PolyButadiene (HTPB) compositions. HTPE propellants have similar mechanical properties to HTPB propellants but they give a less severe response in ‘slow cook-off’ tests for IM compliance. A literature review is presented on the development and properties of HTPE propellants in an attempt to place them in relation to recent trends in Insensitive Munitions. To gain a better understanding of the behaviour of HTPE propellants an HTPE pre-polymer and a range of binder network samples with different NCO/OH equivalence ratios, with and without plasticizer, have been synthesised and characterised by a range of techniques. The thermal decomposition of the HTPE binder network and propellant samples were also studied. Desmodur N-3200 was used as a curing agent and n-BuNENA as an energetic plasticizer. Similar analyses were performed on analogous HTPB pre-polymer and binder network samples and the results were compared with those obtained for the corresponding HTPE samples. Two kinds of HTPE propellant were manufactured containing HTPE pre-polymer, n-BuNENA, 2NDPA and either AP or AP+PSAN as oxidiser. Also HTPB propellant was prepared. Small cook-off test vehicles (SCTV) were filled with HTPE and HTPB propellants and slow cook-off tests were performed. In contrast to HTPB binders, which become harder during slow heating, it was found that the HTPE binders soften under the same conditions. This behaviour is possibly due to chain scission of the soft and hard segments of the HTPE polymer matrix. Thermooxidative processes and reactions of the energetic plasticizer decomposition products are believed to be the responsible for the scission of the polymeric matrix. From the binder characterisation and slow cook-off results it is concluded that there is a relation between the degree of polymeric matrix scission during slow heating and the violence of the response at the point of self ignition. This underlies the main difference between HTPB and HTPE propellants in slow cook-off. While HTPB compositions become harder and more brittle, HTPE propellants become softer and have a lower surface area at the self ignition point.

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4

Caro, R. "Hydroxy-terminated polyether binders for composite rocket propellants." Thesis, Cranfield University, 2007. http://hdl.handle.net/1826/1637.

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Propellants based on cross-linked Hydroxy Terminated PolyEther (HTPE) binders are being used as alternatives to Hydroxy Terminated PolyButadiene (HTPB) compositions. HTPE propellants have similar mechanical properties to HTPB propellants but they give a less severe response in ‘slow cook-off’ tests for IM compliance. A literature review is presented on the development and properties of HTPE propellants in an attempt to place them in relation to recent trends in Insensitive Munitions. To gain a better understanding of the behaviour of HTPE propellants an HTPE pre-polymer and a range of binder network samples with different NCO/OH equivalence ratios, with and without plasticizer, have been synthesised and characterised by a range of techniques. The thermal decomposition of the HTPE binder network and propellant samples were also studied. Desmodur N-3200 was used as a curing agent and n-BuNENA as an energetic plasticizer. Similar analyses were performed on analogous HTPB pre-polymer and binder network samples and the results were compared with those obtained for the corresponding HTPE samples. Two kinds of HTPE propellant were manufactured containing HTPE pre-polymer, n-BuNENA, 2NDPA and either AP or AP+PSAN as oxidiser. Also HTPB propellant was prepared. Small cook-off test vehicles (SCTV) were filled with HTPE and HTPB propellants and slow cook-off tests were performed. In contrast to HTPB binders, which become harder during slow heating, it was found that the HTPE binders soften under the same conditions. This behaviour is possibly due to chain scission of the soft and hard segments of the HTPE polymer matrix. Thermooxidative processes and reactions of the energetic plasticizer decomposition products are believed to be the responsible for the scission of the polymeric matrix. From the binder characterisation and slow cook-off results it is concluded that there is a relation between the degree of polymeric matrix scission during slow heating and the violence of the response at the point of self ignition. This underlies the main difference between HTPB and HTPE propellants in slow cook-off. While HTPB compositions become harder and more brittle, HTPE propellants become softer and have a lower surface area at the self ignition point.

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5

Beiter, Christopher A. "The role of the combustion zone microstructure in the pressure-coupled response of composite propellants." Diss., Georgia Institute of Technology, 1991. http://hdl.handle.net/1853/12539.

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Tanaka, Martin Lyn. "Influence of storage environment upon crack opening and growth in composite solid rocket propellant." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-01242009-063016/.

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7

Rettenmaier, Andrew Karl. "Experimental evaluation of erosive burning in composite propellants - effect of binder." Purdue University, 2013.

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Draper, Robert. "Novel Nanostructures and Processes for Enhanced Catalysis of Composite Solid Propellants." Master's thesis, University of Central Florida, 2013. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/5929.

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The purpose of this study is to examine the burning behaviour of composite solid propellants (CSP) in the presence of nanoscale, heterogenous catalysts. The study targets the decomposition of am- monium perchlorate (AP) as a key component in the burning profile of these propellants, and seeks to identify parameters of AP decomposition reaction that can be affected by catalytic additives. The decomposition behavior of AP was studied in the presence of titanium dioxide nanoparticles in varying configurations, surface conditions, dopants, morphology, and synthesis parameters with the AP crystals. The catalytic nanoparticles were found to enhance the decomposition rate of the ammonium perchlorate, and promote an accelerated burning rate of CSP propellants containing the additives. Furthermore, different configurations were shown to have varying degrees of effec- tiveness in promoting the decomposition behaviour. To study the effect of the catalyst's configuration in the bulk propellant, controlled dispersion con- ditions of the nanoparticle catalysts were created and studied using differential scanning calorime- try, as well as model propellant strand burning. The catalysts were shown to promote the greatest enthalpy of reaction, as well as the highest burn rate, when the AP crystals were recrystalized around the nanoparticle additives. This is in contrast to the lowest enthalpy condition, which cor- responded to catalysts being dispersed upon the AP crystal surface using bio-molecule templates. Additionally, a method of facile, visible light nanoparticle tracking was developed to study the effect of mixing and settling parameters on the nano-catalysts. To accomplish this, the titania nanoparticles were doped with fluorescent europium molecules to track the dispersion of the cat- alysts in the propellant binder. This method was shown to succesfully allow for dispersion and agglomeration monitoring without affecting the catalytic effect of the TiO2 nanoparticles.<br>M.S.M.S.E.<br>Masters<br>Materials Science Engineering<br>Engineering and Computer Science<br>Materials Science and Engineering

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Yesilirmak, Yener. "Determination Of Degree Of Mixing In Solid Rocket Propellants." Master's thesis, METU, 2006. http://etd.lib.metu.edu.tr/upload/2/12607751/index.pdf.

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Composite propellants are mainly composed of: crystalline oxidizer, metallic fuel, and polymeric binder. Additives, such as plasticizers, catalysts, bonding agents and curing agents may also be incorporated to propellant compositions in small amounts. These ingredients should be mixed rigorously in order to obtain a uniform microstructure throughout the cast propellant profile. The quality of the propellant mixture has to be determined quantitatively to improve the product quality and to reduce costs. In this study, it was aimed to develop an easy, cost effective and rapid test method for determining the optimum mixing conditions for the manufacturing process of solid rocket propellants. An analytical method used in the literature for assessing mixing quality in highly filled polymeric systems is wide-angle x-ray diffractometry (WA-XRD). After finding out the concentration distribution of the components indirectly by WA-XRD, degree of mixing was identified using statistical methods. To accomplish this, series of samples were taken from various locations of the mixing chamber and analyzed by WA-XRD. Degree of mixing calculations based on ratio of intensity arising from aluminum phase over total crystal intensity, and the ratio of intensity arising from ammonium perchlorate phase over total crystal intensity gave satisfactory results. Radial mixing efficiency of planetary mixer was determined, and it was found that mixing at the center was more effective than mixing at the outer regions. Also, by scanning electron microscopy technique (SEM), interactions between binder and solid loading during mixing process were observed. It was seen that polymeric matrix gradually encloses solid particles during mixing.

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Grant, Edwin H. "A study of the ignition process of composite solid propellants in a small rocket motor." Princeton University, 2013.

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Books on the topic "Composite propellants"

1

Greatrix, D. R. Normal acceleration model for composite-propellant combustion. [s.n.], 1988.

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Greatrix, D. R. A model for normal acceleration effects on composite propellant combustion. [s.n.], 1989.

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C, Richards M., Thiokol Corporation Space Operations, and George C. Marshall Space Flight Center., eds. RSRM-9 (360L009) final report: Ballistics mass properties. Thiokol Corp., Space Operations, 1990.

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C, Richards M., Thiokol Corporation Space Operations, and George C. Marshall Space Flight Center., eds. RSRM-9 (360L009) final report: Ballistics mass properties. Thiokol Corp., Space Operations, 1990.

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Drendel, Albert S. RSRM-9 (360L009) final report: Ballistics mass properties. Thiokol Corp., Space Operations, 1990.

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S, Gant Frederick, and United States. National Aeronautics and Space Administration., eds. Stress relaxation functions: Methods of approximation:final report. Dept. of Mechanical and Aerospace Engineering, The University of Alabama in Huntsville, 1994.

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Gill, M. TP-H1148 knitline integrity evaluation: Final report. Thiokol Corp., Space Operations, 1990.

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Gill, M. TP-H1148 knitline integrity evaluation: Final report. Thiokol Corp., Space Operations, 1990.

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Kumar, Ramohalli, and United States. National Aeronautics and Space Administration., eds. Composite solid propellant predictability and quality assurance: Meeting report, April 21, 1989. University of Arizona, 1989.

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Greatrix, D. R. Erosive burning model for composite-propellant rocket motors with large length-to-diameter ratios. [s.n.], 1987.

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Book chapters on the topic "Composite propellants"

1

Salko, A. J., A. P. Denisjuk, Yu G. Shepelev, and A. B. Vorozhtsov. "Utilization of Composite Propellants with Obtaining Specific Products." In Application of Demilitarized Gun and Rocket Propellants in Commercial Explosives. Springer Netherlands, 2000. http://dx.doi.org/10.1007/978-94-011-4381-3_24.

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Weiser, Volker, Andrea Franzin, Luigi T. DeLuca, et al. "Combustion Behavior of Aluminum Particles in ADN/GAP Composite Propellants." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_10.

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Machacek, O., G. Eck, and K. Tallent. "Class 1.3 Composite Propellants as Ingredients in Commercial Explosives — the UTEC Experience." In Application of Demilitarized Gun and Rocket Propellants in Commercial Explosives. Springer Netherlands, 2000. http://dx.doi.org/10.1007/978-94-011-4381-3_1.

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Pang, Wei Qiang, Luigi T. DeLuca, Hui Xiang Xu, Xue Zhong Fan, Feng Qi Zhao, and Wu Xi Xie. "Effects of Dual Oxidizers on the Properties of Composite Solid Rocket Propellants." In Chemical Rocket Propulsion. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27748-6_17.

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Isert, Sarah, and Steven F. Son. "The Relationship Between Flame Structure and Burning Rate for Ammonium Perchlorate Composite Propellants." In Challenges and Advances in Computational Chemistry and Physics. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-59208-4_6.

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Katikani, Kishore Kumar, A. Venu Gopal, and Venkateseara Rao Vemana. "Optimization of Machining Parameters for Multi-performance Characteristics in Milling of Composite Solid Propellants Using RSM." In Advances in Applied Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-1201-8_75.

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Mezroua, Abderrahmane, Michel H. Lefebvre, Djalal Trache, and Kamel Khimeche. "Burning Rate of PVC—Plastisol Composite Propellants and Correlation Between Closed Vessel and Strand Burner Tests Data." In Innovative Energetic Materials: Properties, Combustion Performance and Application. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-4831-4_12.

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Jayaraman, K., and G. Boopathy. "Aluminum Agglomerate Size Measurements in Composite Propellant Combustion." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-1771-1_47.

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Traissac, Y., J. Ninous, R. Neviere, and J. Pouyet. "Mechanical Behavior of a Solid Composite Propellant During Motor Ignition." In Advances in Chemistry. American Chemical Society, 1996. http://dx.doi.org/10.1021/ba-1996-0252.ch014.

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Kang, Sang Guk, Myung Gon Kim, Sang Wuk Park, Chun Gon Kim, and Cheol Won Kong. "Liquid Nitrogen Storing and Pressurization Test of a Type III Cryogenic Propellant Tank." In Advances in Composite Materials and Structures. Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-427-8.397.

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Conference papers on the topic "Composite propellants"

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Fitzgerald, R. P., and M. Q. Brewster. "Validation of Composite Propellant Combustion Modeling Using Laminate Propellants." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4628.

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Welland, Willianne, Antoine van der Heijden, Stefano Cianfanelli, and Lawrence Batenburg. "Improvement of HNF and Propellant Characteristics of HNF-Based Composite Propellants." In 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-5764.

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Franson, C., O. Orlandi, C. Perut, et al. "New high energetic composite propellants for space applications: refrigerated solid propellant." In Progress in Propulsion Physics. EDP Sciences, 2009. http://dx.doi.org/10.1051/eucass/200901031.

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MARINE, MICKY, and KUMAR RAMOHALLI. "Processing experiments on model composite propellants." In 26th Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2313.

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Weber, Jason, Matthew Culley, and Quinn Brewster. "Radiant Ignition of AP-Composite Propellants." In 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3752.

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Wang, Xiaojian, and Thomas Jackson. "Modeling of Aluminized Composite Solid Propellants." In 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-4041.

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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:

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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Maggi, Filippo, Francesco Miccio, Luciano Galfetti, and Luigi T. De Luca. "Flame Structure Simulation of Nonaluminized Composite Propellants." In 57th International Astronautical Congress. American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.iac-06-c4.p.3.03.

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Cauty, Franek, and Charles Erades. "Macroscopic heterogeneity of the composite solid propellants." In 37th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3427.

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Fonblanc, Gilles, and Bruno Herran. "The maturity of BUTACENE based composite propellants." In 30th Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-3194.

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Reports on the topic "Composite propellants"

1

Wiegand, Donald A. Constant Critical Strain for Mechanical Failure of Several Particulate Polymer Composite Explosives and Propellants and Other Explosives. Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada327298.

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Mellor, A. M. Workshop on ESD (Electrostatic Discharge) Ignition of Composite Solid Propellants Held on April 18-19, 1989 in Nashville, Tennessee. Defense Technical Information Center, 1990. http://dx.doi.org/10.21236/ada218599.

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Buckmaster, J. Modelling of Composite-Propellant Flames. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada399738.

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Blomshield, F. S. Nitramine Composite Solid Propellant Modelling. Defense Technical Information Center, 1989. http://dx.doi.org/10.21236/ada220198.

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Baron, D. T., C. T. Liu, and T. C. Miller. Subcritical Crack Growth in a Composite Solid Propellant. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada409841.

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Szatkowski, J. L. Design of Composite Material Chambers for Solid Propellant Missile Motors. Defense Technical Information Center, 1985. http://dx.doi.org/10.21236/ada158890.

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Wormhoudt, Joda. Spectrally Analyzed Embedded Infrared Fiber Optic Diagnostic of Advanced Composite Propellant Combustion. Defense Technical Information Center, 2003. http://dx.doi.org/10.21236/ada422571.

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Behrens, R., and L. Minier. The thermal decomposition behavior of ammonium perchlorate and of an ammonium-perchlorate-based composite propellant. Office of Scientific and Technical Information (OSTI), 1998. http://dx.doi.org/10.2172/653952.

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