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Letteratura scientifica selezionata sul tema "Composite propellant"

Autore: Grafiati

Pubblicato: 4 giugno 2021

Ultima modifica: 29 gennaio 2023

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Articoli di riviste sul tema "Composite propellant"

1

Abdullah, Mohamed, F. Gholamian e A. R. Zarei. "Noncrystalline Binder Based Composite Propellant". ISRN Aerospace Engineering 2013 (24 settembre 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 e A. Yu Krainov. "NUMERICAL SIMULATION OF COMBUSTION OF THE COMPOSITE SOLID PROPELLANT CONTAINING BIDISPERSED BORON POWDER". Vestnik Tomskogo gosudarstvennogo universiteta. Matematika i mekhanika, n. 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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3

Aziz, Amir, Rizalman Mamat, Wan Khairuddin Wan Ali e Mohd Rozi Mohd Perang. "Review on Typical Ingredients for Ammonium Perchlorate Based Solid Propellant". Applied Mechanics and Materials 773-774 (luglio 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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4

Hamed, J. O., O. O. Ogunleye e C. A. Osheku. "Optimal design of a composite propellant formulation using response surface methodology". Advances in Materials Science 17, n. 1 (1 marzo 2017): 44–57. http://dx.doi.org/10.1515/adms-2017-0004.

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Abstract (sommario):

Abstract There is a continuous demand for high performance composite propellant formulations to meet mission requirements. The performance of composite propellant formulations can be enhanced by optimizing propellant formulation. However, the main objective of this study is to formulate a composition for composite propellant by optimizing the specific impulse which is the measure of propellant performance. A central composite design (ccd) consisting five ingredients (ammonium nitrate, powdered aluminum, polyester resin, ammonium dichromate and powdered charcoal) at five levels was used to formulate optimum propellant formulation from composite materials of ammonium nitrate based propellant verified for propellant characteristics using propellant performance evaluation programme (propep 3). The responses evaluated are specific impulse, characteristic velocity, density, temperature and molecular weight. Response surface methodology was used to analyze the results of the ccd of the composite formulations. The optimum values for specific impulse, characteristic velocity, density, temperature and molecular weight of the mixture from the surface plot are 212.178 s, 1335.81 m/s, 1640.6 k g/m3, 1968.73 k and 21.7722 g/mol respectively. The optimum predicted specific impulse was 212.178 s at composite composition of 73.61% ammonium nitrate, 4.36% powdered aluminum, 14.39% polyester resin, 5.10% ammonium dichromate and 2.54% powdered charcoal. The propellant optimum composition validated with propep 3 are in good agreement with each other in their accompany propellant characteristics. Therefore, the optimal propellant formulation enhanced the performance of solid propellants.

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5

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

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Ammonium-nitrate-(AN-) based composite propellants prepared with a hydroxyl-terminated polybutadiene (HTPB)/polytetrahydrofuran (PTHF) blend binder have unique thermal decomposition characteristics. In this study, the burning characteristics of AN/HTPB/PTHF propellants are investigated. The specific impulse and adiabatic flame temperature of an AN-based propellant theoretically increases with an increase in the proportion of PTHF in the HTPB/PTHF blend. With an AN/HTPB propellant, a solid residue is left on the burning surface of the propellant, and the shape of this residue is similar to that of the propellant. On the other hand, an AN/HTPB/PTHF propellant does not leave a solid residue. The burning rates of the AN/HTPB/PTHF propellant are not markedly different from those of the AN/HTPB propellant because some of the liquefied HTPB/PTHF binder cover the burning surface and impede decomposition and combustion. The burning rates of an AN/HTPB/PTHF propellant with a burning catalyst are higher than those of an AN/HTPB propellant supplemented with a catalyst. The beneficial effect of the blend binder on the burning characteristics is clarified upon the addition of a catalyst. The catalyst suppresses the negative influence of the liquefied binder that covers the burning surface. Thus, HTPB/PTHF blend binders are useful in improving the performance of AN-based propellants.

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6

Jayaraman, Kandasamy, Ponnurengam Malliappan Sivakumar, Ali Zarrabi, R. Sivakumar e S. Jeyakumar. "Combustion Characteristics of Nanoaluminium-Based Composite Solid Propellants: An Overview". Journal of Chemistry 2021 (19 maggio 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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7

Yao, Er Gang, Feng Qi Zhao, Si Yu Xu, Rong Zu Hu, Hui Xiang Xu e Hai Xia Hao. "Combustion Characteristics of Composite Solid Propellants Containing Different Coated Aluminum Nanopowders". Advanced Materials Research 924 (aprile 2014): 200–211. http://dx.doi.org/10.4028/www.scientific.net/amr.924.200.

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Aluminum nanopowders coated with oleic acid (nmAl+OA), perfluorotetradecanoic acid (nmAl+PA) and nickel acetylacetonate (nmAl+NA) were prepared. The combustion characteristics of hydroxyl terminated polybutadiene (HTPB) composite solid propellants containing different coated aluminum nanpowders were investigated. The result shows that the burning rate of the propellant sample containing nmAl+NA is the highest at different pressure, the maximum burning rate is up to 26.13 mm·s-1at 15 MPa. The burning rates of propellant samples containing nmAl+OA and nmAl+PA are almost the same at different pressures, and higher than the propellant samples containing untreated aluminum nanopowders only at the pressure range of 10 ~ 15 MPa. The flame brightness of different propellants under different pressure is not the same. The flame brightness is increased with the pressure increasing. The flame center zone brightness of the propellant containing nmAl+PA and nmAl+NA is brighter under 4 MPa, and the brightness of nmAl+NA is the brightest. The surface coating of aluminum nanopowder has little effect on the combustion flame temperature of solid propellant. The burning surface temperature increases with the pressure increasing.

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8

Runtu, Khevinadya Ramadhani, Wahyu Sri Setiani e Mala Utami. "Application Energetic Materials for Solid Composite Propellant to Support Defense Rocket Development". International Journal of Social Science Research and Review 6, n. 1 (6 gennaio 2023): 153–59. http://dx.doi.org/10.47814/ijssrr.v6i1.756.

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In its application in space technology, solid composite propellants are often used as fuel in rockets for military purposes. Increasing the energy of the propellant is carried out by observing two stages, the use of energetic materials and improvements to the process technology. The current development of propellant technology makes it possible to use new energetic materials, simple formulations, high energy, and smokeless. The purpose of this research is to find out developments related to the use of highly energetic materials as raw materials for composite propellants for defense rockets at the Rocket Technology Research Center, ORPA-BRIN. This study uses qualitative analysis methods with research designs in the literature studies and simulation results. In the context of mastering rocket propellant technology in Indonesia, the application of highly energetic materials is expected to be able to solve the problem of rocket propulsion performance. Currently, the Rocket Technology Research Center, ORPA-BRIN is developing a smokeless propellant composite with a composition based on the energetic materials AP/HTPB/Al and an oxidizing agent RDX. From the results of the combustion simulation software ProPEP and RPA, it shows that the composition of the resulting combustion gaseous (Al2O3 and HCl) shows a decrease when using RDX energetic material-based propellant. It's known that RDX can significantly reduce smoke in propellant combustion products. The application of the new highly energetic materials compound is expected to significantly solve the problem of solid rocket propulsion performance.

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9

Cui, Huiru, Xuan Lv, Yurong Xu, Zhiwen Zhong, Zixiang Zhou e Weili Ma. "A Step-by-Step Equivalent Microprediction Method for the Mechanical Properties of Composite Solid Propellants considering Dewetting Damage". International Journal of Aerospace Engineering 2022 (14 febbraio 2022): 1–12. http://dx.doi.org/10.1155/2022/2427463.

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Reliable prediction of the macromechanical properties of composite solid propellants in the microscale can accelerate the development of propellants with high mechanical properties. According to the characteristics of the composition ratio of a four-component hydroxyl-terminated polybutadiene (HTPB) propellant with the component ammonium perchlorate (AP), hydroxyl-terminated polybutadiene, aluminum powder (AL), and cyclotrimethylenetrinitramine (or RDX for short), an improved random delivery algorithm was developed to separately model filler particles with the different sizes. A step-by-step equivalent representative volume element (RVE) model was generated to reflect the microstructures of the propellant. The isotropy and uniformity of the RVE model were also tested using a two-point probability function. The Park-Paulino-Roesler (PPR) cohesive model was introduced to simulate the particle debonding (or dewetting) in solid propellant. The stress-strain curves of the propellant were obtained by the macroscopic test with the extension rate 200 mm/min at different temperatures. Based on these experimental data, the 8 characteristic parameters suitable for the microinterface of the propellant were obtained by using an inversion optimization method. A microscale finite element prediction model of the propellant considering dewetting damage was constructed to study the evolution process of the microdamage of the propellant. The predicted stress-strain curves of the propellant under different loading conditions were in good agreement with the test results.

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10

Junqueira Pimont, Lia, Paula Cristina Gomes Fernandes, Luiz Fernando de Araujo Ferrão, Marcio Yuji Nagamachi e Kamila Pereira Cardoso. "Study on the Mechanical Properties of Solid Composite Propellant Used as a Gas Generator". Journal of Aerospace Technology and Management, n. 1 (21 gennaio 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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Più fonti

Tesi sul tema "Composite propellant"

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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2

Carro, Rodolphe Valentin. "HIGH PRESSURE TESTING OF COMPOSITE SOLID ROCKET PROPELLANT MIXTURES: BURNER FACILITY CHARACTERIZATION". Master's thesis, University of Central Florida, 2007. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/3204.

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Abstract (sommario):

Much Research on composite solid propellants has been performed over the past few decades and much progress has been made, yet many of the fundamental processes are still unknown, and the development of new propellants remains highly empirical. Ways to enhance the performance of solid propellants for rocket and other applications continue to be explored experimentally, including the effects of various additives and the impact of fuel and oxidizer particle sizes on burning behavior. One established method to measure the burning rate of composite propellant mixtures in a controlled laboratory setting is to use a constant-volume pressure vessel, or strand burner. To provide high-pressure burn rate data at pressures up to 360 atm, the authors have installed, characterized and improved a strand burner facility at the University of Central Florida. Details on the facility and its improvements, the measurement procedures, and the data reduction and interpretation are presented. Two common HTPB/AP propellant mixtures were tested in the original strand burner. The resulting burn rates were compared to data from the literature with good agreement, thus validating the facility and related test techniques, the data acquisition, data reduction and interpretation. After more than 380 successful recordings, an upgraded version of the strand burner, was added to the facility. The details of Strand Burner II, its improvements over Strand Burner I, and its characterization study are presented.
M.S.
Department of Mechanical, Materials and Aerospace Engineering
Engineering and Computer Science
Mechanical Engineering MSME

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3

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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4

Styborski, Jeremy A. "Effects of aluminum and iron nanoparticle additives on composite AP/HTPB solid propellant regression rate". Thesis, Rensselaer Polytechnic Institute, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=1561975.

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

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

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5

Li, Hung-Peng. "Investigation of the Stability of Metallic/Composited-Cased Solid Propellant Rocket Motors under External Pressure". Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/29323.

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Abstract (sommario):

Solid rocket motors consist of a thin metallic or composite shell filled with a soft rubbery propellant. Such motors are vulnerable and prone to buckling due to sudden external pressures produced by nearby detonation. The stability conditions of rocket motors subjected toaxisymmetric, external pressure loading are examined. The outer cases of motors are considered as isotropic (metallic) or anisotropic (composite), thin and high-strength shells, which are the main structures of interest in the stability analyses. The inner, low-strength elastic cores are modeled as linear and nonlinear elastic foundations. A general, refined, Sanders' nonlinear shell theory, which accounts for geometric nonlinearity in the form of von Karman type of nonlinear strain-displacement relations, is used to model thin-walled, laminated,composite cylindrical shells. The first order shear deformable concept is adopted in the analyses to include the transverse shear flexibility of composites. A winkler-type of linear and nonlinear elastic foundation is applied to model the internal foundations. Pasternak-foundation constants are also chosen tomodify the proposed elastic foundation model for the purpose of shear interactions. A set of displacement-based finite element codes have been formulated to determine critical buckling loads and mode shapes. The effect of initial imperfections on the structural responses are also incorporated in the formulations. A variety of numerical examples are investigated to demonstrate the validity and efficiency of the purposed theory under various boundary condiitions and loading cases. First, linear eigenvalue analysis is used to examine approximate buckling loads and buckling modes as well as symmetric conditions. An iterative solution procedure, either Newton-Raphson or Riks-Wempner method is employed to trace the nonlinear equilibrium paths for the cases of stress, buckling and post-buckling analyses. Both ring and shell-type models are applied for the structural analyses with different internal elastic foundations and initial imperfections.
Ph. D.

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6

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.
M.S.M.S.E.
Masters
Materials Science Engineering
Engineering and Computer Science
Materials Science and Engineering

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7

Bohlin, Johannes. "Lifetime prediction of a polymeric propellant binder using the Arrhenius approach". Thesis, Uppsala universitet, Tillämpad materialvetenskap, 2021. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-446609.

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The thermal-oxidative degradation of a crosslinked hydroxy-terminated polybutadiene (HTPB)/cycloaliphatic diisocyanate (H12MDI) based polymer, which is commonly used as a polymeric binder in propellants, is investigated at temperatures from 95°C to 125°C with the aim of estimating the lifetime of the material in storage conditions (20°C) using the Arrhenius approach. Furthermore, the effect of antioxidants and to a lesser extent plasticizer on the degradation process was also studied. Diffusion-limited oxidation (DLO) was theoretically modelled and DLO conditions were estimated by gathering oxygen permeability and consumption data from similar studies. It was concluded that DLO-effects might be present at the highest experiment temperature (125°C) depending on the actual properties of the material investigated. The mechanical degradation was monitored by conducting tensile tests in a DMA apparatus and photographs using a microscope was taken to examine potential DLO effects. The degradation process of the stabilized polymer (with antioxidant) did not showcase Arrhenius behaviour, which was confirmed by the failure to construct a satisfactory mastercurve. This was most likely due to loss of antioxidants, resulting in autocatalytic oxidation(acceleration of the oxidation process). However, the induction period of the stabilized polymer showcased Arrhenius behaviour in the temperature region 95-125°C with an ~E_a = 90 kJ/mol. If the activation energy E_a is assumed to remain constant, the lifetime at ambient temperature (20°C) is predicted to be approximately 176 Years for a 2mm thick sample. However, this is probably an overestimation since curvature in the Arrhenius plot has been observed for many rubber materials in the lower temperature region. Assuming the E_a drops from ~90 kJ/mol to~71 kJ/mol, a more conservative lifetime prediction of 58 Years was estimated.

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8

Lee, Hsing-Juin. "Determination of the complex modulus of a solid propellant and random vibration analysis of the layered viscoelastic cylinders with finite element method". Diss., Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/77816.

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Aeronautical structures, such as aircraft or missiles, are usually highly sophisticated systems often subjected to random vibration environment. Thus, in various design, development, and production stages, laboratory random vibration testing of sampled solid rocket motors on electromagnetic or hydraulic shakers are routinely performed as an important experiment-oriented quality control strategy. Nevertheless, it is crucial to understand the dynamic structural behavior of these layered viscoelastic cylinders such as solid rocket motors under random vibration tests analytically. In this study, a methodology has been developed to deal with the random vibration of a general class of composite structures with frequency-dependent viscoelastic material properties as represented by the example of solid rocket motors. The method combines the finite element method, structural dynamics, strain energy approach, and random vibration analysis concepts. The method is a more powerful technique capable of treating sophisticated random vibration problems with complicated geometry, nonhomogeneous materials, and frequency-dependent stiffness and damping properties. Before the random vibration analysis could proceed, a microcomputer-based dynamic mechanical analyzer system was used together with time-temperature superposition principle to obtain the frequency-dependent dynamic viscoelastic properties of the solid propellant. The strain energy approach has been used to calculate the frequency-dependent equivalent viscoelastic damping which is in turn judiciously represented by a combination of viscous damping and structural damping to accommodate this frequency dependent material property. Modal analysis data together with half power band width calculated at each natural frequency are highly useful guides in the harmonic analysis to achieve computational efficiency. On one hand, the technique used in this study has a hybrid taste in the sense that it makes use of best features and capabilities of both modal analysis and harmonic analysis to achieve the goal of random vibration analysis in addition to the power of finite element technique. The displacement, acceleration and stress power spectra have been obtained for significant points on the rocket model together with their root mean square values. These data can be used for various analyses, testing, design, and other purposes as discussed in later sections of this study.
Ph. D.

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9

Picquart, Marion. "Développement d’une loi de comportement pour les méthodes de dimensionnement des chargements en propergol solide composite". Thesis, université Paris-Saclay, 2020. http://www.theses.fr/2020UPASC019.

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Ces travaux de thèse portent sur le développement d’une loi de comportement viscoélastique non-linéaire pour les propergols solides composites. Une base expérimentale mettant en évidence le comportement à modéliser est construite à l’aide du propergol d’étude. Puis, les origines microscopiques de ce comportement macroscopique sont investiguées, au moyen d’éprouvettes spécialement conçues à cet effet. Les résultats de l’étude montrent que le frottement et la cavitation sont deux mécanismes prépondérants. Les relations mathématiques entre ces micromecanismes et les propriétés mécaniques du matériau sont déterminées par homogénéisation, puis introduites dans un cadre viscoélastique isotrope tridimensionnel. Les paramètres du modèle ainsi obtenu sont identifiés sur la base expérimentale, suite à quoi la loi est capable de restituer la majeure partie des non-linéarités du comportement exprimées sous sollicitations cycliques. Après intégration dans un code de calcul par éléments finis, la loi est finalement validée sur des cas d’application réels. Les résultats montrent qu’une meilleure restitution du comportement du propergol au cours de son cycle de vie permet d’améliorer le dimensionnement des chargements de manière significative
This work describes the development of a viscoelastic nonlinear constitutive law for solid composite propellants. An experimental basis showing the nonlinear behavior expressed by solid propellants is constructed. Then, microscopic sources of this macroscopic behavior are investigated using new samples specifically designed. Results show that friction and cavitation are responsible for the major parts of the nonlinearities. Homogenization is used to determine mathematical relations between these two mechanisms and the mechanical properties of the material. The relations are then integrated in a viscoelastic, isotropic, tridimensional model. Parameters are identified using the experimental basis. The model shows a good ability to reproduce and predict the propellant behavior nonlinearities expressed under cyclic loads. After completion of the development, the model is used into a design method and finite element calculation are performed on real objects. Results validate the new method and show that improving the behavior prediction also improves the design method and generates profits

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10

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

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

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Libri sul tema "Composite propellant"

1

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

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2

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

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3

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

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4

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

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5

Ahmed, Rafiq. Loads analysis and testing of flight configuration solid rocket motor outer boot ring segments. Huntsville, Ala: George C. Marshall Space Flight Center, 1990.

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6

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

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7

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

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8

Composite propellant technology research: Mechanical property characterization : semi-annual report. Huntsville, Ala: Dept. of Mechanical Engineering, College of Engineering, University of Alabama in Huntsville, 1991.

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9

C, Richards M., Thiokol Corporation Space Operations e George C. Marshall Space Flight Center., a cura di. RSRM-9 (360L009) final report: Ballistics mass properties. Brigham City, UT: Thiokol Corp., Space Operations, 1990.

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10

C, Richards M., Thiokol Corporation Space Operations e George C. Marshall Space Flight Center., a cura di. RSRM-9 (360L009) final report: Ballistics mass properties. Brigham City, UT: Thiokol Corp., Space Operations, 1990.

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Capitoli di libri sul tema "Composite propellant"

1

Jayaraman, K., e G. Boopathy. "Aluminum Agglomerate Size Measurements in Composite Propellant Combustion". In Lecture Notes in Mechanical Engineering, 437–45. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-1771-1_47.

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2

Traissac, Y., J. Ninous, R. Neviere e J. Pouyet. "Mechanical Behavior of a Solid Composite Propellant During Motor Ignition". In Advances in Chemistry, 195–210. Washington, DC: American Chemical Society, 1996. http://dx.doi.org/10.1021/ba-1996-0252.ch014.

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3

Kang, Sang Guk, Myung Gon Kim, Sang Wuk Park, Chun Gon Kim e Cheol Won Kong. "Liquid Nitrogen Storing and Pressurization Test of a Type III Cryogenic Propellant Tank". In Advances in Composite Materials and Structures, 397–400. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-427-8.397.

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4

He, Ning, Cong Xiang, Bin Qin e Qi Zhang. "Calculation of TNT Equivalence of Composite Propellant and Visualized Software Development". In Lecture Notes in Computer Science, 161–68. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-11842-5_21.

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5

Li, Jinfei, Weidong Huang, Kai Qu, Wenshuang Wang e Ming Yang. "Experimental Research on Fatigue Damage of Composite Solid Propellant with Constant Constrain". In Lecture Notes in Electrical Engineering, 315–22. Berlin, Heidelberg: Springer Berlin Heidelberg, 2016. http://dx.doi.org/10.1007/978-3-662-48768-6_36.

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6

Kalal, R. K., H. Shekhar, P. S. Alegaonkar, Rekha Sangtyani e Arvind Kumar. "Thermo-Physical Properties and Combustion Wave of Nitramine Based Composite Propellant Compositions". In Springer Proceedings in Physics, 371–80. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-7691-8_37.

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7

Liu, C. T. "Non-Destructive Evaluation of Near Tip Damage Fields in a Composite Solid Propellant". In Computational Mechanics ’88, 221–25. Berlin, Heidelberg: Springer Berlin Heidelberg, 1988. http://dx.doi.org/10.1007/978-3-642-61381-4_51.

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8

Hashim, Syed Alay, Manu Lahariya, Srinibas Karmakar e Arnab Roy. "Calculation of Theoretical Performance of Boron-Based Composite Solid Propellant for the Future Applications". In Lecture Notes in Mechanical Engineering, 327–35. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-1771-1_35.

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9

Zhang, Xi, Xiaojiang Li, Zhi Ren, Jing Chen, Meng Liu e Xiong-Gang Wu. "A New Insight of Carbon Blacks and Burning Catalysts in Composite Modified Double Base Propellant". In Springer Proceedings in Physics, 467–80. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-1774-5_35.

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10

Yeh, H. Y., M. D. Le e C. T. Liu. "A Study of the Loading Rate Effect on the Crack Growth Behavior in a Composite Solid Propellant". In Fracture of Engineering Materials and Structures, 523–28. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3650-1_76.

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Atti di convegni sul tema "Composite propellant"

1

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

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2

Robinson, M. "Composite cryogenic propellant tank development". In 35th Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1375.

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3

Keizers, H., A. Hordijk, L. van Vliet e F. Bouquet. "Modelling of composite propellant properties". In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3323.

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4

BLOMSHIELD, F., e J. OSBORN. "Nitramine composite solid propellant modeling". In 26th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-2311.

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5

Reeling Brouwer, Gerhard, Huub Keizers e Jim Buswell. "Aging in Composite Propellant Grains". In 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-4058.

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6

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

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7

Franson, C., O. Orlandi, C. Perut, G. Fouin, C. Chauveau, I. Gökalp e M. Calabro. "New high energetic composite propellants for space applications: refrigerated solid propellant". In Progress in Propulsion Physics. Les Ulis, France: EDP Sciences, 2009. http://dx.doi.org/10.1051/eucass/200901031.

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8

Jayaraman, K. "Development of Pyro Igniter for Gas Turbine Engine Application". In ASME 2013 Gas Turbine India Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gtindia2013-3517.

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Abstract (sommario):

As the initiation of ignition of gas turbine combustor is relying on conventional spark plug methods, it has some limitations at fuel lean mixture conditions, turbulence streams and high altitude relight conditions. Severely reduced spark plug performance and durability is an unfortunate consequence as engines are simultaneously being pushed to higher power densities and leaner stoichiometry in order to improve efficiency and lower emissions. However, an important parameter is the ignition under extreme conditions, lean combustible mixture and high initial pressure, requiring high voltage when using conventional spark plug technology and also significantly reduces the lifetime. An alternative solution to standard spark plug is the use of pyro materials to igniter applications. The overall energy conversion efficiency from chemical energy to electrical energy and mechanical energy will be less when compared to direct conversion of chemical energy to the required applications. Also, the pyro type sources are compact in size. In the gas turbine the exploitation of pyro igniter is inevitable. This research paper involves the demonstration of chlorine free propellant formulation, burning rate studies, application and compatibility of pyro igniter to initiate the ignition of gas turbine combustor. Ammonium Nitrate (AN) plus polymer binder (Hydroxyl Terminated Poly Butadiene – HTPB) and Ammonium Dichromate (ADC) catalyst based composite propellant pyro igniter material have been considered. This composite propellant delivers comparatively low performance, low temperature and low burn rate when compared to Ammonium Perchlorate (AP) based propellant. But AP based propellants discharges corrosive (HCl) gases. AN based composite propellant have chosen for the clean exhaust and non-toxic gases. The impact sensitivity of AN based propellant is quite normal comparable with AP based compositions and low when compared to double based propellants. The burning rate of the propellant is measured in 10 to 60 bar pressure range. The pyro igniter is fabricated and ignition tests are conducted. Average energy release rate of the pyro igniter is 16.6 KJ/s in the designed configuration.

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9

Goldsborough, Mark, Gary Rosenfield, Bernard Kosowski e William Wood. "HIGH IMPULSE DENSITY COMPOSITE PROPELLANT SYSTEMS". In 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-5959.

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10

Chen, Yang, Vahid Morovati e 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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Rapporti di organizzazioni sul tema "Composite propellant"

1

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

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2

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

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3

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

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4

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

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5

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

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6

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

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7

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

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8

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

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