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Relevant bibliographies by topics / Hydroxyl terminated poly-butadiene

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Academic literature on the topic 'Hydroxyl terminated poly-butadiene'

Author: Grafiati

Published: 6 September 2023

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Journal articles on the topic "Hydroxyl terminated poly-butadiene"

1

Uscumlic, Gordana, Mohamed Zreigh, and Dusan Mijin. "Investigation of the interfacial bonding in composite propellants. 1,3,5-trisubstituted isocyanurates as universal bonding agents." Journal of the Serbian Chemical Society 71, no. 5 (2006): 445–58. http://dx.doi.org/10.2298/jsc0605445u.

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A series of 1,3,5-trisubstituted isocyanurates (substituents: CH2CH2OH CH2CH=CH2 and CH2CH2COOH) was synthesized according to a modified literature procedure. Experimental investigations included modification of the synthetic procedure in terms of the starting materials, solvents, temperature isolation techniques, as well as purification and identification of the products. All the synthesized isocyanurates were identified by their melting point and FTIR, 1H NMR and UV spectroscopic data. Fourier transform infrared spectrophotometry was also used to study the interaction between ammonium perchlorate, hydroxyl terminated poly(butadiene), carboxyl terminated poly(butadiene), poly(butadiene-co-acrylonitrile), poly(propylene ether) cyclotrimethylenetrinitramine and the compounds synthesized in this work which can serve as bonding agents. The results show that tris(2-hydroxyethyl)isocyanurate is a universal bonding agent for the ammonium perchlorate/carboxyl terminated poly(butadiene)/cyclotrimethylenetrinitramine composite propellant system.

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2

Xiang, Dong, Miao Liu, Guanliang Chen, Teng Zhang, Li Liu, and Yongri Liang. "Optimization of mechanical and dielectric properties of poly(urethane–urea)-based dielectric elastomers via the control of microstructure." RSC Advances 7, no. 88 (2017): 55610–19. http://dx.doi.org/10.1039/c7ra11309a.

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In this work, we fabricated hydroxyl-terminated butadiene–acrylonitrile copolymer-based poly(urethane–urea) dielectric elastomers, and investigated the relationship between multi-length scale structure and dielectric, mechanical properties.

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3

Brzic, Sasa, Ljiljana Jelisavac, Jela Galovic, Danica Simic, and Jelena Petkovic. "Viscoelastic properties of hydroxyl-terminated poly(butadiene) based composite rocket propellants." Chemical Industry 68, no. 4 (2014): 435–43. http://dx.doi.org/10.2298/hemind130426067b.

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In the present study, the viscoelastic response of three composite solid propellants based on hydroxyl-terminated poly(butadiene), ammonium perchlorate and aluminum has been investigated. The investigation was surveyed by dynamic mechanical analysis over a wide range of temperatures and frequencies. The mechanical properties of these materials are related to the macromolecular structure of the binder as well as to the content and nature of solid fillers. The storage modulus, loss modulus, loss factor and glass transition temperature for each propellant sample have been evaluated. The master curves of storage (log G' vs log ?) and loss modulus (log G'' vs log ?) were generated for each propellant. A comparison of logaT vs temperature curves for all propellants indicate conformance to Williams-Landel-Ferry equation. Choosing the glass transition as the reference temperature, WLF equation constants are determined. Fractional free volume at the glass transition temperature and thermal coefficient of free volume expansion values are in accordance with the consideration that Al is reinforcing filler.

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4

Tanver, Abbas, Mu Hua Huang, Yun Jun Luo, and Ze Huan Hei. "Chemical Kinetic Studies on Polyurethane Formation of GAP and HTPB with IPDI by Using In Situ FT-IR Spectroscopy." Advanced Materials Research 1061-1062 (December 2014): 337–41. http://dx.doi.org/10.4028/www.scientific.net/amr.1061-1062.337.

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The high-performance solid propellants play very important role in defense industry, which required highly energetic binders with good mechanical properties. In order to get the activation parameters for energetic binders, In-Situ FT-IR spectroscopic technique is used to study the chemical kinetics of glycidyl azide polymer (GAP) and hydroxyl terminated poly butadiene (HTPB) with isophorone diisocyanate (IPDI) at various temperatures. The reaction was followed by monitoring the change in intensity of the absorption band of NCO stretching at 2257cm-1and CO stretching at 1731cm-1. The polyurethane reaction has been found to be second order and the rate constant seems to be different between GAP/IPDI and HTPB/IPDI due to reactivity difference of OH groups. Dibutyl tin dilurate (DBTDL) was used as curing catalyst. By using Arrhenius and Eyring equations, the activation parameters were obtained at different temperatures (60, 70, 80 and 90°C). The apparent activation energy for the two systems GAP/IPDI and HTPB/IPDI were found to be 63.51 kJ mol-1and 41.06 kJ mol-1while the enthalpy and entropy of activation were found to be 62.35 kJ mol-1and-36.24 kJ.mol-1K-1, 39.08 J mol-1and-98.84 J mol-1K-1respectively.Key words: In-Situ FT-IR; glycidyl azide polymer (GAP); hydroxyl terminated poly butadiene (HTPB); chemical kinetics; polyurethane; dibutyl tin dilurate (DBTDL).

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5

Brzic, Sasa, Vesna Rodic, Mirjana Dimic, Danica Simic, Ljiljana Jelisavac, and Marica Bogosavljevic. "Influence of 1,4-butanediol on hydroxyl-terminated poly(butadiene) based composite propellant binder characteristics." Scientific Technical Review 65, no. 3 (2015): 55–60. http://dx.doi.org/10.5937/str1503055b.

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6

Sai Teja, P., B. Sudhakar, A. D. Dhass, R. Krishna, and M. Sreenivasan. "Numerical and experimental analysis of hydroxyl-terminated poly-butadiene solid rocket motor by using ANSYS." Materials Today: Proceedings 33 (2020): 308–14. http://dx.doi.org/10.1016/j.matpr.2020.04.097.

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7

Ero?lu, Mehmet S. "Characterization of the network structure of hydroxyl terminated poly(butadiene) elastomers prepared by different reactive systems." Journal of Applied Polymer Science 70, no. 6 (November 7, 1998): 1129–35. http://dx.doi.org/10.1002/(sici)1097-4628(19981107)70:6<1129::aid-app9>3.0.co;2-q.

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8

Stoeva, S., P. Kartalov, and K. Jankova. "Combined relaxation study of poly(vinyl chloride) blends with chlorinated poly(ethylene), hydroxyl-terminated poly(butadiene), and ethylene-propylene-diene terpolymer." Journal of Polymer Science Part B: Polymer Physics 36, no. 10 (July 30, 1998): 1595–608. http://dx.doi.org/10.1002/(sici)1099-0488(19980730)36:10<1595::aid-polb1>3.0.co;2-p.

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9

Subramanian, K. "Synthesis and characterization of poly(vinyl ferrocene) grafted hydroxyl-terminated poly(butadiene): A propellant binder with a built-in burn-rate catalyst." Journal of Polymer Science Part A: Polymer Chemistry 37, no. 22 (November 15, 1999): 4090–99. http://dx.doi.org/10.1002/(sici)1099-0518(19991115)37:22<4090::aid-pola7>3.0.co;2-r.

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10

Sankaran, S., and Manas Chanda. "Chemical toughening of epoxies. II. Mechanical, thermal, and microscopic studies of epoxies toughened with hydroxyl-terminated poly(butadiene-co-acrylonitrile)." Journal of Applied Polymer Science 39, no. 8 (April 20, 1990): 1635–47. http://dx.doi.org/10.1002/app.1990.070390802.

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Dissertations / Theses on the topic "Hydroxyl terminated poly-butadiene"

1

Kumar, Nomesh. "Hyperviscoelastic constitutive modelling and crack propagation behavior of solid propellant." Thesis, IIT Delhi, 2018. http://eprint.iitd.ac.in:80//handle/2074/8031.

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2

Smyth, Daniel A. "Modeling Solid Propellant Ignition Events." BYU ScholarsArchive, 2011. https://scholarsarchive.byu.edu/etd/3125.

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

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Conference papers on the topic "Hydroxyl terminated poly-butadiene"

1

English, Brian E., Heather H. DiBiaso, and Mark G. Allen. "Microcombustors Based on Controllable Solid Fuel Elements." In ASME 2003 International Mechanical Engineering Congress and Exposition. ASMEDC, 2003. http://dx.doi.org/10.1115/imece2003-42823.

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This paper focuses on the control of solid-fuel burn rate by controlling the solid-fuel chemistry or by controlling heat losses. Laser cutting and lamination have been used to fabricate milli-scale test structures to characterize burn rates of composite solid fuel. The base ingredients for the solid fuels tested were phase-stabilized ammonium nitrate (PSAN), ammonium perchlorate (AP), and sodium azide (SA). These base ingredients were tested alone or mixed with hydroxyl-terminated poly-butadiene (HTPB) plus various accelerants. Several experiments were performed to test the controllability of composite solid fuels. Burn-rate tests at atmospheric pressure consisted of 250 to 500 micron deep square combustion chambers packed with fuel and resistively heated on the top surface until combustion was achieved. Experiments were also performed to increase burn rate through chamber pressurization. Reaction times for a set amount of fuel were observed to increase exponentially as nozzle diameter was decreased. Finally, combustion chamber geometry was altered to control reaction propagation by increasing localized heat losses. A 500 micron thick triangular chamber was fabricated and ignited at the larger end, allowing the reaction to propagate toward the triangle tip. These results indicate that controllable actuation of solid propellants on the microscale for non-thrust, gas generation actuator applications is feasible.

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2

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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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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