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Articoli di riviste sul tema "Burning rate"

Autore: Grafiati

Pubblicato: 4 giugno 2021

Ultima modifica: 29 aprile 2023

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1

Atwood, A. I., T. L. Boggs, P. O. Curran, T. P. Parr, D. M. Hanson-Parr, C. F. Price e J. Wiknich. "Burning Rate of Solid Propellant Ingredients, Part 2: Determination of Burning Rate Temperature Sensitivity". Journal of Propulsion and Power 15, n. 6 (novembre 1999): 748–52. http://dx.doi.org/10.2514/2.5523.

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2

Doriath, G. "HIGH BURNING RATE SOLID ROCKET PROPELLANTS". International Journal of Energetic Materials and Chemical Propulsion 4, n. 1-6 (1997): 646–60. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v4.i1-6.610.

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3

Kubota, N., T. Sonobe, A. Yamamoto e H. Shimizu. "Burning rate characteristics of GAP propellants". Journal of Propulsion and Power 6, n. 6 (novembre 1990): 686–89. http://dx.doi.org/10.2514/3.23273.

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4

Lipatnikov, A. N. "Burning Rate in Impinging Jet Flames". Journal of Combustion 2011 (2011): 1–11. http://dx.doi.org/10.1155/2011/737914.

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A method for evaluating burning velocity in premixed turbulent flames stabilized in divergent mean flows is quantitatively validated using numerical approximations of measured axial profiles of the mean combustion progress variable, mean and conditioned axial velocities, and axial turbulent scalar flux, obtained by four research groups from seven different flames each stabilized in an impinging jet. The method is further substantiated by analyzing the combustion progress variable balance equation that is yielded by the extended Zimont model of premixed turbulent combustion. The consistency of the model with the aforementioned experimental data is also demonstrated.

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5

Zain-ul-Abdin, Zain-ul-Abdin, Li Wang, Haojie Yu, Muhammad Saleem, Muhammad Akram, Nasir M. Abbasi, Hamad Khalid, Ruoli Sun e Yongsheng Chen. "Ferrocene-based polyethyleneimines for burning rate catalysts". New Journal of Chemistry 40, n. 4 (2016): 3155–63. http://dx.doi.org/10.1039/c5nj03171k.

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6

MIZUNO, TOMOYUKI. "BURNING BEHAVIOUR OF UPHOLSTERED FURNITURE IN FIRE TEST : Part 1 Burning rate". Journal of Structural and Construction Engineering (Transactions of AIJ) 363 (1986): 103–9. http://dx.doi.org/10.3130/aijsx.363.0_103.

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7

Rashkovskiy, S. A., V. G. Krupkin e V. N. Marshakov. "Burning rate of solid homogeneous energetic materials with a curved burning surface". Journal of Physics: Conference Series 1250 (giugno 2019): 012041. http://dx.doi.org/10.1088/1742-6596/1250/1/012041.

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8

LI, Jing, Toshimi TAKAGI, Tatsuyuki OKAMOTO e Shinichi KINOSHITA. "Flame Structure, Burning Velocity and Burning Rate in Stretch Controlled Premixed Flame". Transactions of the Japan Society of Mechanical Engineers Series B 70, n. 691 (2004): 767–72. http://dx.doi.org/10.1299/kikaib.70.767.

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9

Krishnan, S., e R. Jeenu. "Subatmospheric burning charaterristics of AP/CTPB composite propellants with burning rate modifiers". Combustion and Flame 80, n. 1 (aprile 1990): 1–6. http://dx.doi.org/10.1016/0010-2180(90)90048-v.

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10

Tahsini, Amir Mahdi. "Regression rate response in spin-stabilized solid fuel ramjets". Journal of Mechanics 37 (2020): 37–43. http://dx.doi.org/10.1093/jom/ufaa012.

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ABSTRACT The regression rate of the solid fuel in the spinning solid fuel ramjet is investigated here using numerical simulations. The finite volume solver of the reacting turbulent flow is developed to study the flow field in the back-step combustion chamber where the burning rate of the solid fuel is computed using the conjugate heat transfer. The dependence of the burning rate on the circumferential velocity of the ramjet is studied, and it is shown that the spin augments the burning rate due to the enhancement of the convective heat flux along the fuel grain. So, the spin can be used to improve the performance of the solid fuel ramjets. In addition, the effect of rapid change in spin velocity on the regression rate of the fuel is investigated, which shows the transient-burning behavior. The results show that although the spin may increase the burning rate by ∼10% in steady-state operation of the ramjet, the spin acceleration may cause the overshoot in burning rate with the peak value >30% in the unsteady operation.

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11

Hariprasad, V., P. Sankar, P. Shivahari e V. R. Sanal Kumar. "Studies on Gravity Influence on Solid Propellant Burn Rate". Applied Mechanics and Materials 232 (novembre 2012): 342–47. http://dx.doi.org/10.4028/www.scientific.net/amm.232.342.

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Experimental studies have been carried out using the in-house developed propellant samples at the atmospheric conditions to examine the influence of propellant surface orientation / attitude on burn rate. A series of burning tests are conducted with different grain orientations, viz., vertical, inverted and horizontal. We have observed 5 % burn rate augmentation on end-burning grains when the burning surface evolution was against the earth gravity compared to the normal vertical candle burning condition. We conjectured that the coupled effects of the instantaneous variations of the propellant burning surface attitude and the flight acceleration during the mission could alter the flame structure due to the local gravitational influence, which in turn alter the burn rate. This paper throws light for developing a suitable gravitational force dependant burn rate model for improving the performance prediction of solid rocket motors for aerospace applications.

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12

Greatrix, David R. "Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations". International Journal of Aerospace Engineering 2008 (2008): 1–10. http://dx.doi.org/10.1155/2008/826070.

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A general numerical model based on the Zeldovich-Novozhilov solid-phase energy conservation result for unsteady solid-propellant burning is presented in this paper. Unlike past models, the integrated temperature distribution in the solid phase is utilized directly for estimating instantaneous burning rate (rather than the thermal gradient at the burning surface). The burning model is general in the sense that the model may be incorporated for various propellant burning-rate mechanisms. Given the availability of pressure-related experimental data in the open literature, varying static pressure is the principal mechanism of interest in this study. The example predicted results presented in this paper are to a substantial extent consistent with the corresponding experimental firing response data.

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13

Andabak Rogulj, Ana, Ivana Škrinjar, Danica Vidović Juras, Vanja Vučićević Boras † e Božana Lončar Brzak. "Burning mouth syndrome – a burning enigma". Medicina Fluminensis 57, n. 1 (1 marzo 2021): 4–16. http://dx.doi.org/10.21860/medflum2021_365333.

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Burning Mouth Syndrome (BMS) is a chronic pain condition characterized by an intraoral burning sensation and an absence of oral mucosal lesions and disturbances in laboratory findings. Burning symptoms usually affect the anterior two-thirds of the tongue, its lateral borders, hard palate and labial mucosa, but other oral cavity sites may also be affected. Taste alterations and a decrease in the salivary flow rate frequently accompany the burning symptoms. This condition mostly affects peri- and postmenopausal women. To date, the etiology of BMS remains unclear. This unknown etiology means that no appropriate treatment is currently available. A large number of the treatments and medications have been tried for BMS, but treatment management remains unsatisfactory in some patients. The purpose of this article is to present current knowledge on the treatment of BMS.

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14

Harting, George C., J. W. Mordosky, Baoqi Zhang, T. T. Cook e Kenneth K. Kuo. "BURNING RATE CHARACTERIZATION OF OXSOL LIQUID OXIDIZER". International Journal of Energetic Materials and Chemical Propulsion 5, n. 1-6 (2002): 563–75. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v5.i1-6.590.

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15

Kubota, N., e H. Okuhara. "Burning rate temperature sensitivity of HMX propellants". Journal of Propulsion and Power 5, n. 4 (luglio 1989): 406–10. http://dx.doi.org/10.2514/3.23169.

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16

YANO, Yutaka, e Tsutomu GOMI. "Burning rate characteristics of RDX-CMDB propellants." Journal of the Japan Society for Aeronautical and Space Sciences 34, n. 391 (1986): 447–52. http://dx.doi.org/10.2322/jjsass1969.34.447.

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17

Hasegawa, H., M. Fukunaga, K. Kitagawa e T. Shimada. "Burning rate anomaly of composite propellant grains". Combustion, Explosion, and Shock Waves 49, n. 5 (settembre 2013): 583–92. http://dx.doi.org/10.1134/s0010508213050109.

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18

Kubota, N., e T. Sonobe. "Burning rate catalysis of azide/nitramine propellants". Symposium (International) on Combustion 23, n. 1 (gennaio 1991): 1331–37. http://dx.doi.org/10.1016/s0082-0784(06)80397-8.

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19

Kubota, N., e N. Hirata. "Super-rate burning of catalyzed HMX propellants". Symposium (International) on Combustion 21, n. 1 (gennaio 1988): 1943–51. http://dx.doi.org/10.1016/s0082-0784(88)80431-4.

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20

Shepherd, I. G., E. Bourguignon, Y. Michou e I. Gökalp. "The burning rate in turbulent bunsen flames". Symposium (International) on Combustion 27, n. 1 (gennaio 1998): 909–16. http://dx.doi.org/10.1016/s0082-0784(98)80488-8.

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21

Hessler, R. O., e R. L. Glick. "Error analysis of burning-rate measurement procedures". Combustion, Explosion, and Shock Waves 36, n. 1 (gennaio 2000): 96–107. http://dx.doi.org/10.1007/bf02701518.

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22

Constantin, Peter, Alexander Kiselev, Adam Oberman e Leonid Ryzhik. "Bulk Burning Rate in¶Passive–Reactive Diffusion". Archive for Rational Mechanics and Analysis 154, n. 1 (agosto 2000): 53–91. http://dx.doi.org/10.1007/s002050000090.

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23

Oyumi, Yoshio, Kiyotaka Inokami, Kazuhiro Yamazaki e Koki Matsumoto. "Burning Rate Augmentation of BAMO Based Propellants". Propellants, Explosives, Pyrotechnics 19, n. 4 (agosto 1994): 180–86. http://dx.doi.org/10.1002/prep.19940190406.

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24

Gao, Jing-min, Li Wang, Hao-jie Yu, An-guo Xiao e Wen-bing Ding. "Recent Research Progress in Burning Rate Catalysts". Propellants, Explosives, Pyrotechnics 36, n. 5 (21 settembre 2011): 404–9. http://dx.doi.org/10.1002/prep.200900093.

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25

Ambekar, Anirudha, Minsung Kim, Woong-Hyun Lee e Jack J. Yoh. "Characterization of display pyrotechnic propellants: Burning rate". Applied Thermal Engineering 121 (luglio 2017): 761–67. http://dx.doi.org/10.1016/j.applthermaleng.2017.04.097.

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26

Markan, Akshit, Peter B. Sunderland, James G. Quintiere, John L. de Ris, Dennis P. Stocker e Howard R. Baum. "A Burning Rate Emulator (BRE) for study of condensed fuel burning in microgravity". Combustion and Flame 192 (giugno 2018): 272–82. http://dx.doi.org/10.1016/j.combustflame.2018.01.044.

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27

Xianggeng, Wei, Bo Tao, Wang Pengbo, Ma Xinjian, Lou Yongchun e Chen Jian. "Burning Rate Enhancement Analysis of End-Burning Solid Propellant Grains Based on X-Ray Real-Time Radiography". International Journal of Aerospace Engineering 2020 (22 giugno 2020): 1–9. http://dx.doi.org/10.1155/2020/7906804.

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Unexpected pressure rise may occur in the end-burning grain solid rocket motor. It is generally believed that this phenomenon is caused by the nonparallel layer combustion of the burning surface, resulting in the increase of burning rate along the inhibitor. In order to explain the cause of this phenomenon, the experimental investigation on four different end configurations were carried out. Based on the X-ray real-time radiography (RTR) technique, a new method for determining the dynamic burning rate of propellant and obtaining the real-time end-burning profile was developed. From the real-time images of the burning surface, it is found that there was a phenomenon of nonuniform burning surface displacement in the end-burning grain solid rocket motor. Through image processing, the real-time burning rate of grain center line and the real-time cone angle are obtained. Based on the analysis of the real-time burning rate at different positions of the end surface, the end face cone burning process in the motor working process is obtained. The closer to the shell, the higher the burning rate of the propellant. Considering the actual structure of this end-burning grain motor, it is speculated that the main cause of the cone burning of the grain may be due to the heat conduction of the metal wall. By adjusting the initial shape of the grain end surface, the operating pressure of the combustion chamber can be basically unchanged, so as to meet the mission requirements. The results show that the method can measure the burning rate of solid propellant in real time and provide support for the study of nonuniform combustion of solid propellant.

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28

Hafizi, Mohammad, Rizalman Mamat, Amir Aziz, M. M. Noor e Ahmad Tamimi. "Development of Strand Burner Test by Using Aluminized AP/HTPB". Materials Science Forum 880 (novembre 2016): 99–104. http://dx.doi.org/10.4028/www.scientific.net/msf.880.99.

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One of the key factors that play an important role in the performance of a solid propellant rocket is dependent on its burning rate. A strand burner is a type of apparatus used to measure the propellant burning rate at elevated pressure. This study investigates the relation between burning rates of aluminized ammonium perchlorate at low pressure. Chamber pressure was varied from 1 atm, 3 atm, 5 atm and 7 atm. This study shows that propellant burning rate is about 50%-62% higher when the burn rate test is conducted at atmospheric condition compared to when it is done in inert gas. The investigation’s results also revealed an increasing propellant burning rate when the chamber pressure is increased. In conclusion, the burning condition and chamber pressure influences the propellant burning rate.

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29

Wu, Xueshun, Peng Wang, Zhennan Zhu, Yunshou Qian, Wenbin Yu e Zhiqiang Han. "The Equivalent Effect of Initial Condition Coupling on the Laminar Burning Velocity of Natural Gas Diluted by CO2". Energies 14, n. 4 (4 febbraio 2021): 809. http://dx.doi.org/10.3390/en14040809.

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Initial temperature has a promoting effect on laminar burning velocity, while initial pressure and dilution rate have an inhibitory effect on laminar burning velocity. Equal laminar burning velocities can be obtained by initial condition coupling with different temperatures, pressures and dilution rates. This paper analysed the equivalent distribution pattern of laminar burning velocity and the variation pattern of an equal weight curve using the coupling effect of the initial pressure (0.1–0.3 MPa), initial temperature (323–423 K) and dilution rate (0–16%). The results show that, as the initial temperature increases, the initial pressure decreases and the dilution rate decreases, the rate of change in laminar burning velocity increases. The equivalent effect of initial condition coupling can obtain equal laminar burning velocity with an dilution rate increase (or decrease) of 2% and an initial temperature increase (or decrease) of 29 K. Moreover, the increase in equivalence ratio leads to the rate of change in laminar burning velocity first increasing and then decreasing, while the increases in dilution rate and initial pressure make the rate of change in laminar burning velocity gradually decrease and the increase in initial temperature makes the rate of change in laminar burning velocity gradually increase. The area of the region, where the initial temperature influence weight is larger, gradually decreases as the dilution rate increases, and the rate of decrease gradually decreases.

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30

Singh, RS. "Changes in Soil Nutrients Following Burning Burning of Dry Tropical Savanna". International Journal of Wildland Fire 4, n. 3 (1994): 187. http://dx.doi.org/10.1071/wf9940187.

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The effects of fire in dry tropical savanna ecosystems on plant available nutrients (nitrate-N, ammonium-N and phosphate - P); N - mineralization rate; soil microbial biomass C, N and P; canopy biomass and root biomass were studied during selected months. Parameters studied were the vegetative, reproductive, flowering and fruiting, fruitfall, early senescence and late senescence. The values of nitrate-N, ammonium-N and phosphate - P, N- mineralization and nitrification rate; microbial C, N and P, canopy biomass and root biomass indicated significant difference due to month and treatment, but were not significant due to year. Following fire, the increase in the build up of microbial biomass in the dry season and canopy growth and N-mineralization rate in the wet season are nutrient conserving mechanisms that prevent nutrient loss. Therefore fire can be a management tool for better productivity and nutritive quality in dry tropical environments.

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31

Panetta, Paul D., Richard Byrne e Hualong Du. "The Direct Quantitative Measurement of In-Situ Burn (ISB) Rate and Efficiency". International Oil Spill Conference Proceedings 2017, n. 1 (1 maggio 2017): 1006–19. http://dx.doi.org/10.7901/2169-3358-2017.1.1006.

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ABSTRACT In-situ burning (ISB) is an important tool to remove oil from the environment. During ISB, it is important to know the volume reduction of oil for the overall accounting of the spilled oil, as a metric for operational decisions, and to account for the ISB portion of the oil budget. The burn rate depends on the type of oil, degree of emulsification and weathering, estimated thickness, weather conditions, and size of the burn area. Furthermore, each spill has a unique physical environment and oil properties that affect burn efficiency and rate. The volume of oil consumed during ISB is typically computed using a manual, coarse, time integration of the instantaneous burn area based on visual observations and a characteristic burn rate. The area is typically estimated in the field using known boom geometry and visual inspection of the fire-water interface, and recorded manually. We have developed methods to measure the instantaneous consumption of burning oil and thus the oil burn rate by integrating direct measurements of thickness using acoustics sensors in the water under the slick with direct measurements of the area of the burning oil using infrared and visible light images from cameras above the burning oil. Data were collected during the burning of several oils and petroleum products including ANS, rock, diesel, and hexane. The acoustic thickness measurement took into account the high temperature gradient in the oil and combined with multi camera automated burn area estimates yielded an instantaneous measurement of the volume of oil consumed while burning. We were able to identify the buildup of the burn, the active burning phase, and in the case of confined burns the vigorous burning phase. Knowing the instantaneous thickness and surface area during burning allowed us to directly calculate the burn rate and to study the dynamics of ISB. We are working on validating the burn rate and efficiency with direct measurements of the weight of the oil and residue before, during, and after burning. The authors believe these are the first direct measurements of slick thickness using acoustics during ISB.

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32

Zhao, Jinlong, Quanyi Liu, Hong Huang, Rui Yang e Hui Zhang. "Experiments investigating fuel spread behaviors for continuous spill fires on fireproof glass". Journal of Fire Sciences 35, n. 1 (gennaio 2017): 80–95. http://dx.doi.org/10.1177/0734904116683716.

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A series of large-scale spill fire experiments with continuous discharge on a rectangular fireproof glass sheet were conducted, to better understand spill fire spread behaviors on land. JP-5 and heptane were selected as the fuels, with discharge rates varying from 0.93 to 6.82 L/min. Results show that the spread process can be divided into five phases: spread burning, shrink burning, quasi-steady burning, boiling burning, and extinguished. Not all of the burning phases appear during the process, which is related to the burning scale and the type of fuel. The burning rate of the quasi-steady burning phase is smaller than that of pool fires under the same burning scale. The ratio of the spill fire burning rate to the pool fire burning rate is close to 0.54 for JP-5 and 0.78 for heptane. In addition, we observed that the burning areas expand quickly at the beginning of a boiling burning phase and that the disturbance or entrainment of the flames becomes violent at the beginning of this phase. In the spread process, the empirical correlation between the maximum burning areas [Formula: see text] and the discharge rate [Formula: see text] is [Formula: see text] ( W is the width of glass) for JP-5, and [Formula: see text] for Heptane. The ratio of maximum area to quasi-steady area is approximately 1.46 in the experiments.

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33

Mizuno, T., e K. Kawagoe. "Burning behaviour of upholstered chairs. Part 2. Burning rate of chairs in fire tests." Fire Science and Technology 5, n. 1 (1985): 69–78. http://dx.doi.org/10.3210/fst.5.69.

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34

Hoque, Ehtasimul, Chandra Shekhar Pant e Sushanta Das. "Statistical Evaluation of Burning Rate Data of Composite Propellants Obtained from Acoustic Emission Technique". Defence Science Journal 71, n. 1 (1 febbraio 2021): 18–24. http://dx.doi.org/10.14429/dsj.71.16007.

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The acoustic emission technique has been considered to be one of the most reliable and robust methods for the measurement of the steady burning rate of composite propellants. In this work, attempts were made to quantify the measurement variability of the burning rate of composite solid propellants by acoustic emission method using statistical tools. A total of 1100 individual measurements were subjected to statistical treatment. The combination of confidence interval and repeatability limit delineated the extent of natural dispersion in the burning rate measurement data. The very high coefficient of variation values for the propellant compositions, having a burning rate of more than 25 mm s–1 raised concerns about the suitability of the acoustic emission method for high burning rate compositions. The Reliability interval approach was employed to determine the statistically significant sample size for different composite propellants having a burning rate range of 5–31 mm s–1. The entire set of data was screened for identification of outlying observation using the Dixon Q test, and the extent of contamination was quantified. Moreover, the application of statistical techniques could have far-reaching implications for quality control perspectives of burning rate measurement by acoustic emission and could be implemented as reference tolerance limits and preventive measures for ensuring the good health of the instrument as well as propellant processing.

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35

Wang, B., H. Peng e YX Chen. "Effects of deformation on the burning behavior of solid propellants". International Journal of Spray and Combustion Dynamics 9, n. 2 (9 giugno 2016): 116–26. http://dx.doi.org/10.1177/1756827716653292.

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In this paper, the burning rate of solid propellants under strains was investigated. In particular, the variations of burning rate at a deformation of 20% or less was measured using a novel apparatus. The results showed that the burning rate increased with increasing strain, but such increase became stable if the strain was increased to a threshold value. In addition, a quadratic functional correlation could be drawn between the burning rate ratio and strain, which was in agreement with the theoretical analysis.

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36

Derk, Greg, Grant A. Risha, Eric Boyer e Richard A. Yetter. "HIGH-PRESSURE BURNING RATE MEASUREMENTS BY DIRECT OBSERVATION". International Journal of Energetic Materials and Chemical Propulsion 18, n. 3 (2019): 213–27. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.2019028230.

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37

Mizukami, T., Y. Utiskul, T. Naruse e J. Quintiere. "A Compartment burning rate model for various scales". Fire Safety Science 9 (2008): 839–48. http://dx.doi.org/10.3801/iafss.fss.9-839.

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38

Davies, R. "Ignition and Burning Rate of Water Hyacinth Briquettes". Journal of Scientific Research and Reports 2, n. 1 (10 gennaio 2013): 111–20. http://dx.doi.org/10.9734/jsrr/2013/1964.

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39

Moiseeva, K. M., e A. Yu Krainov. "The burning rate of coal-dust-air suspension". Journal of Physics: Conference Series 1261 (giugno 2019): 012023. http://dx.doi.org/10.1088/1742-6596/1261/1/012023.

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40

Zivorad, Lazic. "Burning rate of a trimodal composite rocket propellant". Journal of Propulsion and Power 6, n. 5 (settembre 1990): 515–18. http://dx.doi.org/10.2514/3.23250.

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41

OJIMA, Jun. "Generation Rate of Carbon Monoxide from Burning Charcoal". Industrial Health 49, n. 3 (2011): 393–95. http://dx.doi.org/10.2486/indhealth.ms1189.

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42

Bhat, V. K., Haridwar Singh, R. R. Khare e K. R. K. Rao. "Burning Rate Studies of Energetic Double Base Propellants". Defence Science Journal 36, n. 1 (20 gennaio 1986): 71–75. http://dx.doi.org/10.14429/dsj.36.5963.

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43

Rao, R. Bhaskara, e Harihar Singh. "Burning Rate Characteristics of Magnesium Sodium Nitrate Propellants". Defence Science Journal 42, n. 3 (1 gennaio 1992): 173–76. http://dx.doi.org/10.14429/dsj.42.4377.

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44

Borovskoy, I. G., A. B. Vorozhtsov e A. E. Salko. "Magnetogasdynamic Control of Burning Rate of Condensed System". Defence Science Journal 45, n. 1 (1 gennaio 1995): 47–49. http://dx.doi.org/10.14429/dsj.45.4102.

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45

Sabdenov, K. O., e M. Erzada. "Analytical calculation of the negative erosive burning rate". Combustion, Explosion, and Shock Waves 49, n. 6 (novembre 2013): 690–99. http://dx.doi.org/10.1134/s0010508213060087.

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46

Pressley, H. M. "In situ burning-rate determination using flash radiography". NDT & E International 25, n. 4-5 (agosto 1992): 238. http://dx.doi.org/10.1016/0963-8695(92)90305-z.

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47

Gaunce, Michael T., e John R. Osborn. "Temperature sensitivity coefficients of solid propellant burning rate". Acta Astronautica 13, n. 3 (marzo 1986): 127–30. http://dx.doi.org/10.1016/0094-5765(86)90044-5.

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48

KIKUCHI, Yoshihiro. "Investigation of Burning Rate of Sodium Pool Fires". Journal of Nuclear Science and Technology 23, n. 1 (gennaio 1986): 83–85. http://dx.doi.org/10.1080/18811248.1986.9734951.

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49

Singh, Gurdip, I. P. S. Kapoor e D. K. Pandey. "Hexammine metal perchlorates as energetic burning rate modifiers". Journal of Energetic Materials 20, n. 3 (gennaio 2002): 223–44. http://dx.doi.org/10.1080/07370650208244822.

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50

Tao, Y. X., e M. Kaviany. "Burning rate of liquid supplied through a wick". Combustion and Flame 86, n. 1-2 (luglio 1991): 47–61. http://dx.doi.org/10.1016/0010-2180(91)90055-g.

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