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Journal articles on the topic 'Propellant management'

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Author: Grafiati

Published: 10 December 2022

Last updated: 28 January 2023

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1

Shruti Dipak Jadhav, Raghvendra Pratap Singh, Atri Bandyopadhyay, and Tapas Kumar Nag. "Conceptual Study on Propulsive Characteristics and Performance of Cryogenic Propellants." international journal of engineering technology and management sciences 6, no. 6 (November 28, 2022): 368–73. http://dx.doi.org/10.46647/ijetms.2022.v06i06.065.

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In the era of cryogenic propellants with high specific impulse; under microgravity situations, long-term storage and higher energy thruster management are highly needed. As methane is a reasonable cooling membrane for radiation and ablation chambers so high LOX/LCH4 combustion efficiency and reliable spark ignition to be achieved to develop a methane engine. To maintain the thermocouple system in the spacecraft and to prevent outer harmful radiation in space, the respected agencies may use thick-walled propellant containers with high pressure. To check the feasibility and effectiveness of a subcooled cryogenic propellant, a combination of pump depressurization as active cooling and liquid choke evaporation as passive cooling has been proposed and analyzed.

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2

Collicott, Steven H., and Boris Yendler. "Asymmetric Propellant Positioning in Symmetric Tanks and Propellant Management Devices." Journal of Spacecraft and Rockets 59, no. 2 (March 2022): 482–88. http://dx.doi.org/10.2514/1.a35095.

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3

Zhuang, Bao Tang, Yong Li, Ha Lin Pan, and Qi Hu. "Experiment Investigation on Fluid Storage Characteristic and Transportation Performance of Propellant Refillable Reservoir in Microgravity Environment." Applied Mechanics and Materials 390 (August 2013): 91–95. http://dx.doi.org/10.4028/www.scientific.net/amm.390.91.

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Satellites store and manage propellant by surface tension. A surface tension propellant management device (PMD) consists of a propellant refillable reservoir (PRR) for propellant storage and propellant acquisition vanes (PAVs) for propellant transportation. PRR is a key part of vane type surface tension tank (STT), and its storage performance determines the fluid management of vane type STT. In the present paper, a model test system was established and microgravity drop tower tests conducted based on experimental study of fluid storage and transportation behavior of PRR. Laws of fluid storage and transportation of PRR in microgravity environment were obtained. The test results show that two types of PRR both have good liquid storage capacity, and the double cone PRR exhibits good liquid storage capacity in lateral acceleration. A rational design of PRR can effectively store liquid and control liquid transportation velocity. The test results offer a guideline for optimization of new-style vane type PMD, and also provide a new method for fluid control in space environment.

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4

LIU, XIAOLIN, YIYONG HUANG, and GUANGYU LI. "CFD SIMULATION OF CAPILLARY RISE OF LIQUID IN CYLINDRICAL CONTAINER WITH LATERAL VANES." International Journal of Modern Physics: Conference Series 42 (January 2016): 1660154. http://dx.doi.org/10.1142/s201019451660154x.

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Orbit refueling is one of the most significant technologies, which has vital strategic meaning. It can enhance the flexibility and prolong the lifetime of the spacecrafts. Space propellant management is one of the key technologies in orbit refueling. Based on the background of space propellant management, CFD simulations of capillary rise of liquid in Cylindrical container with lateral vanes in space condition were carried out in this paper. The influence of the size and the number of the vanes to the capillary flow were analyzed too. The results can be useful to the design and optimization of the propellant management device in the vane type surface tension tank.

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5

Pylypenko, O. V., O. D. Nikolayev, I. D. Bashliy, and O. M. Zavoloka. "Approach to numerical simulation of the spatial motions of a gas/liquid medium in a space stage propellant tank in microgravity with account for the hot zone." Technical mechanics 2022, no. 4 (December 15, 2022): 3–13. http://dx.doi.org/10.15407/itm2022.04.003.

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Space propulsion systems ensure multiple startups and shutdowns of the main liquid-propellant rocket engines in microgravity conditions for spacecraft preset motions and reorientation control. During the passive flight of a space stage (after its main engine shutdown), the liquid propellant in the tanks continues moving by inertia in microgravity and moves as far away from the propellant management device as possible. In this case, the pressurization gas is displaced to the propellant management device, which creates the potential danger of the gas entering the engine inlet in quantities unacceptable for multiple reliable engine restarts. In this regard, the determination of the parameters of fluid movement in propellant tanks under microgravity conditions is a pertinent problem to be solved in the designing of liquid-propellant propulsion systems. This paper presents an approach to the theoretical calculation of the parameters of motion of the gas–liquid system in the propellant tanks of today’s space stages in microgravity conditions. The approach is based on the use of the finite element method, the Volume of Fluid method, and up-to-date computer tools for finite-element analysis (Computer Aided Engineering - CAE systems). A mathematical simulation of the spatial motion of the liquid propellant and the formation of free gas inclusions in passive flight was performed, and the motion parameters and shape of the free liquid surface in the tank and the location of gas inclusions were determined. The liquid motion in a model spherical tank in microgravity conditions was simulated numerically with and without account for the hot zone near the tank head. The motion parameters of the gas-liquid interface in a model cylindrical tank found using the proposed approach are in satisfactory agreement with experimental data. The proposed approach will significantly reduce the extent of experimental testing of space stages under development.

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6

HIMENO, Takehiro. "Propellant Management in Liquid Rockets and Space Vehicles." JAPANESE JOURNAL OF MULTIPHASE FLOW 27, no. 4 (2013): 385–92. http://dx.doi.org/10.3811/jjmf.27.385.

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7

Himeno, Takehiro, Toshinori Watanabe, and Akira Konno. "Numerical Analysis for Propellant Management in Rocket Tanks." Journal of Propulsion and Power 21, no. 1 (January 2005): 76–86. http://dx.doi.org/10.2514/1.4792.

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8

PYLYPENKO, O. V., D. E. SMOLENSKYY, O. D. NIKOLAYEV, and I. D. BASHLIY. "The approach to numerical simulation of the spatial movement of fluid with forming free gas inclusions in propellant tank at space flight conditions." Kosmìčna nauka ì tehnologìâ 28, no. 5 (October 28, 2022): 03–14. http://dx.doi.org/10.15407/knit2022.05.003.

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The space propulsion systems ensure se veral start-ups and shutdowns of main liquid-propellant rocket engines under microgravity conditions for the spacecraft program movements and reorientation control. During the passive flight of the space stage (after its main engine shutdown), the liquid propellant in the tanks continues to move by inertia in microgravity away from the propellant management device as much as possible. In this case, the pressurization gas is displaced to the propellant management device, which creates the potential danger of gas entering the engine inlet in quantities unacceptable for the reliable engine restart. In this regard, determining the parameters of fluid movement in propellant tanks in microgravity conditions is an urgent problem that needs to be solved in the design period of liquid propulsion systems. We have developed an approach to the theoretical computation of the parameters of the motion of the ‘gas — fluid’ system in the propellant tanks of modern space stages in microgravity conditions. The approach is based on the use of the finite element method, the Volume of Fluid method and modern computer tools for finite-element analysis (Computer Aided Engineering — CAE systems). For the passive leg of the launch vehicle space flight, we performed mathematical modeling of the spatial movement of liquid propellant and forming free gas inclusions and determined the parameters of movement and shape of the free surface of the liquid in the tank as well as the location of gas inclusions. The numerical simulation of the fluid movement in an experimental sample of a spherical shape tank was performed with regard to the movement conditions in the SE Yuzhnoye Design Bureau ‘Drop tower’ for studying space object s in microgravity. The motion parameters of the ‘gas — fluid’ interface obtained as a result of mathematical modeling are in satisfactory agreement with the experimental data obtained. The use of the developed approach will significantly reduce the amount of experimental testing of the designed space stages.

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9

Kositsyna, Olena, Kostiantyn Varlan, Mykola Dron, and Oleksii Kulyk. "Determining energetic characteristics and selecting environmentally friendly components for solid rocket propellants at the early stages of design." Eastern-European Journal of Enterprise Technologies 6, no. 6 (114) (December 21, 2021): 6–14. http://dx.doi.org/10.15587/1729-4061.2021.247233.

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This paper has investigated the possibility to theoretically calculate a value of the specific impulse for highly energetic compositions using only two parameters – the heat of the reaction and the number of moles of gaseous decomposition reaction products. Specific impulse is one of the most important energetic characteristics of rocket propellant. It demonstrates the level of achieving the value of engine thrust and propellant utilization efficiency. Determining the specific impulse experimentally is a complex task that requires meeting special conditions. For the stage of synthesis of new promising components, the comparative analysis of energetic characteristics, forecasting the value of specific impulse, especially relevant are calculation methods. Most of these methods were first developed to determine the energetic characteristics of explosives. Since explosives and rocket propellants in many cases have similar energy content and similar chemical composition, some estimation methods can be used to assess the specific impulse of solid rocket propellant. The specific impulse has been calculated for 45 compositions based on environmentally friendly oxidizers (ammonium dinitramide, hydrazinium nitroformate, hexanitrohexaazaisowurtzitane) and polymer binders polybutadiene with terminal hydroxyl groups, glycidylazide polymer, poly-3-nitratomethyl-3-methyloxetane). It was established that the estimation data obtained correlate well with literary data. Deviation of the derived values of the specific impulse from those reported in the literature is from 0.4 % to 1.8 %. The calculation results could be used for preliminary forecasting of energetic characteristics for highly energetic compositions, selecting the most promising components, as well as their ratios.

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10

Fisher, Mark F. "Propellant Management in Booster and Upper-Stage Propulsion Systems." Journal of Propulsion and Power 14, no. 5 (September 1998): 649–56. http://dx.doi.org/10.2514/2.5326.

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11

Liu, Jintao, Yong Li, Wen Li, Hua Zhai, and Lei Chen. "Testing Liquid Distribution in a Vane-Type Propellant Tank under Conditions of Microgravity Using a Drop Tower Test." International Journal of Aerospace Engineering 2020 (November 17, 2020): 1–13. http://dx.doi.org/10.1155/2020/6402083.

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Propellant management devices (PMDs) are a key component used to manage liquid propellant in a propellant tank under zero gravity conditions. A microgravity drop tower test system was established to investigate the performance of a PMD. A single module was used for the experiments, and the microgravity level was less than 3 × 10 − 3 g . Anhydrous ethanol was used as the simulate liquid. Different volume fractions of liquid were used to study the influence of the PMD on performance management. Experiments were conducted with the position of the container oriented in different directions. Changes in the gas-liquid interface were studied during the test. This kind of vane transports liquid through the rectangular area between the vane and the wall. The velocity flows along the vane of different liquid volume fractions in the tank were different at the beginning ( t < 0.8 s ) compared with the end of the test. The liquid relocation time was less than 0.8 s while the liquid volume fraction was larger than 25%. The liquid relocation time was prolonged when the liquid volume fraction was less than 25%. The liquid climbing height along the vane under microgravity increased as the volume fraction of liquid reduced. The climbing velocity of the liquid is half reduction when the liquid volume fraction is small. The time for the liquid transferred from the top of the tank to the liquid outlet can be obtained by climbing velocity. It shows that the maneuverability of the satellite decreases at the end of its life. The above results are applicable to all propellant tank with vertical vanes. These results provide a favorable reference for further optimized design of vertical vane-type propellant tanks.

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12

Song, Liqian, Yan Wang, Dabin Liu, Hua Qian, Xiaoting Rui, and M. Mehdi Shafieezadeh. "Evaluation of the Mechanical Failure Criterion to Consider the Triple Base Propellant Safety Life: Application of Sustainable Renewables for Environmental Hazards." Discrete Dynamics in Nature and Society 2022 (September 22, 2022): 1–8. http://dx.doi.org/10.1155/2022/8395116.

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Implementation of clean energy and renewables is essential for the consideration of environmental impact because it can be implemented in supply chain networks and sustainable management procedures for safety. In order to study the safety life failure criterion of a triple base propellant under the failure mode of mechanical properties, an accelerated aging test, an evaluation method for the launch safety test of gun propellant charge, and a compressive strength test were used. The failure criterion of mechanical properties was obtained by researching the correlation between launch safety change and mechanical property change of samples. Berthelot’s equation was used to predict the safety life of the triple base propellant. The results show that the mechanical failure criterion is “27% reduction of maximum compressive strength.” The safety life at 25°C and 75% humidity is 13.77 years.

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13

Hartwig, Jason W. "Propellant Management Devices for Low-Gravity Fluid Management: Past, Present, and Future Applications." Journal of Spacecraft and Rockets 54, no. 4 (July 2017): 808–24. http://dx.doi.org/10.2514/1.a33750.

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14

Reichel, Yvonne, and Michael E. Dreyer. "Study of Rotating Menisci in a Generic Propellant-Management Device." AIAA Journal 51, no. 8 (August 2013): 1982–92. http://dx.doi.org/10.2514/1.j052461.

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15

Yao, Weixin. "Interoperability: an indispensable propellant of e-China." International Journal of Services and Standards 1, no. 4 (2005): 446. http://dx.doi.org/10.1504/ijss.2005.007471.

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16

Hu, Qi, Yong Li, Hai Lin Pan, and Bao Tang Zhuang. "Microgravity Experiment Research on Orbital Refueling Process in the Vane Type Tank." Applied Mechanics and Materials 390 (August 2013): 53–56. http://dx.doi.org/10.4028/www.scientific.net/amm.390.53.

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Aiming at vented orbital refueling, the microgravity experiment research on orbital refueling process (ORP) is carried out in the paper. By using the microgravity test system of orbital refueling and proper experiment means, the microgravity drop tower (DT) test of all the ORP is accomplished triumphantly, then the transformation process of fuel surface and flow characteristic are obtained, and the extrusion efficiency of the refueling tank is gotten, and the on-orbit propellant resupply performance of VTT is validated. The results indicate that, the orbital refueling in the vane type tank is absolutely feasible, and the performance of propellant management device (PMD) in the tank is good.

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17

Purohit, G. P., and L. D. Loudenback. "Application of etched disk stacks in surface tension propellant management devices." Journal of Propulsion and Power 7, no. 1 (January 1991): 22–30. http://dx.doi.org/10.2514/3.23289.

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18

Collicott, Steven H. "Computing the Effects of Practical Tolerances on Propellant Management Device Performance." AIAA Journal 52, no. 7 (July 2014): 1578–80. http://dx.doi.org/10.2514/1.j052945.

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19

Saravia, Manuel Martín, Luca Bernazzani, Alessio Ceccarini, Alfio Emanuele Vinci, and Fabrizio Paganucci. "Modeling and Characterization of a Thermally Controlled Iodine Feeding System for Electric Propulsion Applications." Aerospace 7, no. 2 (January 23, 2020): 10. http://dx.doi.org/10.3390/aerospace7020010.

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Iodine is considered as a feasible alternative to xenon as a propellant for electric propulsion systems, thanks to its good propulsive performance, high availability, and high storage density. However, as iodine is stored in solid state at ambient temperature, current state-of-the-art propellant management systems are not suitable to be used with it. Moreover, due to its high reactivity, iodine imposes requirements on material-compatibility, hindering the use of mass flow measurement and control systems typically used with other propellants. The architecture of a controlled iodine feeding system for low power (200 W class) ion and Hall effect thrusters is presented and the resulting prototype is described. It consists of a sublimation assembly whose temperature is used to control the tank pressure, a normally-closed ON-OFF valve, and a thermal throttle to perform the fine control of the mass flow rate. A 1D thermal-fluid model concerning the vapor generation in the tank, and its evolution along the different components is detailed. The thermal throttle model has been experimentally verified using air as a working fluid. The model results agree with the measurements of the verification tests in the hypothesis of the presence of an extended region at the entrance of the pipe where the laminar flow velocity and temperature profiles are not fully developed (known as entry flow region). Finally, the system is experimentally characterized and the model of the full system is calibrated using experimental measurements. The calibration shows that the thermal throttle flow presents an entry flow region, that the viscosity is correctly modeled, and that there is a difference between the measured tank temperature and the effective sublimation temperature.

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20

Szelecka, Agnieszka. "Advanced laboratory for testing plasma thrusters and Hall thruster measurement campaign." Nukleonika 61, no. 2 (June 1, 2016): 213–18. http://dx.doi.org/10.1515/nuka-2016-0036.

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Abstract Plasma engines are used for space propulsion as an alternative to chemical thrusters. Due to the high exhaust velocity of the propellant, they are more efficient for long-distance interplanetary space missions than their conventional counterparts. An advanced laboratory of plasma space propulsion (PlaNS) at the Institute of Plasma Physics and Laser Microfusion (IPPLM) specializes in designing and testing various electric propulsion devices. Inside of a special vacuum chamber with three performance pumps, an environment similar to the one that prevails in space is created. An innovative Micro Pulsed Plasma Thruster (LμPPT) with liquid propellant was built at the laboratory. Now it is used to test the second prototype of Hall effect thruster (HET) operating on krypton propellant. Meantime, an improved prototype of krypton Hall thruster is constructed.

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21

Skoner, David P. "Balancing Safety and Efficacy in Pediatric Asthma Management." Pediatrics 109, Supplement_E1 (February 1, 2002): 381–92. http://dx.doi.org/10.1542/peds.109.se1.381.

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In the treatment of childhood asthma, balancing safety and efficacy is key to achieving optimal therapeutic benefit. Inhaled corticosteroids (ICS), because of their efficacy, remain a cornerstone in managing persistent pediatric asthma, but also are associated with significant adverse effects, including growth suppression. Consequently, careful attention must be given to balancing their safety and efficacy, which should include an understanding of airway patency and systemic absorption (dose, disease severity, propellant and lipophilicity of inhalant), bioavailability (inhalation technique, propellant, delivery devices, and hepatic first-pass metabolism), techniques for using minimum effective doses (dosing time, add-on therapy), and reduction of other exacerbating conditions (allergens, influenza, upper-respiratory diseases). The growth-suppressive effects of ICS may be most evident in children with: 1) mild asthma because the relatively high airway patency may facilitate increased levels of deposition and steroid absorption in more distal airways, and 2) evening dosing that may reduce nocturnal growth hormone activity. A step-down approach targeting a minimum effective dose and once-daily morning dosing is suggested for achieving the most acceptable safety/efficacy balance with ICS. The achievement of regular, safe, and correct ICS use requires significant knowledge and time for both caregiver and patient. Chromones, methylxanthines, long-acting β-agonists, and leukotriene receptor antagonists are currently available alternatives to ICS for the control of persistent childhood asthma. Chromones are safe but, like methylxanthines, are difficult to use and frequently result in compromised effectiveness. Long-acting β-agonists are not recommended as monotherapy for persistent asthma. Several factors that support leukotriene receptor antagonists as a therapeutic option for mild-to-moderate persistent pediatric asthma include established efficacy, good safety profiles, and simple, oral dosing. Physicians must evaluate and compare the balance of safety and efficacy for each agent to determine the appropriate asthma therapy for individual patients.

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22

Collicott, Steven H. "Convergence Behavior of Surface Evolver Applied to a Generic Propellant-Management Device." Journal of Propulsion and Power 17, no. 4 (July 2001): 845–51. http://dx.doi.org/10.2514/2.5815.

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23

Lee, Kyounghwan, Seonghyeon Park, Hongjae Kang, and Jongkwang Lee. "Non-ignition Evaluation Method for Hypergolic Propellant Using Microreactor." Journal of the Korean Society of Propulsion Engineers 26, no. 2 (April 30, 2022): 20–27. http://dx.doi.org/10.6108/kspe.2022.26.2.020.

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24

Sanghavi, R. R., P. J. Kamale, M. A. R. Shaikh, S. D. Shelar, K. Sunil Kumar, and Amarjit Singh. "HMX based enhanced energy LOVA gun propellant." Journal of Hazardous Materials 143, no. 1-2 (May 2007): 532–34. http://dx.doi.org/10.1016/j.jhazmat.2006.09.087.

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25

Martinez, Rafael A., and Mitchell L. R. Walker. "Propellant Thermal Management Effect on Neutral Residence Time in Low-Voltage Hall Thrusters." Journal of Propulsion and Power 29, no. 3 (May 2013): 528–39. http://dx.doi.org/10.2514/1.b34702.

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26

Liu, J. T., C. Zhou, Y. L. Wu, B. T. Zhuang, and Y. Li. "Numerical investigation of performance of vane-type propellant management device by VOF methods." IOP Conference Series: Materials Science and Engineering 72, no. 4 (January 15, 2015): 042041. http://dx.doi.org/10.1088/1757-899x/72/4/042041.

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27

Lee, Hyunseob, Jongyun Oh, Heesung Yang, Sunyoung Lee, and Taeock Khil. "Burn-back Analysis for Propellant Grains with Embedded Metal Wires." Journal of the Korean Society of Propulsion Engineers 26, no. 2 (April 30, 2022): 12–19. http://dx.doi.org/10.6108/kspe.2022.26.2.012.

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28

Wei, YueXing, XiaoQian Chen, and YiYong Huang. "Interior corner flow theory and its application to the satellite propellant management device design." Science China Technological Sciences 54, no. 7 (April 12, 2011): 1849–54. http://dx.doi.org/10.1007/s11431-011-4374-4.

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29

Darr, S. R., C. F. Camarotti, J. W. Hartwig, and J. N. Chung. "Hydrodynamic model of screen channel liquid acquisition devices for in-space cryogenic propellant management." Physics of Fluids 29, no. 1 (January 2017): 017101. http://dx.doi.org/10.1063/1.4973671.

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30

Szelecka, Agnieszka, Jacek Kurzyna, and Loic Bourdain. "Thermal stability of the krypton Hall effect thruster." Nukleonika 62, no. 1 (March 1, 2017): 9–15. http://dx.doi.org/10.1515/nuka-2017-0002.

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Abstract The Krypton Large IMpulse Thruster (KLIMT) ESA/PECS project, which has been implemented in the Institute of Plasma Physics and Laser Microfusion (IPPLM) and now is approaching its final phase, was aimed at incremental development of a ~500 W class Hall effect thruster (HET). Xenon, predominantly used as a propellant in the state-of-the-art HETs, is extremely expensive. Krypton has been considered as a cheaper alternative since more than fifteen years; however, to the best knowledge of the authors, there has not been a HET model especially designed for this noble gas. To address this issue, KLIMT has been geared towards operation primarily with krypton. During the project, three subsequent prototype versions of the thruster were designed, manufactured and tested, aimed at gradual improvement of each next exemplar. In the current paper, the heat loads in new engine have been discussed. It has been shown that thermal equilibrium of the thruster is gained within the safety limits of the materials used. Extensive testing with both gases was performed to compare KLIMT’s thermal behaviour when supplied with krypton and xenon propellants.

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31

Cho, Janghee, Donghee Lee, Sulhee Kim, Donggeun Lee, and Heejang Moon. "Study on Breakup Characteristics of Gel Propellant Using Pressure Swirl Injector." Journal of the Korean Society of Propulsion Engineers 25, no. 5 (October 31, 2021): 10–17. http://dx.doi.org/10.6108/kspe.2021.25.5.010.

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32

Bordeleau, Geneviève, Richard Martel, Mathieu Drouin, Guy Ampleman, and Sonia Thiboutot. "Biodegradation of Nitroglycerin from Propellant Residues on Military Training Ranges." Journal of Environmental Quality 43, no. 2 (March 2014): 441–49. http://dx.doi.org/10.2134/jeq2013.06.0241.

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33

Zhang, S., G. J. Tang, M. I. Friswell, and D. J. Wagg. "Multi-objective Optimization of Zero Propellant Spacecraft Attitude Maneuvers." Journal of Optimization Theory and Applications 163, no. 3 (February 12, 2014): 926–48. http://dx.doi.org/10.1007/s10957-014-0524-8.

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34

Dey, D., I. Krukkert, and E. Osse. "Inclusion of innovative technology in integrated waste management of a city: case of Bogura, Bangladesh." Journal of Water, Sanitation and Hygiene for Development 10, no. 3 (July 20, 2020): 608–14. http://dx.doi.org/10.2166/washdev.2020.046.

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Abstract Bogura is the largest municipality in Bangladesh by population. Its huge population and agri-industry produces a great deal of solid, faecal and industrial waste which has been a matter of concern for the municipality. IRC started working for a solution and completed a pre-feasibility and feasibility study to find innovative technologies and an operation model. The feasibility study has produced an integrated solution of faecal sludge, municipal solid waste, agri-waste and aerosol can recycling model which also helps to reduce surface and ground water contamination. The solution integrates conventional anaerobic digestion with new torrefaction and aerosol-propellant capture technologies which treats the municipality solid waste and aerosol cans to produce biofuel and liquid petroleum gas, respectively.

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35

Hu, Q., Y. Li, H. L. Pan, J. T. Liu, and B. T. Zhuang. "Numerical analysis and experiment research on fluid orbital performance of vane type propellant management device." IOP Conference Series: Materials Science and Engineering 72, no. 4 (January 15, 2015): 042042. http://dx.doi.org/10.1088/1757-899x/72/4/042042.

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36

Berglund, Michael D., Charles E. Bassett, James M. Kelso, John Mishic, and Dean Schrage. "The Boeing Delta IV launch vehicle—Pulse-settling approach for second-stage hydrogen propellant management." Acta Astronautica 61, no. 1-6 (June 2007): 416–24. http://dx.doi.org/10.1016/j.actaastro.2007.01.048.

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37

Shim, Yong-Ho, and Ji-Tae Kim. "Successful plant scale production of solid propellant recycling from obsolete ammunition." Journal of Material Cycles and Waste Management 19, no. 2 (April 12, 2016): 898–905. http://dx.doi.org/10.1007/s10163-016-0495-y.

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38

Lee, Sook, Taek-joon Son, Sang-Min Choi, and Jin-Hyo Bae. "Study on Deriving the Buckling Knockdown Factor of a Common Bulkhead Propellant Tank." Journal of the Korean Society of Propulsion Engineers 26, no. 3 (June 30, 2022): 10–21. http://dx.doi.org/10.6108/kspe.2022.26.3.010.

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39

Kovtun, V. S. "The methodology of variable management of propellant fuel consumption by jet-propulsion engines of a spacecraft." Thermal Engineering 59, no. 13 (December 2012): 960–69. http://dx.doi.org/10.1134/s0040601512130046.

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40

Kaul, S. N., N. N. Rao, T. Nandy, and L. Szpyrkowicz. "Wastewater management for hazardous chemicals ‐ disposal of ammonium perchlorate wastes from propellant production for space vehicles." Toxicological & Environmental Chemistry 81, no. 3-4 (June 2001): 111–22. http://dx.doi.org/10.1080/02772240109359024.

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41

Downes, Alexander B. "Restraint or Propellant? Democracy and Civilian Fatalities in Interstate Wars." Journal of Conflict Resolution 51, no. 6 (December 2007): 872–904. http://dx.doi.org/10.1177/0022002707308079.

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42

Gonzalez, Daniel, and Hartmut Derendorf. "Ciclesonide in the Management of Asthma." Clinical Medicine. Therapeutics 1 (January 2009): CMT.S2133. http://dx.doi.org/10.4137/cmt.s2133.

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Ciclesonide is a novel inhaled corticosteroid (ICSs) approved in most countries for the management of persistent asthma. Although inhaled corticosteroids are first-line therapy in the treatment of asthma, long term use and high-doses of these products may result in significant side effects. When developing a new ICSs, the goal is to identify a drug with comparable (or superior) efficacy to active comparators, and an improved safety profile. Ciclesonide is a prodrug which is administered through a hydrofluoroalkane-propellant metered dose inhaler (HFA-MDI). Once it reaches the lungs, the parent compound is metabolized by esterases to desisobutyryl ciclesonide (des-CIC), an active metabolite with a 100-fold greater affinity for the glucocorticoid receptor. Ciclesonide has a unique pharmacokinetic-pharmacodynamic profile which confers an improved therapeutic ratio. Several clinical trials have shown that its efficacy is superior to placebo and similar to several active comparators. However, its high pulmonary deposition and on-site activation minimizes the risk for local side effects. Also, its low oral bioavailability, high hepatic clearance, and extensive plasma protein binding, among other factors, decrease the risk for systemic side effects. Doses of ciclesonide as high as 1280 μg/day (ex-actuator) result in minimal hypothalamic-pituitary-adrenal (HPA) axis suppression, a measure commonly used to assess systemic bioavailability for an ICSs. This review will provide a summary of ciclesonide's role in the management of asthma, including a discussion of relevant clinical trials designed to evaluate its efficacy and safety.

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Kim, Kahee, and Jung-Ho Park. "Impact Sensitivity and Friction Sensitivity of HTPB Based Propellant According to the Aluminum Content." Journal of the Korean Society of Propulsion Engineers 25, no. 6 (December 31, 2021): 60–65. http://dx.doi.org/10.6108/kspe.2021.25.6.060.

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Huang, Zhiyong, Guofeng Jin, and Xuanjun Wang. "NUMERICAL SIMULATION APPLIED FOR UNSYMMETRICAL DIMETHYLHYDRAZINE PROPELLANT GAS DISPERSION BASED ON CFD TECHNOLOGY." Environmental Engineering and Management Journal 10, no. 7 (2011): 971–74. http://dx.doi.org/10.30638/eemj.2011.139.

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TALAWAR, M., J. NAIR, S. PUNDALIK, R. SATPUTE, and S. VENUGOPALAN. "Diaminofurazan (DAF): Thermolysis and evaluation as ballistic modifier in double base propellant." Journal of Hazardous Materials 136, no. 3 (August 25, 2006): 978–81. http://dx.doi.org/10.1016/j.jhazmat.2006.01.047.

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Damse, R. S., and A. K. Sikder. "Role of inorganic additives on the ballistic performance of gun propellant formulations." Journal of Hazardous Materials 154, no. 1-3 (June 2008): 888–92. http://dx.doi.org/10.1016/j.jhazmat.2007.10.103.

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Li, Miaomiao, Fengsheng Li, Ruiqi Shen, and Xiaode Guo. "Molecular dynamics study of the structures and properties of RDX/GAP propellant." Journal of Hazardous Materials 186, no. 2-3 (February 2011): 2031–36. http://dx.doi.org/10.1016/j.jhazmat.2010.12.101.

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Chu, I. Tien, Shu Yao Tsai, Wan Tran Huang, Jo Ming Tseng, Jin Shuh Li, and Chun Ping Lin. "Modelling Method for Preventing Thermal Runaway Reaction Accident of Thermal Reactive Material." Advanced Materials Research 936 (June 2014): 2030–34. http://dx.doi.org/10.4028/www.scientific.net/amr.936.2030.

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Thermally reactive materials have caused many serious accidents involving storage and transportation, due to being thermally reactive. The safe storage and management of these materials still is a critical problem in many countries. We studied the thermal hazard of thermal reactive materials, such as a propellant, by employing differential scanning calorimetry (DSC) non-isothermal tests and isothermal tests, and then comparing the kinetic parameters by isothermal and non-isothermal of kinetics, avoiding the mistaken results of the single thermal analysis model. The chosen approach was to obtain reliable kinetics of thermal decomposition by safety and effective technology by modelling method, which acquired the safety parameters of storage condition that could be applied as thermal reactive materials safer design during storage safety conditions and relevant operations.

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Cassol, Alessandra, Claudio Reis Gonçalo, André Santos, and Roberto Lima Ruas. "The strategic management of intellectual capital: a model based on absorptive capacity to enhance innovation." Revista Ibero-Americana de Estratégia 15, no. 1 (March 1, 2016): 27–43. http://dx.doi.org/10.5585/ijsm.v15i1.2161.

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The intellectual capital is noticed as a strategic resource capable of being propellant of innovation. In this context, it is suggested that the intellectual capital and the absorptive capacity may be influencing of the capacity to innovate in organizations.. This article aims to propose and analyze a Model of Strategic Management of Intellectual Capital from practices of absorptive capacity as enhancement of innovation. It is used as a method an exploratory research with the approach of quantitative and application of questionnaires for a sample of 104 managers. In the data analysis, it is used the technique of structural equation modeling through PLS (Partial Least Squares), with the analysis of path coefficients, we observe a strong relation among the constructs, what confirmed the hypotheses of the research. We verify that the organizational practices adopted for the development of intellectual capital, absorptive capacity and innovation are: a) ongoing training of employees; b) programs of suggestions; c) assimilation of new technologies; d) application of technical knowledge; e) partnerships with supporting innovation institutions. As contributions, the found evidences indicate that the absorptive capacity promotes the advance of innovation, and it´s still possible to observe management practices of intellectual capital from organizational routines.

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Miller, M. S., B. M. Rice, A. J. Kotlar, and R. J. Cramer. "A new approach to propellant formulation: minimizing life-cycle costs through science-based design." Clean Products and Processes 2, no. 1 (May 4, 2000): 0037–46. http://dx.doi.org/10.1007/s100980050049.

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