Relevant bibliographies by topics / Propellant management

Academic literature on the topic 'Propellant management'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Propellant management"

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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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Propellant management"

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Chai, Patrick R. "Stochastic feasibility assessments of orbital propellant depot and commercial launch enabled space exploration architectures." Diss., Georgia Institute of Technology, 2014. http://hdl.handle.net/1853/54291.

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The 2010 National Space Policy of the United State of America introduced by President Obama directed NASA to set far reaching exploration milestones that included a crewed mission to a Near Earth Asteroid by 2025 and a crewed mission to Martian orbit by the mid-2030s. The policy was directly influenced by the recommendations of the 2009 Review of United States Human Space Flight Plans Committee, which called for an evolutionary approach to human space exploration and emphasized the criticality of budgetary, programmatic, and program sustainability. One potential method of improving the sustainability of exploration architectures is the utilization of orbital propellant depots with commercial launch services. In any exploration architecture, upwards of seventy percent of the mass required in orbit is propellant. A propellant depot based architecture allows propellant to be delivered in small increments using existing commercial launch vehicles, but will require three to five times the number of launches as compared to the using the NASA planned 70 to 130 metric ton heavy lift launch system. Past studies have shown that the utilization of propellant depots in exploration architectures have the potential of providing the sustainability that the Review of United States Human Space Flight Plans Committee emphasized. However, there is a lack of comprehensive analysis to determine the feasibility of propellant depots within the framework of human space exploration. The objective of this research is to measure the feasibility of a propellant depot and commercial launch based exploration architecture by stochastic assessment of technical, reliability, and economic risks. A propellant depot thermal model was developed to analyze the effectiveness of various thermal management systems, determine their optimal configuration, quantify the uncertainties in the system models, and stochastically compute the performance feasibility of the propellant depot system. Probabilistic cost analysis captured the uncertainty in the development cost of propellant depots and the fluctuation of commercial launch prices, and, along with the cost of launch failures, provided a metric for determining economic feasibility. Probabilistic reliability assessments using the launch schedule, launch reliability, and architecture requirements of each phase of the mission established launch success feasibility. Finally, an integrated stochastic optimization was performed to determine the feasibility of the exploration architecture. The final product of this research is an evaluation of propellant depots and commercial launch services as a practical method to achieving economic sustainability for human space exploration. A method for architecture feasibility assessment is demonstrated using stochastic system metrics and applied in the evaluation of technical, economic, and reliability feasibility of orbital propellant depots and commercial launch based exploration architectures. The results of the analysis showed the propellant depots based architectures to be technically feasible using current commercial launch vehicles, economically feasible for having a program budget less than $4 billion per year, and have launch reliability approaching the best single launch vehicle, Delta IV, with the use of redundant vehicles. These results serve to provide recommendations on the use of propellant depots in exploration architectures to the Moon, Near Earth Objects, Mars, and beyond.The 2010 National Space Policy of the United State of America introduced by President Obama directed NASA to set far reaching exploration milestones that included a crewed mission to a Near Earth Asteroid by 2025 and a crewed mission to Martian orbit by the mid-2030s. The policy was directly influenced by the recommendations of the 2009 Review of United States Human Space Flight Plans Committee, which called for an evolutionary approach to human space exploration and emphasized the criticality of budgetary, programmatic, and program sustainability. One potential method of improving the sustainability of exploration architectures is the utilization of orbital propellant depots with commercial launch services. In any exploration architecture, upwards of seventy percent of the mass required in orbit is propellant. A propellant depot based architecture allows propellant to be delivered in small increments using existing commercial launch vehicles, but will require three to five times the number of launches as compared to the using the NASA planned 70 to 130 metric ton heavy lift launch system. Past studies have shown that the utilization of propellant depots in exploration architectures have the potential of providing the sustainability that the Review of United States Human Space Flight Plans Committee emphasized. However, there is a lack of comprehensive analysis to determine the feasibility of propellant depots within the framework of human space exploration. The objective of this research is to measure the feasibility of a propellant depot and commercial launch based exploration architecture by stochastic assessment of technical, reliability, and economic risks. A propellant depot thermal model was developed to analyze the effectiveness of various thermal management systems, determine their optimal configuration, quantify the uncertainties in the system models, and stochastically compute the performance feasibility of the propellant depot system. Probabilistic cost analysis captured the uncertainty in the development cost of propellant depots and the fluctuation of commercial launch prices, and, along with the cost of launch failures, provided a metric for determining economic feasibility. Probabilistic reliability assessments using the launch schedule, launch reliability, and architecture requirements of each phase of the mission established launch success feasibility. Finally, an integrated stochastic optimization was performed to determine the feasibility of the exploration architecture. The final product of this research is an evaluation of propellant depots and commercial launch services as a practical method to achieving economic sustainability for human space exploration. A method for architecture feasibility assessment is demonstrated using stochastic system metrics and applied in the evaluation of technical, economic, and reliability feasibility of orbital propellant depots and commercial launch based exploration architectures. The results of the analysis showed the propellant depots based architectures to be technically feasible using current commercial launch vehicles, economically feasible for having a program budget less than $4 billion per year, and have launch reliability approaching the best single launch vehicle, Delta IV, with the use of redundant vehicles. These results serve to provide recommendations on the use of propellant depots in exploration architectures to the Moon, Near Earth Objects, Mars, and beyond.
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Hartwig, Jason W. "Liquid Acquisition Devices for Advanced In-Space Cryogenic Propulsion Systems." Case Western Reserve University School of Graduate Studies / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=case1396562473.

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Books on the topic "Propellant management"

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Kemme, Michael R. Reducing air pollutant emissions from solvent multi-base propellant production. [Champaign, IL]: US Army Corps of Engineers, Construction Engineering Research Laboratory, 1999.

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Miks, Kathryn F. Reduced smoke propellant binder residue as a fuel source. [Champaign, IL]: US Army Corps of Engineers, Construction Engineering Research Laboratories, 1997.

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Office, General Accounting. Space shuttle: Declining budget and tight schedule could jeopardize space station support : report to the Chairman, Subcommittee on Oversight of Government Management and the District of Columbia, Committee on Governmental Affairs, U.S. Senate. Washington, D.C: The Office, 1995.

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Office, General Accounting. Space shuttle: NASA must reduce costs further to operate within future projected funds : report to Congressional requesters. Washington, D.C: The Office, 1995.

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Office, General Accounting. Space shuttle: Need to sustain launch risk assessment process improvements : report to the Honorable James A. Hayes, House of Representatives. Washington, D.C: The Office, 1996.

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Office, General Accounting. Space shuttle: Follow-up evaluation of NASA's solid rocket motor procurement : report to the Chairman, Committee on Government Operations, House of Representatives. Washington, D.C: The Office, 1989.

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Office, General Accounting. Space shuttle: Status of advanced solid rocket motor program : report to the Chair, Subcommittee on Government Activities and Transportation, Committee on Government Operations, House of Representatives. Washington, D.C: U.S. General Accounting Office, 1992.

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Office, General Accounting. Space shuttle: NASA's major changes to flight hardware : fact sheet for the Chairman, Committee on Science, Space, and Technology, House of Representatives. Washington, D.C: The Office, 1988.

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Office, General Accounting. Space shuttle: Further improvements needed in NASA's modernization efforts : report to congressional requesters. Washington, D.C. (P.O. Box 37050, Washington 20013): U.S. General Accounting Office, 2004.

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Office, General Accounting. Space shuttle: Follow-up evaluation of NASA's solid rocket motor procurement : report to the Chairman, Committee on Government Operations, House of Representatives. Washington, D.C: The Office, 1989.

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Book chapters on the topic "Propellant management"

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Martínez-Pastor, J., Patricio Franco, Domingo Moratilla, and Pedro J. Lopez-Garcia. "Optimization of Forming Processes for Gelled Propellant Manufacturing." In Management and Industrial Engineering, 1–28. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-60432-9_1.

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Liu, Yang, Jiu-ling Sui, Yu Zhao, Fu-ting Bao, and Wei-hua Hui. "Large Scale Parallel Algorithms for 3D Grain Burnback Analysis of Solid Propellant Rocket Motors." In Proceedings of the 22nd International Conference on Industrial Engineering and Engineering Management 2015, 797–806. Paris: Atlantis Press, 2016. http://dx.doi.org/10.2991/978-94-6239-180-2_75.

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Cooperrider, David L. "Propelling PRME's promise." In Responsible Management Education, 36–46. London: Routledge, 2021. http://dx.doi.org/10.4324/9781003186311-7.

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Benru, Li, and Guo Shuling. "Propellent Management for Satellite Propulsion System under Microgravity." In Microgravity Fluid Mechanics, 453–57. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-50091-6_47.

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Hartwig, Jason William. "Optimal Propellant Management Device for a Small-Scale Liquid Hydrogen Propellant Tank." In Liquid Acquisition Devices for Advanced In-Space Cryogenic Propulsion Systems, 343–69. Elsevier, 2016. http://dx.doi.org/10.1016/b978-0-12-803989-2.00014-0.

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Hira, Harmanjit. "Chapter-09 Inhalation Devices and Propellants." In Step by Step� Management of Bronchial Asthma, 205–24. Jaypee Brothers Medical Publishers (P) Ltd., 2008. http://dx.doi.org/10.5005/jp/books/10830_9.

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Majchrzak, Tim A., Jan C. Dageförde, Jan Ernsting, Christoph Rieger, and Tobias Reischmann. "How Cross-Platform Technology Can Facilitate Easier Creation of Business Apps." In Apps Management and E-Commerce Transactions in Real-Time, 104–40. IGI Global, 2017. http://dx.doi.org/10.4018/978-1-5225-2449-6.ch005.

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Applications for mobile devices – apps – have seen unprecedented growth in importance. Ever better apps keep propelling the proliferation of mobile computing. App development is rather easy, particularly if it is based on Web technology. However, implementing apps that are user friendly and useful in the long-run is cumbersome. Thereby, it typically is expensive for corporate developers. Nonetheless, business apps are embraced by enterprises. To overcome the overhead of developing separately for multiple platforms and to mitigate the problems of device fragmentation, cross-platform development approaches are employed. While many such approaches exist, few have found widespread usage. In this chapter, we argue what the path towards future solutions could look like. We thereby take a rather technological look, but always keep business-orientation in mind. Our findings suggest that much effort is needed to enable the next generations of business apps. However, such apps will provide many merits and possibilities. Moreover, they provide the chance to master several of today's challenges.
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Campbell, Laurie O., Joshua H. Truitt, Christine P. Herlihy, and Jarrad D. Plante. "A Thematic Analysis of Leadership Qualities of Women Leaders in Technology." In Encyclopedia of Strategic Leadership and Management, 1–15. IGI Global, 2017. http://dx.doi.org/10.4018/978-1-5225-1049-9.ch001.

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There is known gender disparity and inequity of women leaders in technology and STEM fields. A rapid gender decline in these burgeoning fields has sparked a national renewed interest in purposefully attracting and mentoring more women to roles in technology leadership. The gender disparity is not only in attracting young women to consider a technology or STEM career but it is in women staying engaged once they choose a career in these areas. Efforts have been made to improve the sustainability of women in technology leadership roles. Books, articles, and manuscripts have been written, formal and informal meetings and corporate awareness programs have been conducted and mentorship programs abound to attract girls to consider technology as a career choice. Further, identifying women role models has been a strategy employed to promote gender awareness. Within the chapter, the qualitative content analysis study investigates four women roles models and identifies leadership characteristics of these known women leaders in technology. It answers the following questions: What are the leadership characteristics of known women role models in technology? What do these leaders value? How do their differences impact their leadership in the field? Finally, what have they identified as propelling them towards innovation and discovery?
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Taheri, Babak, Roya Rahimi, and Dimitrios Buhalis. "Conclusion The Sharing Economy Perspectives, opportunities and challenges." In The Sharing Economy and the Tourism Industry. Goodfellow Publishers, 2022. http://dx.doi.org/10.23912/9781915097064-5098.

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The sharing economy, which can be defined as an economic system in which assets and services are shared between people, has intensified the ability for human interaction as well as peer-to-peer (P2P) commercial exchange (Altinay & Taheri, 2019, p.180). Since the inception of the World Wide Web in 1992, the internet has revolutionised marketplaces. A range of unprecedented implications emerged for users, propelling the dramatic evolution of the marketplace. A range of electronic, mobile, and social business models emerged to support a range of diverse marketplaces. The development of new business models facilitated the sharing of underutilized assets. The ‘Sharing Economy’ effectively was developed to support sharing of products and services that often stayed idle for long periods of time. Sharing economy service ecosystems emerged to facilitate sharing of resources and help actors exchange resources, interact, and create value and meaning. The sharing economy is a fast-growing and heavily debated phenomenon in management and marketing literature. It had a massive impact on consumer behaviours and has grown in both scale and scope over the past years via different platforms. Examples include Airbnb for apartments, Blablacar for cars and Peerby for tools. Apart from positive economic consequences, the sharing economy can have positive environmental and social effects. It gives people the opportunity to reuse goods and services, improving sustainability. Sharing can bring people together and stimulate social cohesion in neighbourhoods.
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Conference papers on the topic "Propellant management"

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Notardonato, W., G. Haddad, K. V. Krishna-Murty, J. Zhu, J. S. Kapat, and L. C. Chow. "Miniature Joule–Thomson (JT) Cryocoolers for Propellant Management." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-61545.

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Boil-off of cryogenic propellants is an issue of concern in any space mission. There could be boil-off of liquid propellants in the cryogenic storage tank, transfer line or in the space vehicle external tank itself due to heat leak. The current insulation technology uses a multilayered thermal protective coating of 304 Stainless Steel and Welded Invar, which allows the propellant to withstand the extreme internal and external temperature variations generated during pre-launch, launch, and flight operations, which does not provide for zero boil-off (ZBO). Usage of a cryocooler to prevent propellant boil-off would potentially reduce the launch costs. Owing to its attractive features like simplicity, compactness and rapid cool-down characteristics, an innovative concept of using Joule-Thomson (JT) cryocoolers for prechilling, densification and ZBO applications of cryogenic propellants is focused upon. The liquid oxygen propellant transfer line at NASA Kennedy Space Center is considered for demonstration of the above concept. Various thermodynamic cycle parameters are optimized for the cryocooler to make the demonstration possible. Cycle optimization is done also taking into account the feasibility to develop some crucial components for the JT cryocooler like a micro channel heat recuperator and cold heads. Current state of developments in the heat exchanger is briefly described. Some advantages of using miniaturized cryocoolers in launch vehicle operations are also discussed.
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Yendler, Boris. "Active Propellant Management." In SpaceOps 2006 Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-5569.

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DOMINICK, S., and J. TEGART. "Propellant management in toroidal tanks." In 21st Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1231.

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OBERG, D., and P. MISRA. "Propellant management operations on GSTAR-III." In 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1800.

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Tegart, James, and James Tegart. "A vane type propellant management device." In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-3028.

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Hartwig, Jason W. "A Detailed Historical Review of Propellant Management Devices for Low Gravity Propellant Acquisition." In 52nd AIAA/SAE/ASEE Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-4772.

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Collicott, Steven H., Emily A. Beckman, and Praveen Srikanth. "Conformal Tanks: Small-Sat Propellant Management Technology." In AIAA Propulsion and Energy 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3874.

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Behruzi, Philipp, Jorg Klatte, Nicolas Fries, Gaston Netter, Thilo Kranz, and Adriana Sirbi. "Cryogenic Propellant Management during Ballistic Flight Phases." In 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4047.

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Konopka, Martin, Anna Schubert, Diana Gaulke, Dennis Haake, Thorben Bruns, Alexander Fischer, and Jens Gerstmann. "Liquid Hydrogen Propellant Management Experiments and Simulations." In 2018 Joint Propulsion Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4941.

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JAEKLE, JR., D. "Propellant management device conceptual design and analysis - Sponges." In 29th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-1970.

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Reports on the topic "Propellant management"

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Audley, M. P. Logisitcs Management Report for U.S. Navy Propellant-Actuated Devices (PAD). Fort Belvoir, VA: Defense Technical Information Center, June 2002. http://dx.doi.org/10.21236/ada404733.

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2

Audley, Mike P. Logistics Management Report for U.S. Navy Propellant-Actuated Devices (PAD). Fort Belvoir, VA: Defense Technical Information Center, June 2003. http://dx.doi.org/10.21236/ada417726.

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