Relevant bibliographies by topics / Pressurized cabins

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Pressurized cabins'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 February 2022

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Journal articles on the topic "Pressurized cabins"

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Gusev, Sergey A., and Vladimir N. Nikolaev. "Optimization Parameters of Air-conditioning and Heat Insulation Systems of a Pressurized Cabins of Long-distance Airplanes." IOP Conference Series: Materials Science and Engineering 302 (January 2018): 012042. http://dx.doi.org/10.1088/1757-899x/302/1/012042.

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Valko, Peter C., Jack P. Campbell, David L. McCarty, Dennis Martin, and Joe Turnbull. "Prehospital Use of Pulse Oximetry in Rotary-Wing Aircraft." Prehospital and Disaster Medicine 6, no. 4 (1991): 421–28. http://dx.doi.org/10.1017/s1049023x00038905.

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AbstractA prospective study of 200 patients was conducted to evaluate the use of pulse oximetry as an adjunct to clinical monitoring of critically ill patients transported by rotary-wing aircraft with non-pressurized cabins. Thirty-four subjects (17%) were found to have significant hemoglobin desaturation of less than 90%, as defined by pulse oximetry (SpO2). Data were recorded continuously for later review. Desaturation often was noted prior to alterations in vital signs or clinical appearance. In 32 of the 34 hypoxemic subjects (94%), therapeutic interventions corrected the low SpO2. The use of pulse oximetry permitted measures for cardiorespiratory support to be instituted and assessed more rapidly than otherwise would have been possible. The availability of a continuous record of SpO2 facilitated detailed review of case management. It is concluded that the use of pulse oximetry is a practical and valuable adjunct for monitoring critically ill patients transported by rotary-wing aircraft.
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Coste, Olivier, Pascal Van Beers, and Yvan Touitou. "Impact of Hypobaric Hypoxia in Pressurized Cabins of Simulated Long‐Distance Flights on the 24 h Patterns of Biological Variables, Fatigue, and Clinical Status." Chronobiology International 24, no. 6 (2007): 1139–57. http://dx.doi.org/10.1080/07420520701800702.

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Hitch, H. P. Y. "Pressure cabins of elliptic cross section." Aeronautical Journal 92, no. 916 (1988): 207–23. http://dx.doi.org/10.1017/s0001924000016158.

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Some observers believe that there will be such growth in the travelling public and such constraint on airport and airspace usage that, by early in the 2000s. very large passenger carrying aircraft will be required. By ‘very large’ is meant anything from 1,000 to 2,000 seaters. Whilst the problems which come to mind when musing on this possibility are mostly those of ‘passenger flow’ in the widest sense and rather less related to the vehicle itself, there are some issues related to the vehicle which suggest themselves. One is the choice of fuselage cross section. Because cabins have to be pressurised (10 psi is a typical figure for cruise altitudes up to say 40,000 ft), it has been the norm to utilise circular cross sections (or double-bubble type) since the pressure forces are contained by hoop loads only, without frame bending, which affords a light and fatigue-insensitive structure (Fig. 1).
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MOHAMED, SALAMA, and REFAT EL-BANNA. "A THERMODYNAMICAL ANALYSIS OF AN A/C PRESSURIZED CABIN." International Conference on Aerospace Sciences and Aviation Technology 1, CONFERENCE (1985): 1–15. http://dx.doi.org/10.21608/asat.1985.26518.

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Khan, Liquan, Gang, Imran, Waqas, and Zaidi. "Concept Design of the Underwater Manned Seabed Walking Robot." Journal of Marine Science and Engineering 7, no. 10 (2019): 366. http://dx.doi.org/10.3390/jmse7100366.

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In this paper, a novel concept designed of a multi-legged underwater manned seabed walking robot is presented. The robot will be used in both shallow water current (1–2 m/sec) and deep water up to 500 m. It is powered by an external electric power source through tether cable. It walks on the seabed with six legs, which makes it distinct from conventional screw-propelled underwater robots. It can walk calmly without making the water turbid. Two anterior arms act as manipulators. All leg joints and manipulators are controlled by Brushless Direct Current Motors. Motivation for this concept comes from soldier crab that walk mostly forward and has an egg-shaped body. It is operated by a pilot sitting in a pressurized cabin, and promptly control operations of the robot and manipulator. Preliminary design of the pressurized cabin, using an empirical formula, “ASME PVHO-1 2007” standard, and validation was carried out through ANSYS Workbench. Hydrodynamic forces acting on the robot body and legs are utilized to withstand the water current and external forces to adjust legs and body posture for stability. Buoyancy rules are employed to control its rising and diving motion. All key technologies employed in the development of the robot and their approaching methods are explained. It will provide a safe operation space for humans in underwater operations.
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Quevreaux, Jason, and Christopher Cropsey. "In-Flight Hypoxemia in a Tracheostomy-Dependent Infant." Case Reports in Anesthesiology 2017 (2017): 1–5. http://dx.doi.org/10.1155/2017/3210473.

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Millions of passengers board commercial flights every year. Healthcare providers are often called upon to treat other passengers during in-flight emergencies. The case presented involves an anesthesia resident treating a tracheostomy-dependent infant who developed hypoxemia on a domestic flight. The patient had an underlying congenital muscular disorder and was mechanically ventilated while at altitude. Although pressurized, cabin barometric pressure while at altitude is less than at sea level. Due to this environment patients with underlying pulmonary or cardiac pathology might not be able to tolerate commercial flight. The Federal Aviation Administration (FAA) has mandated a specific set of medical supplies be present on all domestic flights in addition to legislature protecting “Good Samaritan” providers.
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Marchiando, Andrew. "The Lockheed XC-35 and Harry Armstrong, M.D.: Development of the First Practical Pressurized Cabin Airplane." Aerospace Medicine and Human Performance 88, no. 7 (2017): 703–4. http://dx.doi.org/10.3357/amhp.4845.2017.

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Greene, Michael R., and Shane E. Jacobs. "Decompression Sickness Treatment Using a Pressure Suit After Loss of Spacecraft Atmosphere." Aerospace Medicine and Human Performance 91, no. 7 (2020): 571–77. http://dx.doi.org/10.3357/amhp.5413.2020.

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BACKGROUND: Loss of spacecraft atmosphere (LOA) during Earth-Moon transit may require up to 144 h of pressure suit operations. This work investigates the feasibility of DCS treatment in this paradigm and discusses the operational and engineering implications.METHODS: Three scenarios of LOA-induced DCS were considered: a permanent LOA secondary to a 0.25-in (0.64 cm) hole (unrecoverable cabin leak), a transient LOA, and a permanent LOA with early suit over-pressurization (beyond suit specification). Each was simulated in the context of the current Orion spacecraft operational concept with regards to atmosphere and anticipated cabin depress profile. Probability of DCS symptom resolution (P(SR)) was estimated using the previously derived Hypobaric DCS Treatment Model, with ΔP calculated from a Three Region Well-Stirred Tissue (3RWT) bubble dynamics model. Analysis was conducted and analogies drawn from experiences with the development and testing of the Orion Crew Survival System (OCSS).RESULTS: Maintaining 8 psia at 100% Fio2 following LOA resulted in an eventual halt and regression of bubble growth with a P(SR) of 87% (at 8 h, time to symptom onset (Ts) = 105 min, with ambulation). If cabin atmosphere was not restored and psia dropped to 4.3, bubble growth returned, but again eventually slowed and regressed over time (P(SR) = 75% at 21 h). If the leak is repaired within the 8-h period, 8 psid (psia = 22.7) resulted in P(SR) of greater than 95%. Similarly, if the suit was over-pressurized (12 psid/psia) within 3 h after LOA, P(SR) exceeded 95%.DISCUSSION: A launch/entry pressure suit represents a contingency option for DCS management in the event of LOA.Greene MR, Jacobs SE. Decompression sickness treatment using a pressure suit after loss of spacecraft atmosphere. Aerosp Med Hum Perform. 2020; 91(7):571–577.
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Thakran, Marshal, Meenakshi, Jitender Sharma, and Charles Gilbert Martin. "Design and topological optimization of rear pressure bulkhead for a typical aircraft." Aircraft Engineering and Aerospace Technology 93, no. 7 (2021): 1213–20. http://dx.doi.org/10.1108/aeat-05-2020-0097.

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Purpose The purpose of this paper is to evaluate the model of a rear pressure bulkhead with different design optimizations to meet the pressurized cabin requirements of an aircraft. Design/methodology/approach This paper presents the results of the static analysis of a dome-shaped rear pressure bulkhead model designed in Catia-v5. Numerical analysis of model meshed in hyper-mesh and solved using Opti-Struct for iterative design optimizations. Findings All the iterative models are analyzed at 9 Psi. Rear pressure bulkhead designed with L-section stringer shows better results than the model optimized with T-section stringer for the same thickness. The model optimized with L-shaped stinger also reduces the weight of the bulkhead without affecting the structural integrity. Practical implications It has been concluded in this paper that the selection of specific shapes of the stringers shows a significant influence on weight reduction. Originality/value This paper provides a topical, technical insight into the design and development of a rear pressure bulkhead. It also outlines the future development of dome-shaped rear pressure bulkhead.
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Dissertations / Theses on the topic "Pressurized cabins"

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Uehara, Gilberto Takashi. "Avaliação de conforto em cabine pressurizada através de modelo do ouvido humano." Instituto Tecnológico de Aeronáutica, 2006. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=901.

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O presente trabalho fornece uma ferramenta de análise e avaliação de conforto para os passageiros em cabines pressurizadas de aeronaves. A ferramenta foi desenvolvida com base em um modelo matemático que simula as reações do ouvido humano às variações de pressão da cabine da aeronave durante o vôo. A simulação do modelo e análise de resultados foi realizada através da ferramenta de programação Matlab / Simulink. Pôde-se concluir do estudo que existe uma boa aproximação entre os resultados do modelo proposto e os dados contidos na ARP 1270. O modelo possui diferenças maiores para altas taxas de subida e descida, mas tem boa aproximação para as taxas comumente encontradas na aviação comercial. Um estudo de 3 casos foi conduzido para demonstrar a utilização do modelo na análise do conforto de aeronaves comerciais.
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Corbin, Dominique. "Etude de l'oxydation et de la tenue d'elastomeres irradies : consequences sur l'integrite des cables electriques lors d'une situation accidentelle d'un reacteur a eau pressurise." Caen, 2001. http://www.theses.fr/2001CAEN2002.

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Cette these est un apport a la comprehension et a la prevision des consequences sur l'integrite des cables electriques de l'irradiation electronique survenant lors d'une situation accidentelle d'un reacteur a eau pressurisee. Nous avons etudie la radiooxydation et la tenue mecanique de deux elastomeres irradies, l'epdm (terpolymere ethylene-propylene-hexadiene 1,4) et l'hypalon (polyethylene chlorosulfone), constituant respectivement l'isolant et la gaine de ces cables. Dans un premier volet, les conditions d'exposition caracteristiques de la situation accidentelle sont presentees. Elles induisent un profil de dose tres heterogene dans le cable a cause de la faible penetration des electrons. Cette situation contraste avec celle du fonctionnement normal de la centrale et les conditions des tests de qualification. La dose est alors uniforme et deposee par des photons penetrants. Le deuxieme volet traite de la degradation oxydante, dans des conditions de dose et de debit de dose caracteristiques de la situation accidentelle. Des films fins des deux elastomeres (resines de base et polymeres formules) sont irradies par des electrons et les produits oxydes formes, sont doses chimiquement. L'influence, sur la cinetique de radiooxydation, de trois parametres propres a l'irradiation, la pression d'oxygene, le debit de dose et la dose y est presentee. L'effet de l'antioxydant est etudie dans le cas de l'isolant electrique. Le troisieme volet s'attache a decrire les resultats concernant la simulation experimentale du profil de dose de la situation accidentelle sur des plaques des deux elastomeres formules. L'evolution des proprietes mecaniques a la rupture, en fonction de la dose et de l'epaisseur des plaques, y est presentee et analysee en correlation avec les profils d'oxydation.
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Horák, Marek. "Návrh dvoumotorového letounu kategorie pro sběrnou dopravu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2009. http://www.nusl.cz/ntk/nusl-228595.

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This master’s thesis deal with design of EV-55 Outback airplane with pressurized cabin. In this thesis are given common principles and requirements of regulations on construction pressurized cabin. A necessary fuselage modifications and fuselage construction are included. Also construction and build up of air-conditioning system and emergency oxygen system are included. Some parts of this thesis are about weight and balance, definition of pressurized cabin load, simple stability analysis and basic flight performance calculation. At the end of this master’s thesis a result of weight and flight performances are compared with analogous airplanes by other producers.
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Coelho, Ana Catarina Casaleiro. "Psychophysiological Factors Analysis in Unpressurized Aircraft Cabins." Master's thesis, 2014. http://hdl.handle.net/10400.6/6450.

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In the versatile aviation environment, the pilot’s well-being is a crucial and demanding factor which is directly related to his good performance. Adding the fact that most of the aircraft that belong to the light aviation do not have pressurized cabins, this type of aviation can become a dangerous activity for the safety of pilots and passengers. The change in pilot’s performance during the changing of psychological and physiological parameters has proved to be a very significant factor in terms of flight safety. Also the increasing of altitude in different phases of flight corresponds to a reduction in oxygen partial pressure. This occurrence may lead to early symptoms of hypoxia which may become an even greater danger if the pilots do not have time to feel, or recognize their symptoms. A review of international legislation indicates a high tolerance to establish safety limits in this matter, taking into account the unpredictability of reactions of the human body of each pilot for the same flight conditions. This work is generally focused in acquired data during different flight situations, with different pilots and respective processing of data obtained during different tasks of flight. To achieve the proposed objectives the acquired data contain parameters such as altitude, absolute pressure and temperature inside the cabin; as well as registration oximetry, peripheral and cerebral, to study the phenomenon hypoxia. Also comprises electrocardiogram (ECG) and electroencephalogram (EEG) in order to establish a correlation between the influence of mental workload and other physiological parameters during different phases of flight. The specific objective of this research is the acquisition and processing of data collected directly from the aircraft and the pilot, performing flight simulation tests in different scenarios, contributing to trying to define the physiological limits of each individual with the purpose of creating an alert system on board to avoid possible incidents or accidents. This study also aims to suggest a restriction in the legislation on licensing of light aviation, within physiological limits of each individual, thus contributing to a safer flight environment.
No ambiente versátil da aviação, o bem-estar do piloto é um factor crucial e exigente que está directamente relacionado com o seu desempenho. Adicionando o facto da maioria das aeronaves que pertencem á aviação ligeira não possuírem cabines pressurizadas, este tipo de aviação pode tornar-se numa actividade perigosa para a segurança de pilotos e passageiros. A mudança de desempenho dos pilotos aquando da alteração de parâmetros psicológicos e fisiológicos tem-se revelado um fator bastante significativo em termos de segurança de voo. Também o aumento da altitude nas diferentes fases de voo corresponde a uma diminuição da pressão parcial de oxigénio. Esta ocorrência pode levar a sintomas iniciais de hipoxia o que se pode tornar um perigo ainda maior se os pilotos não possuírem tempo para sentir, ou reconhecer, os seus sintomas. Uma revisão da legislação internacional indica uma grande tolerância a estabelecer limites de segurança neste tema, tendo em conta a imprevisibilidade de reacções do corpo humano de cada piloto para as mesmas condições de voo. O objectivo geral deste trabalho consiste na aquisição de dados durante distintas situações de voo, com diferentes pilotos, e o respectivo processamento dos dados obtidos durante as diferentes tarefas de voo. Para realizar os objectivos propostos os dados adquiridos contêm parâmetros como altitude, pressão absoluta e temperatura no interior da cabina, bem como o registo de oximetrias, periférica e cerebral, para estudar o fenómeno hipoxia. Também compreende electrocardiogramas (ECG) e electroencefalogramas (EEG) de modo a estabelecer uma correlação entre a influência da carga de trabalho mental e outros parâmetros fisiológicos durante as diferentes fases de voo. O objectivo específico desta investigação é a aquisição e processamento de dados recolhidos directamente da aeronave e do piloto, realizando testes de simulação de voo em diferentes cenários, contribuindo para tentar definir os limites fisiológicos de cada individuo com a finalidade de criar um sistema de alerta a bordo para evitar possíveis incidentes ou acidentes. Com este estudo pretende-se também sugerir uma restrição na legislação no licenciamento da aviação ligeira, dentro dos limites fisiológicos de cada individuo, contribuindo assim para um ambiente de voo mais seguro.
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Books on the topic "Pressurized cabins"

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ADMINISTRATION, FEDERAL AVIATION. Fatigue and fail-safe evaluation of flight structure and pressurized cabin for part 23 airplanes. U.S. Dept. of Transportation, Federal Aviation Administration, 1993.

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FEDERAL AVIATION ADMINISTRATION. Fatigue and fail-safe evaluation of flight structure and pressurized cabin for part 23 airplanes. U.S. Dept. of Transportation, Federal Aviation Administration, 1993.

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Low pCo₂ concentrator development: Final report. Life Systems, Inc., 1997.

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Book chapters on the topic "Pressurized cabins"

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Guzenberg, A. S. "Maintenance of Thermal Conditions in Pressurized Spacecraft Cabins." In Space Biology and Medicine – Volume II, Life Support and Habitability. American Institute of Aeronautics and Astronautics, Inc., 1994. http://dx.doi.org/10.2514/5.9781624104664.0209.0222.

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Yang, Biao, Dongsheng Yang, and Chuanfeng Wei. "Simulation Technology for Tissue Dose Ionizing Radiation in the Manned Spacecraft Pressurized Cabin." In Astrophysics and Space Science Proceedings. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-19309-0_57.

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Kimura, N., V. Kovachev, T. Nakamoto, et al. "Heat Transfer from Insulated Rutherford Type Cables Immersed in Pressurized He II." In Advances in Cryogenic Engineering. Springer US, 1998. http://dx.doi.org/10.1007/978-1-4757-9047-4_179.

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Collings, E. W., M. D. Sumption, R. M. Scanlan, S. W. Kim, M. Wake, and T. Shintomi. "Magnetic Studies of AC Loss in Pressurized Rutherford Cables with Coated Strands and Resistive Cores." In Advances in Cryogenic Engineering Materials. Springer US, 1996. http://dx.doi.org/10.1007/978-1-4757-9059-7_159.

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Bagshaw, Michael. "Aviation medicine." In Oxford Textbook of Medicine, edited by Jon G. Ayres. Oxford University Press, 2020. http://dx.doi.org/10.1093/med/9780198746690.003.0200.

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Travel by air is a safe means of transport, but puts people at various physiological risks and is a potential means of spreading infectious disease. Physiological risks associated with flying include hypoxia, as atmospheric pressure falls with altitude. The minimum cabin pressure in commercial passenger aircraft (565 mm Hg, 75.1 kPa) brings a healthy individual’s arterial P along the plateau of the oxyhaemoglobin dissociation curve until just at the top of the steep part, but does not cause desaturation. By contrast, people with respiratory disease and a low arterial oxygen pressure may desaturate, which can be overcome by administering 30% oxygen, this being equivalent to breathing air at ground level. There is no evidence that the pressurized aircraft cabin itself encourages transmission of disease, and recirculation of cabin air is not a risk factor for contracting symptoms of upper respiratory tract infection.
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Conference papers on the topic "Pressurized cabins"

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Perez, J. A. Romera, J. Persson, J. Witt, and L. Eicher. "Mode Transition Analyses of the Attached Pressurized Module Cabin Air Loop with EcosimPro." In International Conference On Environmental Systems. SAE International, 2000. http://dx.doi.org/10.4271/2000-01-2366.

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Zhang, C., S. Lin, and Y. Miao. "Experimental study on discharge coefficient of long flow channel in airplane pressurized cabin." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2020). Institution of Engineering and Technology, 2021. http://dx.doi.org/10.1049/icp.2021.0475.

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Marjoram, Robert H. "Pressurized Hydraulic Mounts for Improved Isolation of Vehicle Cabs." In 3rd International Pacific Conference on Automotive Engineering (1985). SAE International, 1985. http://dx.doi.org/10.4271/852349.

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Nuckols, M. L., and K. W. VanZandt. "Development of an Oxygen “Metabolizer” to Control Oxygen Levels in the Closed Cabin of Submarine Rescue Vehicles." In ASME 2002 21st International Conference on Offshore Mechanics and Arctic Engineering. ASMEDC, 2002. http://dx.doi.org/10.1115/omae2002-28039.

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The U.S. Navy is committed to maintaining the capability of rescuing survivors from a disabled submarine, including situations where the disabled submarine becomes internally pressurized due to flooding, leakage of compressed gas supplies, or through use of auxiliary breathing systems. Efficient submarine rescue requires that pressurized crewmembers be decompressed more rapidly than current decompression procedures allow when using air. The Navy Experimental Diving Unit in Panama City, FL has shown that crew decompression can be accelerated significantly by pre-breathing oxygen. Unfortunately, such oxygen pre-breathing can result in oxygen buildup in the cabin atmospheres of the submarine, and/or rescue chamber through leakage around the face seal of the oxygen masks. High levels of oxygen can create hazardous conditions within the cabin atmosphere due to fire potential and/or oxygen toxicity concerns. This paper addresses the concept development of an oxygen “metabolizer” using a hydrogen catalytic reactor to consume excess oxygen within the closed cabin atmosphere of a rescue vehicle. Such a catalytic reactor has also been shown to give an effective method of reducing the level of oxygen in diver breath heating and diver whole-body heating systems.
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Ebrahimi, Khosrow, Zhongquan C. Zheng, and Mohammad H. Hosni. "Computational Study of the Effects of Particle Size, Particle Injection Configuration, and Operating Pressure Gradient on Turbulent Dispersion of Spherical Micron-Sized Particles in a Generic Mockup Aircraft Cabin." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-88504.

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Computational study of dispersion of particles is one way to evaluate the spread of contaminants and viruses amongst occupants of an enclosure, such as an aircraft cabin. In this investigation, the turbulent dispersion of particles in a ventilated generic cabin is studied. The generic cabin resembles one-half of a Boeing 767-300 aircraft cabin. In the first phase, the turbulent dispersion of particles injected through stainless steel straight vertical tube is simulated. A Lagrangian approach is used to predict the particle concentration in specified monitoring location inside the cabin. The steady RANS solutions for the airflow velocity data are used to initialize the particle-tracking calculations through the Discrete Phase Model (DPM). To calculate the effects of turbulence on the dispersion behavior of particles, a Discrete Random Walk (DRW) model is employed. The particle concentration field under steady-state, zero-gauge-pressure conditions for 3 μm and 10 μm spherical liquid particles are calculated. Through the comparisons between the measured and the calculated particle concentration data for the two examined sizes of mono-disperse particles, the effect of particle size on distribution behavior of micron-sized particles is investigated and discussed. In the second phase, in order to reduce the effect of initial injection velocity for 10 μm particles on their distribution, the straight injection tube is replaced by a cone diffuser while maintaining the upstream primary flow conditions. Using the same RANS model and under the new particle injection configuration, the characteristics of turbulent airflow in the cabin are found to be very similar to those of turbulent airflow without particle injection. A grid independency study is performed for the airflow velocity data prior to validation of the particle distribution results. The steady-state DPM simulations are performed initially for the zero-gauge-pressure condition and then the effect of pressurizing the cabin on particle distribution is investigated by increasing the gauge-pressure up to 0.025 inches of water. Through a detailed study, carried out to obtain an optimum number for the number of tries in the DRW, it is realized that the optimum number of tries is 175 for both cases of pressurized and non-pressurized cabin.
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Veldman, R. L., J. Ari-Gur, and C. Clum. "Effects of Pre-Pressurization on Damage of Blast-Loaded Reinforced Plates." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-80861.

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The effects of pre-pressurization on blast-loaded reinforced rectangular aluminum plates were studied experimentally. In this study, small (0.508 × 0.609 × 0.0016 meter) clamped plates with rivet attached reinforcing members were used as a basic model of the fuselage skin of a commercial aircraft. Both non-pressurized and pre-pressurized plates (static pressure of 41.4 kPa (6.0 psi)) were considered to simulate the typical in-flight loads experienced by a commercial aircraft due to cabin pressurization. This work extends previous research on blast loading of pre-pressurized plates to incorporate the effects of reinforcing members [1]. An experimental configuration was designed using a vacuum vessel system to apply a pressure differential to the reinforced test plate. Bare spherical explosive charges of C4 were then detonated at fixed distances from the plate. The permanent plate deformations or the amount of tearing in the plates were measured for seventeen explosive tests that considered two different blast load intensities. Additionally, a high-speed camera was used to determine the mechanism and time scale of failure propagation in the reinforced panels. The high speed camera was used found to be an excellent tool to record the failure progression in the reinforced panels under blast loading. In general, commencing with the onset of panel deformation, the blast-loaded panels exhibited rivet failure in less than 0.5 milliseconds, initiation of plate tearing in less than 1.0 millisecond, and completion of plate tearing by about 10.0 milliseconds. A comparison of plate deformations and damage showed two distinct results. For the least intense blast load case, both the non-pressurized and pressurized panels deformed but did not tear. In this case, very little effect of pre-pressurization on final panel deformation was noted. For the more intense blast load case, a significant increase in panel damage was observed as static pre-pressurization increased from 0.0 kPa to 41.4 kPa.
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Baliga, Ravi, Tom Neal Watts, and Harish Kamath. "Application of an Integrated Head Assembly Concept at Pressurized Water Reactor Commercial Nuclear Plants." In 2014 22nd International Conference on Nuclear Engineering. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/icone22-30916.

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In a typical pressurized water reactor commercial nuclear plant, a number of components such as CRDMs, a lift rig to lift the Reactor Vessel Closure Head (RVCH), seismic restraints, missile shield, and a cooling system with large air ducts are installed on or directly over the RVCH. These components and systems are typically designed and installed individually to perform designated functions during plant operation. During refueling outages the removal of the RVCH from the pressure vessel and its subsequent re-installation on the pressure vessel for fuel loading requires individual dismantling and reassembly of these components resulting in an expensive and time-consuming process. Prior to detensioning the RVCH from the vessel, a lengthy series of steps or detailed procedures must be followed to safely remove the head area components and to store them in their designated spaces inside containment. The procedure generally includes: removal and storage of the concrete missile shield; removal and storage of CRDM cooling ducts; removal of seismic restraints; removal of head area cables; installation of the tripod assembly over the service structure; disconnecting the vent and level indicator lines; and installation of temporary lead blankets around the RVCH. Once the refueling is complete, these procedural steps are repeated in reverse order. Each procedure in the refueling process contributes significantly to the total cost associated with personnel time required to perform the refueling, power plant down time and consequent loss of electricity production, radiation exposure to personnel, and risks and costs associated with potential human errors. In addition, these components require a large amount of storage space inside containment raising the risk of having inadvertent contamination of work and storage areas. To reduce the outage duration and the associated radiation exposure to the workers, the authors have designed an Integrated Head Assembly (IHA) for Callaway nuclear plant based on Mr. Baliga’s patented design as disclosed in U.S. Patents. The IHA is an assembly of all head area components integrally attached to the RVCH so that all these components can be lifted with the RVCH in one assembly (see Figure 1). The IHA also provides a forced air convection system that improves the efficiency of the CRDM cooling. The IHA reduces a significant amount of critical path time and radiation dosage during refueling outages. Mr. Baliga’s invention has been implemented at several commercial nuclear plants in the USA (Turkey Point Units 3 and 4; Salem Units 1 and 2; DC Cook Units 1 and 2; Diablo Canyon Units 1 and 2; Davis Besse Unit 1; and Callaway Unit 1). This paper provides details of the IHA design implemented at Callaway nuclear plant in the USA.
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8

Bos, Jim, Robert Dell, Brad Nemeth, C. S. Wei, and William Foley. "Developing a Methodology for Comparing the Energy Efficiency of Hydraulic and Traction Elevators." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-38384.

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Traction elevators are hoisted by wire rope cables and hydraulic elevators are pushed by pressurized hydraulic fluid. Previous work published in IMEC2013-66663 presented methodologies for only traction elevator energy analysis. Many of the elevators in the USA are hydraulic. An objective and inclusive measurement methodology is needed for comparing energy efficiency of these two elevator systems for a valid cost benefit analysis. In this paper, the necessary requirements for a workable system for energy analysis are presented along with case study results. The previously presented elevator energy equations have evolved from simple kilogram-meters to watt-seconds for a more conventional energy analysis.
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9

Allen, Albert, and Adam Przekop. "Vibroacoustic Characterization of a New Hybrid Wing-Body Fuselage Concept." In ASME 2012 Noise Control and Acoustics Division Conference at InterNoise 2012. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/ncad2012-0321.

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A lighter, more robust airframe design is required to withstand the loading inherent to next generation non–cylindrical commercial airliners. The Pultruded Rod Stitched Efficient Unitized Structure concept, a highly integrated composite design involving a stitched and co-cured substructure, has been developed to meet such requirements. While this structure has been shown to meet the demanding out-of-plane loading requirements of the flat-sided pressurized cabin design, there are concerns that the stiff co-cured details will result in relatively high acoustic radiation efficiencies at frequencies well below the thin skin acoustic coincidence frequency. To address this concern and establish a set of baseline vibroacoustic characteristics, a representative test panel was fabricated and a suite of tests were conducted that involved measurements of panel vibration and radiated sound power during point force and diffuse acoustic field excitations. Experimental results are shown and compared with Finite Element and Statistical Energy Analysis model predictions through the use of modal and energy correlation techniques among others. The behavior of the structure subject to turbulent boundary layer excitation is also numerically examined.
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10

Wang, Jinhua, Bing Wang, Bin Wu, and Yue Li. "Design of the Spent Fuel Storage Well of HTR-PM." In 2016 24th International Conference on Nuclear Engineering. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/icone24-60051.

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There are more than 400 reactors in operation to generate electricity in the world, most of them are pressurized water reactors and boiling water reactors, which generate great amount of spent fuel every year. The residual heat power of the spent fuel just discharged from the reactor core is high, it is required to store the spent fuel in the spent fuel storage pool at the first 5 years after discharged from the reactor, and then the spent fuel could be moved to the interim storage facility for long term storage, or be moved to the factory for final treatment. In the accident of the Fukushima in 2011, the spent fuel pool ruptured, which led to the loss of coolant accident, it was very danger to the spent fuel assemblies stored in the pool. On the other hand, the spent fuel stored in the dry storage facility was safe in the whole process of earthquake and tsunami, which proved inherent safety of the spent fuel dry storage facility. In china, the High Temperature gas cooled Reactor (HTR) is developing for a long time in support of the government. At the first stage, HTR-10 with 10MW thermal power was designed and constructed in the Institute of Nuclear Energy Technology (INET) of Tsinghua University, and then the High Temperature Reactor-Pebble bed Modules (HTR-PM) is designed to meet the commercial application, which is in constructing process in Shandong Province. HTR has some features of the generation four nuclear power plant, including inherent safety, avoiding nuclear proliferation, could generate high temperature industrial heat, and so on. Spherical fuel elements would be used as fuel in HTR-PM, there are many coating fuel particles separated in the fuel element. As the fuel is different for the HTR and the PWR, the fuel element would be discharged into the appropriate spent fuel canister, and the canister would be stored in the appropriate interim storage facility. As the residual power density is very low for the spent fuel of HTR, the spent fuel canister could be cooled with air ventilation without water cooling process. The advantage of air cooling mode is that it is no need to consider the residual heat removal depravation due to loss of coolant accident, so as to increase the inherent safety of the spent fuel storage system. This paper introduced the design, arrangement and safety characteristics of the spent fuel storage well of HTR-PM. The spent fuel storage wells have enough capacity to hold the total spent fuel canisters for the HTR-PM. The spent fuel storage facility includes several storage wells, cold intake cabin, hot air discharge cabin, heat shield cylinders, well lids and so on. The cold intake cabin links the inlets of all the wells, which would be used to import cold air to every well. The hot air discharge cabin links the outlets of all the wells, which would be used to gather heated air discharged from every well, the heated air would be discharged to the atmosphere through the ventilating pipe at the top of the hot air cabin. The design of the spent fuel storage well and the ventilating pipe could discharge the residual heat of the spent fuel canisters in the storage wells, which could ensure the operating safety of the spent fuel storage system.
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