Relevant bibliographies by topics / Air India Flight 182

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Academic literature on the topic 'Air India Flight 182'

Author: Grafiati
Published: 4 June 2021
Last updated: 18 February 2022

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Journal articles on the topic "Air India Flight 182"

1

Chakraborty, Chandrima. "Feature Section: Air India Flight 182: A Canadian Tragedy?" TOPIA: Canadian Journal of Cultural Studies 27 (June 2012): 173–76. http://dx.doi.org/10.3138/topia.27.173.

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Soni, Raji Singh, and Asha Varadharajan. "Between Securocratic Historiography and the Diasporic Imaginary: Framing the Transnational Violence of Air India Flight 182." TOPIA: Canadian Journal of Cultural Studies 27 (June 2012): 177–95. http://dx.doi.org/10.3138/topia.27.177.

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Busse, Cassel. "Politics of (Im)moderation: The Production of South Asian Identities in the Canadian Apology for Air India Flight 182." TOPIA: Canadian Journal of Cultural Studies 27 (June 2012): 233–51. http://dx.doi.org/10.3138/topia.27.233.

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Alonso-Breto, Isabel. "Role of the Postcolonial Translator." TranscUlturAl: A Journal of Translation and Cultural Studies 13, no. 1 (August 19, 2021): 49–54. http://dx.doi.org/10.21992/tc29533.

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This essay consists of a meditation upon the emotions, affects and ethical compromises which surround the translation of texts as complex and delicate as Bharati Mukherjee’s short story “The Management of Grief”. This well-known piece of fiction offers a very painful account of how the families of the victims of the Air India Flight 182 attack in 1985 managed to survive the enormous grief of losing their loved ones in such abrupt, violent and unjust manner. The essay author, who decided to translate this story into Spanish so that it could be enjoyed by a wider readership, shares her thoughts regarding the demands of such painful yet necessary task. The whole area of Postcolonial Studies, where she develops her scholarly career, is unfortunately rife with such testing moments, and she wonders about the convenience or even the pertinence of such scholarly/textual interventions.
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Rolf, Christian, Bärbel Vogel, Peter Hoor, Armin Afchine, Gebhard Günther, Martina Krämer, Rolf Müller, Stefan Müller, Nicole Spelten, and Martin Riese. "Water vapor increase in the lower stratosphere of the Northern Hemisphere due to the Asian monsoon anticyclone observed during the TACTS/ESMVal campaigns." Atmospheric Chemistry and Physics 18, no. 4 (March 1, 2018): 2973–83. http://dx.doi.org/10.5194/acp-18-2973-2018.

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Abstract. The impact of air masses originating in Asia and influenced by the Asian monsoon anticyclone on the Northern Hemisphere stratosphere is investigated based on in situ measurements. A statistically significant increase in water vapor (H2O) of about 0.5 ppmv (11 %) and methane (CH4) of up to 20 ppbv (1.2 %) in the extratropical stratosphere above a potential temperature of 380 K was detected between August and September 2012 during the HALO aircraft missions Transport and Composition in the UT/LMS (TACTS) and Earth System Model Validation (ESMVal). We investigate the origin of the increased water vapor and methane using the three-dimensional Chemical Lagrangian Model of the Stratosphere (CLaMS). We assign the source of the moist air masses in the Asian region (northern and southern India, eastern China, southeast Asia, and the tropical Pacific) based on tracers of air mass origin used in CLaMS. The water vapor increase is correlated with an increase of the simulated Asian monsoon air mass contribution from about 10 % in August to about 20 % in September, which corresponds to a doubling of the influence from the Asian monsoon region. Additionally, back trajectories starting at the aircraft flight paths are used to differentiate transport from the Asian monsoon anticyclone and other source regions by calculating the Lagrangian cold point (LCP). The geographic location of the LCPs, which indicates the region where the set point of water vapor mixing ratio along these trajectories occurs, can be predominantly attributed to the Asian monsoon region.
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Kundu, Vaibhav. "Consumer Behavior while Choosing Air Travel in India." International Journal for Research in Applied Science and Engineering Technology 9, no. 8 (August 31, 2021): 2422–28. http://dx.doi.org/10.22214/ijraset.2021.37776.

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Abstract: The domestic airline industry of India has been witnessing an enormous transformation over the period. Different class of people can avail this service due to modern specifications, affordability rates, ease of reachability, frequency of flights, quality of service, etc. The recent studies depict that the number of customers opting for domestic air travel has a steep increase when compared to the past numbers. This has been possible due to increase in connectivity of different areas and reducing the flight fares to increase the accessibility and reachability for the customers. Reducing fares and increasing connectivity does not only help the customers but it has also helped a lot to contribute to the business of airlines to a very large extent. This research mainly focuses on the consumer behavior while choosing different airlines. There are multiple factors which affect while choosing the appropriate flight company for travelling. There are different class of customers and accordingly the airline companies need to match their preferences. Some consumers want affordable rates whereas some customers want better quality o service. This research will basically give an idea which factors pertain the most while choosing the perfect flight for domestic travel within India. Keywords: Quality Service, IndiGo, SpiceJet, Go Air, Air Asia, Vistara, Air India, Statista, Holidify
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Lee, Seung Yong, Paul Bates, Patrick Murray, and Wayne Martin. "Training Flight Accidents." Aviation Psychology and Applied Human Factors 7, no. 2 (September 2017): 107–13. http://dx.doi.org/10.1027/2192-0923/a000121.

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Abstract. Civil aviation is broadly categorized into two sectors: air transportation and general aviation. While the former sector is considered to be ultrasafe the latter requires a stronger focus on safety improvement. There has been considerable research examining the causes of general aviation accidents with a view to improving safety. However, there has been very limited research specifically focused on accidents involving training flights and associated causal factors. A total of 293 training flight accident reports, comprising 111 fatal and 182 nonfatal accidents were reviewed and analyzed to identify causes of training-flight accidents. The study found that based on the odds ratio, if a fatal accident involving training flights occurred it was 4.05 times more likely to be a dual training flight. Other findings included that most accidents occurred during the landing phase and the majority of accidents related to skill deficiency (e.g., an improper/inadequate flare). This was a major causal factor in nonfatal accidents in both dual and solo training flights. However, on dual training flights there were more fatal accidents involving decision deficiencies and mechanical malfunctions (e.g., loss of engine power). A previous study suggested that lack of supervision of student pilots by flight instructors was found to be a main causal factor and thus flight instructor training and recurrency requirements need to be reviewed.
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Wang, Fei. "A New Algorithm of Flight Rerouting Path Planning in Severe Weather." Applied Mechanics and Materials 182-183 (June 2012): 1895–99. http://dx.doi.org/10.4028/www.scientific.net/amm.182-183.1895.

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In order to solve the rerouting problem of air traffic management in severe weather areas, a rerouting path planning problem was researched. First, the convex polygon was used to design danger zone. Then, rerouting path planning model was established. After that, a new algorithm used to determine the initial reroute points was proposed. Finally, two examples of the rerouting problem caused by thunderstorms occurring in Southwest China were studied. Compared to the current existing method in real operation, by using this algorithm, the number of reroute points was effectively reduced, and the danger zone was avoided. Additionally, Compared to the geometric algorithm, by using this algorithm, the rerouting path length was reduced by 2.9% and 5% respectively. The results indicate that the algorithm proposed in this paper is effective and practical.
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Masrifah, Siti. "Evaluasi Kebutuhan Tenaga ATC di Bandara Sultan Hasanuddin Makassar." WARTA ARDHIA 36, no. 2 (June 30, 2010): 108–23. http://dx.doi.org/10.25104/wa.v36i2.77.108-123.

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By looking at the growth of air transport has increased quite significantly, certainly not independent human resources needs to guide them in Air Traffic Control personnel. In this case one of the problems encountered in field of aviation is the imbalance between supply and demand on Ihe one hard, the growth of air transport have increased and on one side of the energv needs of ATC is not in accordance with the operation of the flight. In connection with this case was the result of the ability of the Aviation safety Techical Academy, in terms of manpower needs in Particular ATC Sultan Hasanuddin Airport in Makassar, which now number 144 ATC personel, whereas the ideal number to 145 people personnel. However, the results of estimates / projections for 2015 amounted to 182 personnel required by the ATC.
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Flury, T., S. C. Müller, K. Hocke, and N. Kämpfer. "Water vapor transport in the lower mesosphere of the subtropics: a trajectory analysis." Atmospheric Chemistry and Physics 8, no. 23 (December 10, 2008): 7273–80. http://dx.doi.org/10.5194/acp-8-7273-2008.

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Abstract. The Institute of Applied Physics operates an airborne microwave radiometer AMSOS that measures the rotational transition line of water vapor at 183.3 GHz. Water vapor profiles are retrieved for the altitude range from 15 to 75 km along the flight track. We report on a water vapor enhancement in the lower mesosphere above India and the Arabian Sea. The measurements took place on our flight from Switzerland to Australia and back in November 2005 conducted during EC- project SCOUT-O3. We find an enhancement of up to 25% in the lower mesospheric H2O volume mixing ratio measured on the return flight one week after the outward flight. The origin of the air is traced back by means of a trajectory model in the lower mesosphere and wind fields from ECMWF. During the outward flight the air came from the Atlantic Ocean around 25 N and 40 W. On the return flight the air came from northern India and Nepal around 25 N and 90 E. Mesospheric H2O measurements from Aura/MLS confirm the transport processes of H2O derived by trajectory analysis of the AMSOS data. Thus the large variability of H2O VMR during our flight is explained by a change of the winds in the lower mesosphere. This study shows that trajectory analysis can be applied in the mesosphere and is a powerful tool to understand the large variability in mesospheric H2O.
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Books on the topic "Air India Flight 182"

1

Don, Hauka, ed. The death of Air India Flight 182. London: Star, 1986.

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Air India Flight 182: A Canadian tragedy. Ottawa, Canada]: [Commission of Inquiry into the Investigation of the Bombing of Air India Flight 182], 2010.

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Saklikar, Renée Sarojini. Children of Air India: Un/authorized exhibits and interjections. Gibsons, BC: Nightwood Editions, 2013.

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Commission of Inquiry into the Investigation of the Bombing of Air India Flight 182 research studies. [Ottawa]: Commission of Inquiry into the Investigation of the Bombing of Air India Flight 182, 2010.

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J, Hauka Donald, ed. Margin of terror: A reporter's 20-year odyssey covering the tragedies of the Air India bombing. Mumbai: Jaico Pub. House in arangement with Key Porter Books, 2007.

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Bharati, Mukherjee, ed. The sorrow and the terror: The haunting legacy of the Air India tragedy. Markham, Ont., Canada: Viking, 1987.

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Siṅgha, Guraprīta. Nafarata saṅga piāra dī jaṅga: Kanishakā dhamāke de pīṛata pariwārāṃ dī awāza : wārataka. Ludhiāṇā, India: Cetanā prakāshana, 2013.

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Rae, Bob. Lessons to be learned: The report of the Honourable Bob Rae, independent advisor to the Minister of Public Safety and Emergency Preparedness, on outdtanding questions with respect to the bombing of Air India Flight 182. Ottawa: Air India Review Secretariat, 2005.

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Viswanathan, Padma. The ever after of Ashwin Rao. Toronto: Random House Canada, 2014.

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Newport, Curt. Lost spacecraft: The search for Liberty Bell 7. Burlington, Ont: Apogee Books, 2002.

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Book chapters on the topic "Air India Flight 182"

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Cohen, G. A. "Two Weeks in India." In Finding Oneself in the Other, edited by Michael Otsuka. Princeton University Press, 2012. http://dx.doi.org/10.23943/princeton/9780691148809.003.0004.

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This chapter chronicles Cohen's two-week trip to India (from January 1 to 15, 1993), and touches upon some themes and experiences which had had a profound impact on him during his stay there. It first describes his experiences on board an Air India flight and his meditations on and encounters with poverty upon landing in Delhi and throughout the rest of his stay in the country. The chapter contains the author's personal accounts of his many encounters with people—both native and otherwise—in India, and frequently returns to his meetings with the poor and how he (and the Indian poor) deal with poverty in the nation. Despite his more unpleasant experiences, Cohen writes, that “India gripped me, and I don't want it to let go. As long as I write, it stays with me, I don't have to say goodbye.”
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Godwin, T. "An Empirical Analysis of Delhi - Mumbai Sector Flight Fares." In Research Anthology on Reliability and Safety in Aviation Systems, Spacecraft, and Air Transport, 1477–95. IGI Global, 2021. http://dx.doi.org/10.4018/978-1-7998-5357-2.ch062.

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Revenue management is the art and science of making the right product or service available to the right customer at the right time through the right channel at right price. Dynamic pricing plays a crucial role in the implementation of revenue management in passenger airline reservation system. The liberalization of domestic aviation sector in countries such as India has seen many new market entrants resulting in higher competition while setting the flight fares. The variation in flight fares of Delhi – Mumbai passenger airline sector is studied for a departure date based on the number of days in advance the booking is made. Descriptive and inferential statistical analyses of the fares reveal the impact of airlines, booking channels and departure time windows on the pricing decisions of flight fares. The analysis framework of this study could be used as a basis for a continuous tracking study of flight fares by airline revenue managers to help them arrive at the right fare for each fare class of a flight.
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Conference papers on the topic "Air India Flight 182"

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Gandla, Pavan, and Naresh Nidamanuri. "Accurate Prediction of Buffer Air Temperatures Using Lumped Heat Transfer Method." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2519.

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Abstract Buffer air system plays a vital role in gas turbine engines as it pressurizes bearing compartments, thermal conditioning of life limiting parts, purging the hot gas ingestion and antiicing. Buffer air is normally tapped from compressor section and routed to several locations of the engine through tubes, struts and ducts. Air supply is controlled though a buffer valve which sources air from different sources based on the flight condition. Accurate prediction of steady state buffer air temperature is critical in achieving gas turbine performance, durability and operability. It allows design community to determine optimum amount of buffer air which directly impacts gas turbine efficiency. As buffer air passes through different section of the engine by the time it reaches its intended destination, it losses or gains heat which eventually alter its temperature. Buffer air is currently modelled through a network of chambers and restrictors which is solved through an iterative solver for flow and energy convergence. Heat transfer is neglected in this solver and captures only enthalpy balance and pressure losses. An effort has been made to capture buffer air convective heat transfer as it passes through many channels and ducts on its routing. Lumped heat transfer method is employed and estimated the delta temperature b/w inlet and outlet of the corresponding passage. Outside and inside heat transfer coefficients are estimated using empirical correlations. Under steady state conditions, Final temperature of the buffer air would be the surrounding air temperature at that location and initial temperature of the air is its entry temperature. This delta temperate is incorporated in the buffer air network which then predicts corrected buffer air temperature for any flight conditions. With this methodology predicted buffer air Temperature is matched very close to thermo couple test data for various engine power conditions. Buffer air network model fidelity is greatly improved and gives greater confidence on air temperature for any flight conditions. Design studies are carried out and made a recommendation to incorporate thermal barrier coating on passages so that buffer temperature is retained which improves its thermal conditioning capabilities.
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Garavello, A., M. Russo, Claudio Comis da Ronco, R. Ponza, and E. Benini. "Aerodynamic Shape Optimization of Air-Intakes of a Helicopter Turboshaft." In ASME 2012 Gas Turbine India Conference. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gtindia2012-9506.

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The research project HEAVYcOPTer, a sub task of the European R&D program Clean-Sky GRC2 [1], is devoted to the efficient design and the shape optimization of the Agusta Westland AW101 helicopter turboshaft engine intake and exhaust system, to be carried out by means of advanced multi-objective optimization algorithms coupled with CFD Navier-Stokes solvers. The present paper describes the outcomes of HEAVYcOPTer in relation to the air intakes shape optimisation activities. This paper describes the technical details of such program. The optimisation method chosen for the redesign of the engine installation involves the application of the state of the art genetic algorithm GDEA, developed at the University of Padova and successfully applied in several fluid-dynamics applications, especially in the field of turbomachinery. For the present application, the set of geometrical designs constituting the genetic algorithm population are generated by means of morphing the original CFD model surface mesh: shapes are applied to baseline surface nodes with a displacement intensity driven by the GA chosen scaling factors. Then, CFD models of new designs are automatically generated and analyzed by the flow solver, returning to the GA the evaluation of the selected objective functions required in order to evolve the population in the next step of the evolutionary process. AW101 intakes have been optimised following a multi-objective/multi-point approach, minimizing inlet total pressure loss in both hovering and forward flight conditions simultaneously; optimised solutions were also constrained so as to not exceed the total pressure distortion level at the engine aerodynamic interface plane, so as to ensure inlet/engine compatibility with respect to the compressor surge limit. This approach ensured the improvement of the engine/airframe integration efficiency for the overall rotorcraft flight envelop, reducing fuel burn and increasing the helicopter propulsive efficiency.
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Chen, Jingjing, Yadong Wu, Zhonglin Wang, and Anjenq Wang. "Nacelle: Air Intake Aerodynamic Design and Inlet Compatibility." In ASME 2014 Gas Turbine India Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gtindia2014-8182.

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One of the most challenging operating conditions to be certified for FAR33 & FAR25 requirements is ground crosswind condition. When “Engine” is operated using the designed inlet and nacelle, within the flight envelope, could accommodate inlet separation/distortion resulted from crosswind and high angle-of-attack operating conditions. Inlet flow separation and distortion could trigger fan or core stall, as well as induce high fan and/or engine vibrations. The air induction system or inlet of the engine is designed to provide velocity and pressure distributions with minimum distortion and maximum pressure recovery to the propulsion system. Engine-inlet-airframe compatibility is one of the major tasks required to be evaluated in detail during the engine developing phase. This research is a parametric study of using CFD to evaluate operational characteristics of the air induction system. Comparisons of various inlet designs are made and characterized into three categories, i.e., i) Inlet flow recovery, ii) Inlet flow distortion, iii) Inlet Mach distribution. The objective is to assess the impact of air induction design of turbofan upon inlet compatibility. The current research work includes four parts, i.e., i) A geometry modeling process of nacelle, inlet, wing and fuselage, ii) A meshes generator ICEM, iii) The ANSYS CFX CFD software which could achieves numerical simulation and post-processing, iv) The Matlab platform with the function of coupling all considerations listed above for inlet compatibility optimization, based on genetic algorithm and Kriging agent model. The research introduces the Kriging model and weighting coefficient to optimize total pressure loss coefficient and static pressure recovery coefficient, with the external nacelle flow ignored. Bezier equation was used to fit the optimized curves obtained by changing two control points at the inter surface of nacelle. The wing-mounted model coupled with the nacelles, fuselage and wings was then built to make the assessment of inlet compatibility of air intake system relative to the isolate model. Comparison of aerodynamic performance was then made between the original and optimal nacelle, to show correlation between inlet compatibility and air intake profile.
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Kandaswamy, Nomesh P., Kali Charan Nayak, Guy D. Snowsill, John Irving, and Ben Littley. "CFD Study for the Particle Transport and Deposition in Secondary Air Systems." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2423.

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Abstract The recent expansion of civil aviation industry into the new market demands modern aero-engines to operate in hot, harsh and polluted environments. Moreover there is a significant increase in the flight paths across the sea leading to large amount of micro salt particle ingestion into the engines. These contaminants can cause severe damage to the turbine parts through hot corrosion fatigue. The mechanism of the very small particle transport in the secondary air system and their deposition on turbine parts is less reported and not well understood. This study explores the physics of the particle transport (< 0.5–10 micron) and their deposition characteristics in the secondary air paths. Specifically, a three-dimensional computational fluid dynamics (CFD) model is developed for an engine representative turbine cavity with blade shank utilizing commercial finite volume-based software incorporating the SST k-ω turbulence model. The particle transport is captured using discrete random walk model and their wall interaction (bounce and stick) is simulated using the critical velocity model. A comprehensive parametric study is conducted using 2 and 6 micron CaSO4 particles covering a wide range of operating and design variables. From the parametric study it has been observed that rotor speed, swirl and the radial location of the feed holes strongly influence the flow structure in the shank cavity and particle deposition.
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Matúš, Peter, and Matúš Materna. "Approaches of chosen air navigation services providers to UAV integration into air traffic control systems." In Práce a štúdie. University of Zilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.2.26.

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In this article are approaches of Air Navigation Services (ANS) providers in chosen countries to UAV integration into Air Traffic Control Systems identified and described. Firstly we made a synpaper of theoretical information about ANS and UAV. Product of ANS providers has 11 parts. For UAV traffic control and management are important ATC, CNS, AIS, MET, ATFCM and ASM services. The volume of ANS provided depends on UAV operation development in the country, and on the level of integration of UAV into ATC systems. The biggest problem of UAV operation is the risk of collision with piloted aircraft, and potential threat of people and property on the ground. The biggest risk is during UAV operation close to airports, because there are many aircrafts flying in low altitudes (after take-off and on approach to landing). The consequences of collision in this altitudes in the most serious. Because of this, 4 ways to detect and 2 ways to mitigate an unauthorized UAV close to airport are currently in use. Various combinations of UAV detection and mitigation ways create complex airport UAV protection systems. Secondly, we chose 7 countries (Poland, Hungary, Germany, Great Britain, USA, India, and United Arab Emirates), and analysed their approaches to UAV integration. In all of the analysed countries can remote pilots use a mobile application, which allows them to create a flight plan, and receive all the information, necessary for the flight. Differences between these countries are for example if the permission in required for every UAV flight (in Hungary and India yes), if the ANS provider has an opportunity to watch UAV during flight (in Poland, India, and partly in Germany), if the UAV operation without direct visual contact between remote pilot and UAV is allowed (in Poland and Germany), and if are UAV operations included into airspace capacity management systems (in Poland, Hungary, Germany, and Great Britain). UAV integration process in next years will relate to development of communication systems between UAVs, between UAV and ATC, and between UAV and piloted aircraft. The process will also relate to development of technologies to avoid mid-air collisions.
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Ferguson, J. G. "Brushes as High Performance Gas Turbine Seals." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-182.

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Brush seals are the first simple and practical alternative, to the finned labyrinth, for gas turbine air system seals. Their use has been made possible by a combination of innovative design features, combined with advanced materials and manufacturing techniques. Due to the very high rubbing speeds and temperatures, existing in gas turbine air system seal positions, finned labyrinths have been used almost exclusively since the invention of the gas turbine. Development over the years has reduced their leakage flow to the ultimate, but leakage is very much dependent on clearance. A brush seal, replacing the best possible finned labyrinth seal, needing a clearance of 0.7mm, can reduce the flow to approximately 10% of that of the finned seal. The main advantages of brush seals, therefore, are their dramatic improvement in sealing performance. This is combined, however, with their ability to maintain this performance even during and after transient differential movements. These advantages have been developed and demonstrated after many hours rig and engine running. Back to back engine tests, with brush seals, replacing finned labyrinths in key air system seals, have demonstrated a significant improvement in thrust for a given stator outlet temperature (SOT). Flight trials are in progress, on an engine fitted with brush seals, as a further step to their in service use.
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Kattegollahalli Shivakumar, Darshan, Ganesan Sabbani, Gursharanjit Singh, and Purushothama Harthi Revanasiddappa. "Prediction of Gas Turbine Afterburner Performance Using CFD for Different Operating Conditions and Reheat Strength." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4631.

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A gas turbine afterburner is required to operate under severe conditions of pressure and temperature to meet the design requirements of next generation gas turbine engines. This fact, coupled with the current trends towards higher turbine discharge temperature and the requirement for satisfactory operation over extended fuel/air ratios and flight maps call for greater understanding of the internal aerodynamics for improving thrust developed by the afterburner. The present work focuses on prediction of performance of a practical afterburner for different altitude conditions and reheat strengths (i.e., fuel-air ratios) using Computational Fluid Dynamics (CFD) simulations. Combustion efficiency and thrust boost at these conditions have been predicted. The reacting flow field has been analyzed and changes suggested for improving thrust at low performance points.
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Manoharan, Sajath Kumar, Kasram Santhosh, Mahesh P. Padwale, and G. P. Ravishankar. "Aero Engine Performance Evaluation During Missile Firing Test." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4544.

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Evaluation of engine performance during armament firing in fighter aircraft is a vital qualification aspect for airframe engine integration. Ingestion of missile’s efflux into air intake results in rapid increase of engine inlet temperatures (temperature ramps) which cause flow disturbance to the compressor. Temperature distortion caused due to armament firing and its effect on compressor stability during flight testing is evaluated. Accordingly mitigation actions are recommended for stall/surge free operations. Distortion descriptors are assessed using simulation model (engine performance program) and results compared with engine distortion limits.
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Kane, Aniruddha Ajay, and Ravi K. Peetala. "Parametric Analysis and Performance Evaluation of 2D Scramjet Inlet." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2324.

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Abstract The air breathing propulsion system used for hypersonic vehicle cruising is a scramjet. Inlet design is one of the important step in overall design of scramjet. The initial steps in the inlet design process consist of identification of shock angles, shock hitting points and there after evaluation of performance parameters using inviscid flow consideration at a given Mach number called design Mach number. During the flight, the vehicle operates on the off-design conditions. The current study focusses on the effect of these off-design conditions such as variation of freestream Mach number, angle of attack, total temperature on the flow field and performance parameters using inviscid flow assumption. The performance parameters considered in the present study are total pressure recovery, static pressure ratio, static temperature ratio, kinetic energy efficiency, adiabatic compression efficiency, non-dimensional entropy increase.
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Bhatt, Ashish, B. Balaji, Abdullah Tyeb, Amit Gupta, Mahesh P. Padwale, and G. P. Ravishankar. "Suction Mode Start Characteristics of a Turbofan Engine for a Windmill Relight." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4872.

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Wind-milling occurs when air flowing through the flamed out engine results in increasing spool rotation. Aircraft forward speed and dive angles play an important role in achieving sustainable spool rotation for relight. Aircraft fuel pump connected to power take-off shaft of Engine shuts when engine rpm falls below design speed and cannot deliver pressurized fuel to Engine during wind-milling. Under this condition, engine has to suck the fuel from aircraft using its own fuel pump. The atmospheric pressure available on the aircraft fuel tank assists the engine to operate in suction mode. The datum height between engine inlet and fuel tank outlet changes with the dive angle of the aircraft. A test set up was established in the engine test bed to vary the datum between aircraft fuel tank and Engine inlet. The datum was varied to simulate various dive angles of the aircraft. The negative gravity head (Engine fuel inlet above fuel tank outlet) between engine and fuel tank was varied in steps. Total four test cases were carried out in an engine test bed located at an altitude of 920 m above sea level. The engine was successfully started in suction mode without external assistance of fuel pump. This paper presents the test setup, comparison of engine start cycle under various dive angles of the aircraft to evaluate optimum flight conditions to attempt windmill relight. These tests show that as the negative gravity head is increased, the time taken to start the engine increases. The slope of N2 build up becomes shallower with increase in gravity head.
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