Relevant bibliographies by topics / Aircraft starter

Academic literature on the topic 'Aircraft starter'

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Published: 14 March 2023

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Journal articles on the topic "Aircraft starter"

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Pakhomin, Sergey, and Leonid Pakhomin. "Permanent Magnet Starter Generator for Aircraft." Известия высших учебных заведений. Электромеханика 62, no. 4 (2019): 44–47. http://dx.doi.org/10.17213/0136-3360-2019-4-44-47.

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Su, Wu‐Chung, Min‐Shyan Hwang, and Chia‐Fu Lin. "Aircraft starter/generator control unit design." Journal of the Chinese Institute of Engineers 24, no. 1 (January 2001): 1–8. http://dx.doi.org/10.1080/02533839.2001.9670600.

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Wawrzyński, Wojciech, Mariusz Zieja, Justyna Tomaszewska, and Mariusz Michalski. "Reliability Assessment of Aircraft Commutators." Energies 14, no. 21 (November 6, 2021): 7404. http://dx.doi.org/10.3390/en14217404.

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The article describes the method of predicting the reliability and durability of an aircraft commutator, which is a primary source of electric energy in helicopters. Tests were conducted for 10 starter-generators. From this research it follows that the technical condition of brushes and bearings has a significant impact on the reliability of starter-generators. The reliability of starter-generators was determined based on the method consisting of two stages that was adopted: the first stage involved determining the density function of changes in diagnostic parameter depending on the operating time, but the second stage included the assessment of the reliability of bearings of the starter-generator taking into account the real flight profile. The first stage of the adopted method consisted of defining the dynamic model of changing the length of the starter-generator’s brush, which became the probabilistic model. Subsequently, based on differential equations, Fokker–Planck partial differential equation was derived, which describes the process of increasing the brush wear in a probabilistic way. This method enables the prediction of the residual durability of the helicopter’s starter-generator due to the change in a diagnostic parameter which is the wear of brushes during starter-generator operation. The second stage of this method allows determining the durability of starter-generator’s bearings building upon the average helicopter’s flight profile. Owing to the difficulty in measuring the wear of bearings, the relation between the durability of bearings and the temperature of surroundings can be applied by replacing the flight altitude with temperature. The reliability of the helicopter’s starter-generator was determined based on the serial-type reliability structure.
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Setlak, Lucjan, and Rafał Kowalik. "The Study of Permanent Magnets Synchronous Machine (PMSM) of the Autonomous Electric Power Supply System (ASE), compatible with the Concept of a More Electric Aircraft (MEA)." ITM Web of Conferences 16 (2018): 03001. http://dx.doi.org/10.1051/itmconf/20181603001.

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Based on the analysis and mathematical models of synchronous electric machines (motor/generator), basing on permanent magnets, presented in this paper, the main importance of alternator AC power sources in the form of starter/generator (for conventional aircraft) and in the form of integrated unit starter (motor)/AC synchronous generator S/G AC (with respect to advanced aircraft concept in terms of more electric aircraft) was highlighted. Additionally, through the analysis and selected simulations of the on-board autonomous power supply system of the modern aircrafts, sources of electrical energy (synchronous motor/generator, integrated unit starter/AC generator) were located in board autonomic power system ASE (EPS, PES). Main components of this system are the electro-energetic power system EPS and the energo-electronic power system PES. In addition, the analysis and exemplary simulations of main electricity sources based on mathematical models have contributed to highlighting the main practical applications in accordance with the concept of MEA.
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Slamet Firdaus, Fazrin Andhika, and MAMIN MAMIN. "Analisis Troublehooting Starter Motor terus berputar saat putaran APU Engine mencapai 50% rpm." SEMINAR TEKNOLOGI MAJALENGKA (STIMA) 6 (December 8, 2022): 211–15. http://dx.doi.org/10.31949/stima.v6i0.715.

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Airplanes are a universal means of transportation, with planes, we don't have to worry about the time when we want to go anywhere because with airplane transportation we can go anywhere in an efficient and short time. In this day and age, aircraft technology is very advanced. The aircraft component itself consists of several components, namely the Auxiliary Power Unit (APU). The APU functions to supply pneumatic and electrical energy for aircraft, where the electrical functions for electricity on the aircraft while pneumatic functions for engine starting, hydraulic pressure, air conditioning and others. This research method is descriptive research consisting of drafting, data collection, data processing and report preparation. In this step there are more stages which will later serve to get a conclusion in the study. Basically the trouble that often occurs when the APU starting process is on the starter motor component, Troubleshoot that often occurs in the starter motor component, namely the starter motor will continue to rotate when it reaches 50% rpm rotation caused by a starter motor problem, starter relay problem and electronical speed switch problem. Therefore, we must immediately repair or replace these components according to the aircraft maintenance manual so that the aircraft remains airworthy.
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Liu, Jian Ying, and Min Ma. "Research on the Control Principle of Aircraft AC Starter/Generator." Advanced Materials Research 816-817 (September 2013): 398–401. http://dx.doi.org/10.4028/www.scientific.net/amr.816-817.398.

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AC starter/generator is a new starting/generation dual-function technology applied to the aircraft. The previous pneumatic starter, brushed DC starter/generator or DC starter are replaced by the synchronous AC motor, thereby reducing the weight of airborne equipment effectively. Based on AC starter/generator driven by auxiliary power unit (APU) used on a certain type of aircraft, this paper mainly carries out the research on the composition of AC starter/generator system, starting process and its control principle, as well as demonstrates how the starting torque is controlled. Theoretical study shows that the torque can be precisely controlled through the control of the torque component of stator current when the rotor field oriented vector control strategy is adopted.
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Setlak, Lucjan, and Rafał Kowalik. "Model and Simulation of Permanent Magnets Synchronous Machine (PMSM) of the Electric Power Supply System (EPS), in Accordance with the Concept of a More Electric Aircraft (MEA)." ITM Web of Conferences 16 (2018): 03004. http://dx.doi.org/10.1051/itmconf/20181603004.

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Based on the mathematical model of synchronous electric machine, basing on permanent magnets, presented in this paper, the key importance of alternator AC power sources in the form of generator (for conventional aircraft) and in the form of integrated unit starter/AC synchronous generator S/G AC (with respect to advanced aircraft concept in the field of more/all electric power MEA/AEA) was highlighted. In addition, through the analysis and selected simulations of the power supply system of a modern aircrafts, sources of onboard electrical energy (synchronous generator, integrated unit starter/AC generator) were located in board autonomic power system ASE (EPS, PES). Key components of this system are the electro-energetic power system EPS and the energo-electronic power system PES. Additionally, the analysis and exemplary simulations of key electricity sources based on mathematical models have contributed to highlighting the main practical applications in line with the trend of a more electric aircraft.
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Ismagilov, F. R., V. E. Vavilov, R. R. Urazbakhtin, and R. G. Dadoyan. "Determination of critical speed of bypass turbojet engine with integrated starter-generator high-pressure rotor." Vestnik IGEU, no. 6 (December 28, 2022): 37–48. http://dx.doi.org/10.17588/2072-2672.2022.6.037-048.

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Today, the development of aircraft within the electric aircraft concept framework is relevant. In this case, the key technology is the integrated starter-generator, which makes it possible to refuse the mechanical, pneumatic, and hydraulic power take-off from the aircraft engine. In the well-known scientific articles, integrated starter-generators are designed without considering the features due to their location inside the aircraft engines. This study starts a set of projects devoted to the design of integrated starter-generator for a bypass turbojet engine, considering the features of this technical decision. The purpose of this study is to develop approaches to determine critical rotation frequency of high-pressure rotor considering starter-generator integration. Models to determine the critical rotation frequency of a high-pressure rotor with an integrated starter-generator rotor are developed based on non-traditional models of rotor dynamics by mathematical modeling. An area for the integrated starter-generator location has been determined and a constructive method for its implementation is proposed for a bypass turbojet engine. In this study, mathematical expressions are obtained to determine high-pressure rotor critical speed in case of a detailed study of dynamics and in case of an integrated starter-generator preliminary calculations. Based on the value of the critical speed of the high-pressure rotor calculated from the obtained expressions, firstly, it is possible to check the correctness of the choice of the air gap of the integrated starter-generator and strength calculations of the integrated starter-generator in the most difficult operating mode. Secondly, it is possible to determine safe operation area of the bypass turbojet engine with an integrated starter-generator. The results of the study enhance the theoretical foundations of the design of the integrated starter-generators and make it possible to avoid errors in their design and further operation.
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Ejaz, Noveed, and Muhammad Mansoor. "Analysis of Malfunctioning of Centrifugal Compressor of Starter Engine of an Aircraft." Defect and Diffusion Forum 418 (August 19, 2022): 145–51. http://dx.doi.org/10.4028/p-2ur9hq.

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During aircraft startup, abnormal noise was heard at 100-200 RPM and the aircraft was switched off. On detailed inspection, damage and deformation was found inside the starter fairing, intakes and tail pipe. The failure analysis revealed that the damages were due to the engagement of some stock during rotation, which could be an internal engine’s object. The failure of the bearing inner race was subsequent. The fracture features of shaft were similar to the torsional overload; the fracture was started from a notched region. It was also the consequence of internal object damage.
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Bolorunduro, G. A., A. Mohammed, U. E. Uche, B. G. Ibrahim, and S. T. Audu. "Analysis and remedies for factors responsible for time between overhaul: a case study of Do-228 aircraft starter generator." Nigerian Journal of Technology 41, no. 4 (November 3, 2022): 767–77. http://dx.doi.org/10.4314/njt.v41i4.14.

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The starter generator is used for cranking the engine and to produce electricity for the aircraft system after a sustainable speed. A review of relevant literature reveals the time between the overhaul of the Do-228 aircraft starter generator but did not go in-depth to unravel the factors responsible. A survey research method is adopted to elicit information on the factors. Raosoft sample technique calculator: a software that primarily calculates or generates the sample size of a research or survey was used to obtain the minimum sample size from the study population with the nominal rolls of the technicians as the sampling frame. The questionnaire was vetted and validated by a professional focus group discussion team. The result shows that the factors responsible for the time between overhaul of the starter generator are Environmental Factors (10%), Mechanical Factors (20%), Poor Maintenance Factors (17%), Time Due (25%), Usage/Life Cycle (16%) and Aging (12%). 75% overhaul is unscheduled. It is recommended that the overhauling of the aircraft starter generators be done at 900 as against 1000 flight hour intervals to mitigate unscheduled maintenance.
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Dissertations / Theses on the topic "Aircraft starter"

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Yeoh, Seang Shen. "Control strategies for the More Electric Aircraft starter-generator electrical power system." Thesis, University of Nottingham, 2016. http://eprints.nottingham.ac.uk/34098/.

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The trend towards development of More Electric Aircraft (MEA) has been driven by increased fuel fossil prices and stricter environmental policies. This is supported by breakthroughs in power electronic systems and electrical machines. The application of MEA is expected to reduce the aircraft mass and drag, thereby increasing fuel efficiency and reduced environmental impact. The starter-generator (S/G) scheme is one of the solutions from the MEA concept that brings the most significant improvement to the electrical power generation system. A S/G system is proposed from the possible solutions brought by the MEA concept in the area of electrical power generation and distribution. Due to the wide operating speed range, limited controller stability may be present. This thesis contributes to the control plant analysis and controller design of this MEA S/G system. The general control requirements are outlined based on the S/G system operation and the control structure is presented. The control plants are derived specifically to design the controllers for the S/G control scheme. Detailed small signal analysis is performed on the derived plant while taking into consideration the aircraft operating speed and load range. A safe range for the controller gains can then be determined to ensure stable operation throughout the S/G operation. Adaptive gain and a novel current limit modifier are proposed which improves the controller stability during S/G operation. Model predictive control is considered as an alternative control strategy for potential control performance improvements with the S/G system. The technical results and simulations are supported by Matlab®/Simulink® based models and validated by experimental work on a small scaled drive system.
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Holle, Michael Jay. "Effects of hardness on the lifetime of graphite brushes used for aircraft starter generators." Thesis, Wichita State University, 2011. http://hdl.handle.net/10057/3959.

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This study concentrates on the relationship between the hardness of three different carbon/graphite brushes and the wear rate of the brushes and heat generated within a 400 Amp starter generator. The method being proposed was to alternate the starter generator from the starting mode and the generating mode, and run each carbon/graphite brush in the starter generator for a set time and document both wear rates and heat created. The study originated with a starter generator overheating during normal usage. The original hypothesis was that either excess carbon dust caused arcing, or the energy required to form the carbon dust was releasing too much heat, and thus the brush was too hard. The three carbon/graphite brushes chosen for this researched spanned the range of hardness for this type of material. This thesis analyzed the surfaces of the carbon/graphite brushes to correlate grooves and pitting with the frictional coefficient. An optical microscope, AFM, and SEM were used in the analysis of the surfaces. It was found that as the hardness of the brush went up, the wear rate decreased while the overall heat on the inside of the starter generator increased. From this research it is evident that the hardness of the brushes is the key factor in the excess heat in the starter generator. The energy that is expelled as heat as the carbon brush gradually wears is directly correlated with the increase of operating temperature. A harder brush will prolong the life of the brushes, but also increases the operating temperature to more than the unit is capable of handling.
Thesis (M.S.)--Wichita State University, College of Engineering, Dept. of Mechanical Engineering.
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DERISZADEH, ADEL. "Analysis, modeling and excitation control of three-stage brushless starter-generators for aircraft applications." Doctoral thesis, Politecnico di Torino, 2018. http://hdl.handle.net/11583/2712202.

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In the aircraft application, due to space constraints, employing integrated starter-generator is an efficacious solution. Among various electric machines, wound-rotor synchronous machine (WRSM) offers advantages of high reliability, sufficient controllability, the high power factor in a wide range of torque-speed plan, etc. The requirement of supplying rotor of WRSM is its main drawback. Since in aircraft application, safety is a critical demand, brushless type of WRSM is a practical solution. A conventional structure of brushless WRSM consists three electrical machines which are mounted on the same shaft. Therefore, this kind of WRSM is called three-stage brushless synchronous machine. The first stage of the machine is Pre-exciter which is usually a small PMG. The second stage in an inverse synchronous machine with stationary single-phase field and rotating armature which is called Main Exciter (ME). The third stage is the Main Generator (MG). Electrically, ME is connected to the MG by means of a rotating rectifier. The existence of the rotating rectifier connected between the armature windings of ME and field winding of MG significantly increases the nonlinearity of the system. In consequence, investigating the nonlinear behavior of the rotating rectifier plays a key role in studying of the brushless synchronous starter-generator. In this thesis, using analytical, numerical and experimental analysis, different operation modes of the three-stage brushless synchronous machine are investigated. Using revolving field theory, analytical description of the relationship between the stationary pulsating field flux of ME and its armature voltages is presented. Because of single-phase field winding of ME, at standstill and low-speed operations, for exciting field winding of ME, AC excitation is required. Then, by speed increasing, AC excitation must be switched to DC. Since field excitation of ME is variable, induced armature voltages of ME are different in various operating points. In this thesis, it is explained that during the starting process of the starter-generator, armature voltages of ME are severely unbalanced. Therefore, for the sake of modeling and studying, a model of rotating rectifier with an ability to deal with a wide range of unbalanced conditions is required. As the first step, in this thesis, a novel model of the uncontrolled rectifier with a capability of considering unbalanced input voltages and harmonics in AC-side is proposed.
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Song, Shoujun. "Detailed design of a 30kW switched reluctance starter-generator system used in more, all electric aircraft." Aachen Shaker, 2009. http://d-nb.info/997085940/04.

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Maalouf, Haddad Amira. "Sensorless control of brushless synchronous starter generator including sandstill and low speed region for aircraft application." Thesis, Cachan, Ecole normale supérieure, 2011. http://www.theses.fr/2011DENS0008.

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In More Electric Aircraft, different power system activities are attributed to electrical means such as the start-up of the main engine. In this context, the study of the sensorless control of the Brushless Synchronous Starter Generator (BSSG) that is used to electrically start the main engine is revealed to be a very interesting issue. For long time, the elimination of the mechanical sensor was highly recommended for reliability, cost, weight, integration issues.Hence, this work aims to transpose the results obtained in the research area to an avionic testbench. It presents an adaptive sensorless technique to use when electrically starting the main engine of the aircraft. This is achieved by elaborating three different methods selected depending on the speed of the machine and based on the :- injection of a high frequency signal- use of the back-emf of the Permanent Magnet Generator (PMG)- use of the extended Kalman Filter EKFIn this work, it is shown that the …first method gives good position estimation results from standstill up to 8% of the rated speed. Then, the back-emfs of the PMG are used to detect the position of the BSSG when the speed exceeds the 8% of the rated speed. Good results are observed with this method at medium and high speed.For redundancy reasons, the EKF was also used in this work. Thus, the estimated position can be delivered via two different estimation algorithms in medium and high speed region.The implementation of the algorithm was achieved on an FPGA board since the latter can ensure a very tiny execution time. The fastness of the treatment ensures quasi-instantaneous position estimation and does not practically introduce any phase lag in the position estimation
Aujourd'hui, l'aviation est en train de vivre des évolutions technologiques concernant surtout l'attribution de différentes fonctionnalités aux équipements électriques et ceci au détriment d'équipements hydrauliques et mécaniques assurant les mêmes fonctionnalités.Dans le cadre de l'avion plus électrique, le démarrage électrique sans capteurs mécaniques de la turbine de l'avion préoccupe les avionneurs de nos jours. Les problèmes introduits par ce capteur ont été identifiés : problèmes de coût et de poids, problèmes de fiabilité et d'intégration.Ce travail présente alors une commande sans capteurs pour la machine synchrone à trois étages à utiliser durant le démarrage électrique de l'avion. Ceci est réalisé avec trois méthodes de détection de la position selon la vitesse de rotation, basées sur :- l'injection d'un signal à haute fréquence- l'utilisation d'un filtre de Kalman étendu FKE- les fém. du PMG (Permanent Magnet Generator) La première méthode donne de bons résultats d'estimation depuis l'arrêt jusqu'à 8% de la vitesse nominale de la machine. Au-delà de cette vitesse, es valeurs des fém. du PMG deviennent assez élevées pour être utilisées dans l'estimation de la position. De bons résultats sont obtenus à moyenne et haute vitesse.Pour des questions de redondance, le FKE est aussi utilisé. Ainsi, la position estimée peut être fournie par l'un des deux algorithmes à moyenne et haute vitesse.L'implémentation de ces algorithmes est réalisée via une carte FPGA étant donné que celui-ci garantit un temps d'exécution. La rapidité de traitement garantit une estimation de la position quasi-instantanée et donc n'introduit pratiquement pas des retards dans l'estimation
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Song, Shoujun [Verfasser]. "Detailed design of a 30kW switched reluctance starter/generator system used in more/all electric aircraft / Shoujun Song." Aachen : Shaker, 2009. http://d-nb.info/1160059195/34.

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Fernando, Weeramundage Udaya Nuwantha. "Control systems for switched reluctance and permanent magnet machines in advanced vehicular electric networks." Thesis, University of Manchester, 2012. https://www.research.manchester.ac.uk/portal/en/theses/control-systems-for-switched-reluctance-and-permanent-magnet-machines-in-advanced-vehicular-electric-networks(ba4d8974-e749-4fbc-b690-824002873a96).html.

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This thesis presents the design and analysis of specialised control systems for switched reluctance (SR) and permanent magnet (PM) machines in vehicular electric applications. Control systems for operation in motoring and power generation are considered for both the types of machines. The SR machine operation considered in this thesis is mainly focused towards the application of aero-engine starter/generators. The control designs for PM machines are formulated considering general fault-tolerant and isolated multiphase PM machines which can be applied in the majority of safety-critical vehicular power and propulsion applications. The SR motoring mode presented in this thesis considers the control design for operation from zero speed to a high speed range, while SR generation mode is confined to the high speed range, such as for the requirements of aero-engine starter/generator operation. This thesis investigates applied control methods for both single-pulse and chopping modes of operation. Classical excitation control versus peak current control and the introduction of a zero-voltage interval are compared for SR motor operation. Optimized excitation control versus two classical forms of excitation control are developed and compared for SR generator operation. Studies include simulation of a 12/8 250kW machine and experimental work on a 6/4 300W machine. The PM motoring and power generation considered in this thesis focuses on a special class of PM machines and drives which are specifically designed for fault-tolerant operation. Optimized control strategies for the operation of PM machines with the parallel H-bridge per-phase converter architecture are investigated. Mathematical modelling of the machine and drive with a consideration of harmonics is presented. The developed control methods are then evaluated by means of finite-element model based simulations of a 125kW five phase surface PM rotor machine and an interior PM rotor machine.
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Bui, Minh Dinh [Verfasser], Uwe [Akademischer Betreuer] Schaefer, Sibylle [Akademischer Betreuer] Dieckerhoff, Nguyen Phung [Akademischer Betreuer] Quang, and Kai [Akademischer Betreuer] Strunz. "Maximum torque control of a high speed switched reluctance starter/generator used in more/all electric aircraft / Minh Dinh Bui. Gutachter: Sibylle Dieckerhoff ; Nguyen Phung Quang ; Kai Strunz. Betreuer: Uwe Schaefer." Berlin : Technische Universität Berlin, 2014. http://d-nb.info/1067386394/34.

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Beciu, Andreea-Livia. "Commande robuste à haute performance sans capteur de position d'alterno-démarreurs à grande vitesse avec un fort couple à l'arrêt pour les avions plus électriques." Thesis, Université Paris-Saclay (ComUE), 2018. http://www.theses.fr/2018SACLC078.

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Les avionneurs expriment le besoin de développement de l’avion plus « électrique ». Cela se traduit par des besoins nouveaux en matière de systèmes de motorisation électrique, en termes de puissance à fournir et de partage de ressources matérielles en vue de minimiser la masse embarquée et les coûts. Parmi les études en cours sur l’évolution des machines tournantes, un intérêt particulier porte sur le développement des alterno-démarreurs de type machines synchrones sans balais et à plusieurs étages (BSSG). Celles-ci sont susceptibles de fournir un fort couple lors des phases de démarrage des réacteurs auxquelles elles sont associées. Pour ce faire, la connaissance, à tout moment, de la position du rotor est essentielle. Cependant, l'ajout d’un capteur dédié impacte la conception de la machine, rajoutant du volume, du câblage et augmentant le coût. La réalisation d'une commande dite « sensorless » permettrait de s'affranchir de l'utilisation d'un tel capteur et de simplifier le design des alterno-démarreurs.A partir d'une modélisation fine de la machine, cette thèse étudie les conditions dans lesquelles une telle commande est réalisable et analyse plusieurs techniques permettant d'y parvenir. Une nouvelle méthode d'estimation de la position du rotor, spécifique aux BSSG est proposée, puis illustrée avec des résultats expérimentaux. Cette technique est basée sur le traitement des composantes harmoniques existantes naturellement au stator de la machine et permet l'estimation de la position à l'arrêt et à très basse vitesse. Afin d'étendre l'estimation sur toute la plage de vitesse, une étude d'estimation de position par un observateur d'état à base du modèle complet de la machine en considérant les harmonique injectés (ou existantes) dans les courants du stator est proposée. Cet observateur peut s’appliquer à la machine synchrone à trois étages mais aussi à toute machine synchrone. Dans cette étude, son fonctionnement est illustré sur une machine synchrone à aimants permanents
The aircraft manufacturers express the need to develop a more "electric" aircraft. This brings forward new requirements for the electric drive systems in terms of increasing the available on-board power and resource sharing in order to optimize the overall mass and cost. Among the ongoing studies on the evolution of motor drives, a particular interest is given to the development of multi-level brushless synchronous starter/generators (BSSG). These drives are likely to provide the high torque required to start-up the reactors to which they are associated. For this purpose, the knowledge, at any time, of the rotor position is essential. However, adding a dedicated sensor impacts on the design of the machine, increasing volume, cabling needs and cost. For this purpose, investigating on “sensorless” control laws will permit to avoid using such a sensor and to simplify the design of the Starter/Generators.Using a fine modelling of the machine, this work studies the conditions of feasibility for sensorless control and analyzes several techniques for this purpose. A new method of estimation of the shaft-position, particular to the BSSG architecture is proposed and then illustrated with experimental results. This technique is based on the processing of the existing harmonic components naturally in the stator of the machine and allows the estimation of the position at standstill and the very low speed. To extend the estimation to the whole speed range, a study of position estimation using a state observer using the complete model of the machine considering the knowledge of the existing (or injected) harmonic components in the stator currents is proposed. This observer can be applied to the brushless synchronous starter/generator but also on generic synchronous machines. In this study, its performance is illustrated on a permanent magnet synchronous machine
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Martin, Wayne Leslie. "Pathological Behaviours in Pilots during Unexpected Critical Events: The Effects of Startle, Freeze and Denial on Situation Outcome." Thesis, Griffith University, 2014. http://hdl.handle.net/10072/366319.

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Over the last 40 years significant advances in aviation technology have contributed strongly to improvements in aviation safety. Recent figures suggest that fourth generation aircraft are now achieving fatal accident rates in the order of 10-7 and ongoing work continues to improve this rate. Significant improvements in engine and systems reliability, coupled with safety technologies such as Enhanced Ground Proximity Warning (EGPWS), Airborne Collision Avoidance Systems (ACAS), Global Positioning System (GPS), and Vertical Situation Displays (VSD) have contributed to reductions in accident rates. Additionally, initiatives such as RNAV and RNP (AR) approaches continue to improve non-precision approach accuracy and safety while air traffic control improvements continue to accommodate this increased safety as aircraft traffic continues to grow strongly. Nevertheless, the reliability engendered by all these incremental improvements to safety has a downside. While pilots in the earlier years of airline transport had a healthy expectation for engine and systems failures, the modern airline pilot does not necessarily share this. Indeed, the modern airline aircraft is so reliable, and failures are so rare, that pilots are now unwittingly conditioned into an expectation of unwavering reliability. This unintentional complacency means that attention to emergency procedures and an expectation for dealing with real malfunctions is not as well honed as it perhaps once was.
Thesis (PhD Doctorate)
Doctor of Philosophy (PhD)
School of Biomolecular and Physical Sciences
Science, Environment, Engineering and Technology
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Books on the topic "Aircraft starter"

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Zuev, Sergey, Ruslan Maleev, and Aleksandr Chernov. Energy efficiency of electrical equipment systems of autonomous objects. ru: INFRA-M Academic Publishing LLC., 2021. http://dx.doi.org/10.12737/1740252.

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When considering the main trends in the development of modern autonomous objects (aircraft, combat vehicles, motor vehicles, floating vehicles, agricultural machines, etc.) in recent decades, two key areas can be identified. The first direction is associated with the improvement of traditional designs of autonomous objects (AO) with an internal combustion engine (ICE) or a gas turbine engine (GTD). The second direction is connected with the creation of new types of joint-stock companies, namely electric joint-stock companies( EAO), joint-stock companies with combined power plants (AOKEU). The energy efficiency is largely determined by the power of the generator set and the battery, which is given to the electrical network in various driving modes. Most of the existing methods for calculating power supply systems use the average values of disturbing factors (generator speed, current of electric energy consumers, voltage in the on-board network) when choosing the characteristics of the generator set and the battery. At the same time, it is obvious that when operating a motor vehicle, these parameters change depending on the driving mode. Modern methods of selecting the main parameters and characteristics of the power supply system do not provide for modeling its interaction with the power unit start-up system of a motor vehicle in operation due to the lack of a systematic approach. The choice of a generator set and a battery, as well as the concept of the synthesis of the power supply system is a problem studied in the monograph. For all those interested in electrical engineering and electronics.
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Grant, Barbara G. Getting Started with UAV Imaging Systems: A Radiometric Guide. SPIE, 2016.

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Schmidt, Robert Kyle. The Design of Aircraft Landing Gear. SAE International, 2021. http://dx.doi.org/10.4271/9780768099430.

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The aircraft landing gear and its associated systems represent a compelling design challenge: simultaneously a system, a structure, and a machine, it supports the aircraft on the ground, absorbs landing and braking energy, permits maneuvering, and retracts to minimize aircraft drag. Yet, as it is not required during flight, it also represents dead weight and significant effort must be made to minimize its total mass. The Design of Aircraft Landing Gear, written by R. Kyle Schmidt, PE (B.A.Sc. - Mechanical Engineering, M.Sc. - Safety and Aircraft Accident Investigation, Chairman of the SAE A-5 Committee on Aircraft Landing Gear), is designed to guide the reader through the key principles of landing system design and to provide additional references when available. Many problems which must be confronted have already been addressed by others in the past, but the information is not known or shared, leading to the observation that there are few new problems, but many new people. The Design of Aircraft Landing Gear is intended to share much of the existing information and provide avenues for further exploration. The design of an aircraft and its associated systems, including the landing system, involves iterative loops as the impact of each modification to a system or component is evaluated against the whole. It is rare to find that the lightest possible landing gear represents the best solution for the aircraft: the lightest landing gear may require attachment structures which don't exist and which would require significant weight and compromise on the part of the airframe structure design. With those requirements and compromises in mind,The Design of Aircraft Landing Gear starts with the study of airfield compatibility, aircraft stability on the ground, the correct choice of tires, followed by discussion of brakes, wheels, and brake control systems. Various landing gear architectures are investigated together with the details of shock absorber designs. Retraction, kinematics, and mechanisms are studied as well as possible actuation approaches. Detailed information on the various hydraulic and electric services commonly found on aircraft, and system elements such as dressings, lighting, and steering are also reviewed. Detail design points, the process of analysis, and a review of the relevant requirements and regulations round out the book content. The Design of Aircraft Landing Gear is a landmark work in the industry, and a must-read for any engineer interested in updating specific skills and students preparing for an exciting career.
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Getting Started with Drones: Build and Customize Your Own Quadcopter. Make Community, LLC, 2015.

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Book chapters on the topic "Aircraft starter"

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"Stress Corrosion Cracking of 4340 Steel in Aircraft Ignition Starter Residues." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001560.

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Kiracı, Kasım. "Financial Determinants Affecting Leasing Policies." In Applied Econometric Analysis, 190–213. IGI Global, 2020. http://dx.doi.org/10.4018/978-1-7998-1093-3.ch009.

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Airline companies have started to develop strategies to increase their market share and expand their network structure with the effect of globalization. In this process, one of the most important sources of airline companies to achieve competitive advantage is aircraft. Airline companies have to increase the number of aircraft in the fleet to expand their network structure. On the other hand, the high price of aircraft has led airline companies to adopt new financing strategies. Leasing is one of the financing methods used frequently by airline companies recently. Therefore, this study focuses on the leasing policies of airline companies. In this study, it is aimed to reveal the factors affecting the leasing policies of airline companies. In this context, 26 airlines operating in the period 2000-2017 were analyzed empirically. Panel data analysis was used as the method in the study. The empirical findings of the study indicate that return on assets, asset structure, tangibility, leverage ratio, and liquidity affects the leasing policies of airline companies.
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Shaukat, Syed, and Cheng-Lung Wu. "Impact of Hydrogen Fuel Cell Technology on Aircraft Maintenance." In Challenges and Opportunities for Aviation Stakeholders in a Post-Pandemic World, 49–63. IGI Global, 2023. http://dx.doi.org/10.4018/978-1-6684-6835-7.ch003.

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The aviation industry is adopting a promising approach to decarbonize the aviation sector dramatically by incorporating hydrogen fuel cell technology and expects to start some commercial services as early as 2035. The authors estimate the aircraft operating cost to become less expensive eventually with this forthcoming fuel cell technology, and the total maintenance cost of hydrogen-powered aircraft to come down in the long run for all segments of the aviation sector, from short haul to long haul services. With the possible incorporation of a new superconducting electrical system, a pneumatic power system, and a fully integrated electrical drive train system, additional maintenance will be required due to their cryogenic factors and associated safety issues. This chapter focuses on the potential impacts of hydrogen fuel cell technology on aircraft maintenance reliability, cost, and safety across the wide range of commuter, regional, short, medium, and long-haul segments of the aviation industry.
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Ferreiro, Larrie D. "Fight in the Hills." In Churchill's American Arsenal, C8–270. Oxford University PressNew York, 2022. http://dx.doi.org/10.1093/oso/9780197554012.003.0008.

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Abstract A week after D-Day, the first V-1 buzz bombs began falling on London. By that point in the war, the Allies had spent several years tackling the problem of shooting down enemy aircraft. This chapter describes the development of three of the most successful innovations. The first, the Oerlikon anti-aircraft gun, had been smuggled out of Switzerland at the start of the war, and through a series of political maneuvers was manufactured in both British and American factories. Similarly, the Bofors gun was spirited out of Sweden through espionage and smuggling operations, and mass-produced in converted locksmith plants and factories set up by automobile firms. The proximity fuze began in Britain as a series of experiments to increase the lethality of anti-aircraft shells, and when its research and development project was taken over by the Americans shortly before Pearl Harbor, it grew to be one of the most critical of the war, helping defeat the V-1s and winning the Battle of the Bulge.
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"Failure Analyses of Steel Breech Chambers Used With Aircraft Cartridge Ignition Starters." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c9001145.

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Wylie, Donald P. "Cirrus and Weather: A Satellite Perspective." In Cirrus. Oxford University Press, 2002. http://dx.doi.org/10.1093/oso/9780195130720.003.0010.

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Cirrus were originally thought of as benign cloud forms that could be used for predicting the onset of foul weather, such as “mare's tails” and “anvil edges,” but not of great concern because they do not produce any damaging winds or hydrometers. Our original view of cirrus was from the ground, so they were mostly ignored until aircraft started flying in them and making cirruslike contrails in the latter part of World War II. Cirrus limited visibility for the aircraft, and contrails made detection of aircraft from the ground easier. This led to the first studies of cirrus by the Air Force (Stone 1957). Had our first views of earth been from space, cirrus would have been an obvious cloud and often an obstruction to viewing everything else on the planet. Cirrus are difficult to see on visual satellite images, which is deceiving because they reflect enough solar radiation to obscure quantitative measurements of the land and water surfaces. Cirrus are more obvious in window channel infrared images, and they block any sensor that tries to look horizontally through them from either aircraft or satellites. The term “invisible cirrus” originated from an attempt to fly a horizontal viewing sensor on an aircraft for detecting approaching objects (missiles). The sensor was obscured because of its long path length through cirrus, while ground observers did not report the cirrus. Pilots were uncertain whether they were in a cloud or not. The frequency of cirrus reported from satellite data often surprises other scientists. Wylie and Menzel (1999) reported finding cirrus in 25-30% of GOES/VAS (Geostationary Operational Environmental Satellite/Visual spin scan radiometer Atmospheric Sounder) data over the continental United States. A similar satellite instrument flying globally, the HIRS (High Resolution Infrared Radiometer Sounder) on the National Oceanic and Atmospheric Administration (NOAA) satellites, reported cirrus 43% of the time (Wylie and Menzel 1994; Wylie and Menzel 1999). The horizontally viewing SAGE (Stratospheric Aerosol and Gas Experiment) is even more sensitive and reports cirrus in 50-70% of its data (Wang et al. 1996). These numbers should not have surprised people because the compilations of ground-based weather observations by Warren et al. (1988) show cirrus frequencies as high as 75% in Indonesia.
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Ferreiro, Larrie D. "Fight with Growing Confidence." In Churchill's American Arsenal, C2—C2.P92. Oxford University PressNew York, 2022. http://dx.doi.org/10.1093/oso/9780197554012.003.0002.

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Abstract After the fall of France and the evacuation at Dunkirk, Britain was fighting Germany almost alone. At the same time, its prewar preparations gave it the ability to withstand the initial Nazi assaults from the air (the Battle of Britain and the Blitz). This chapter begins by describing how radar had been adapted to a new defensive system called Chain Home, while British factories were dispersed to provide resiliency. It shows that the United States began opening its own factories to British purchases of aircraft and weapons, which jump-started the defense economy after a decade of Depression-era austerity; this was followed by the Lend-Lease Act of 1941, which allowed purchase on credit. The chapter recounts how the Tizard Mission had introduced the United States to British technology, notably the cavity magnetron, which enabled smaller microwave radars to be fitted into aircraft, to improve air combat and strategic bombing. American science was mobilized under the Organization for Scientific Research and Development (OSRD), led by Vannevar Bush, which established strong cooperation with British research through the OSRD London Mission, led by Bennett Archambault.
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"Applications of DC Motors." In Advances in Computer and Electrical Engineering, 307–48. IGI Global, 2015. http://dx.doi.org/10.4018/978-1-4666-8441-6.ch010.

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This chapter gives the motivation behind using direct current machines and its application in various domains. The authors start discussing the applications of DC machines in toys, disk drives Steel rolling mills, Paper machines, Generator, Electrical Propulsion, Cranes, CD/DVD players, Electric vehicles, RC Vehicles, UAVs, Cement Plants, and Aircraft applications. They then provide a case study on the application of DC Chopper Motor Drive. They conclude the chapter by discussing the use of D.C. Series Motors in Electric Traction.
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Baxter, Colin F. "Torpex and the Battle of the Atlantic." In The Secret History of RDX. University Press of Kentucky, 2018. http://dx.doi.org/10.5810/kentucky/9780813175287.003.0011.

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At the start of World War II, Allied aircraft lacked an effective airborne weapon to use against U-boats in the Battle of the Atlantic. The importance of the Operational Research Section at RAF Coastal Command. Initially, the commander-in-chief of RAF Coastal Command and his civilian scientists were in agreement, but differences over weapon size almost led to the abandonment of the most promising aerial anti-U-boat weapon, the 250-pound Torpex-filled airborne depth charge. The Hedgehog antisubmarine weapon would also fire Torpex-filled projectiles.
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Ginor, Isabella, and Gideon Remez. "In the Thick of the Yom Kippur War." In The Soviet-Israeli War, 1967-1973, 337–46. Oxford University Press, 2017. http://dx.doi.org/10.1093/oso/9780190693480.003.0030.

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Recent testimony from a Soviet general and others showed that the transport aircraft which evacuated the dependents of Soviet advisers from Egypt on the eve of the Yom Kippur War also flew in more advisers to assist in the crossing of the Suez Canal. Another indication of Soviet collusion is the immediate start of a Soviet resupply effort as soon as the offensive was launched on 6 October, which proves earlier prepositioning. Both advisers and Soviet special forces were involved in operations across the canal. Soviet SAM batteries were also redeployed in Egypt and Syria, especially after the tide turned against the Arab onslaught after the first days of fighting. .
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Conference papers on the topic "Aircraft starter"

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Kasram, Santhosh, Sajath Kumar Manoharan, Mahesh P. Padwale, and G. P. Ravishankar. "Engine Ground Start Characteristics of Fighter Aircraft at High Altitude Airbase." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2488.

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Abstract The challenges faced during starting of an aircraft gas turbine engine using a Jet Fuel Starter (JFS) at high altitude airbase are discussed in this paper. Autonomous ground starts at high altitude airbase in soaked sub-zero temperature condition without any external ground support assistance is a challenge. Generally, the start cycle (sub-idle speed) at sub-zero temperatures of a gas turbine engine at high altitudes is influenced by several factors. Drag loads are estimated due to change in lube oil viscosity of engine gearbox and accessory gear box that affects available torque margin of a starter. These estimated loads are superimposed on starter characteristics to identify the available margins for successful starts. The cold start is particularly severe, since it increases the tip clearance between rotor and casing of the engine due to difference in its thermal growth. Higher tip clearances significantly degrade compressor surge margin and results in rotating stall. Inconsistent engine starts were resolved by adopting alternative methods without any change in hardware. This paper presents set of methods used to overcome inconsistent engine starts at high altitude cold weather conditions.
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Arumugam, Puvan, Chris Gerada, Serhiy Bozhko, He Zhang, Weeramundage Fernando, Antonino La Rocca, and Stephen Pickering. "Permanent Magnet Starter-Generator for Aircraft Application." In SAE 2014 Aerospace Systems and Technology Conference. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2014. http://dx.doi.org/10.4271/2014-01-2157.

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Sarakhanova, Regina Yu, Sergey A. Kharitonov, Maksim A. Zharkov, and Dmitry A. Shtein. "The Adaptive Starter-Generator System for Aircraft." In 2021 XVIII International Scientific Technical Conference Alternating Current Electric Drives (ACED). IEEE, 2021. http://dx.doi.org/10.1109/aced50605.2021.9462314.

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Harikumaran, Jayakrishnan, Giampaolo Buticchi, Michael Galea, Alessandro Costabeber, and Pat Wheeler. "Reliability Analysis of aircraft starter generator drive converter." In 2019 IEEE 15th Brazilian Power Electronics Conference and 5th IEEE Southern Power Electronics Conference (COBEP/SPEC). IEEE, 2019. http://dx.doi.org/10.1109/cobep/spec44138.2019.9065643.

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Lei, Jiaxing, Bo Zhou, Jiadan Wei, Xianhui Qin, and Jinliang Bian. "Aircraft starter/generator system based on indirect matrix converter." In IECON 2014 - 40th Annual Conference of the IEEE Industrial Electronics Society. IEEE, 2014. http://dx.doi.org/10.1109/iecon.2014.7049234.

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Williams, R. H., M. P. Foster, D. A. Stone, and S. R. Minshull. "Utilizing existing aircraft wound field generators for starter-generators." In ECCE Asia (ICPE 2011- ECCE Asia). IEEE, 2011. http://dx.doi.org/10.1109/icpe.2011.5944641.

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Zharkov, Maksim A., and Vadim E. Sidorov. "Electric Starter System for Launching a Gas Turbine Aircraft Engine." In 2019 20th International Conference of Young Specialists on Micro/Nanotechnologies and Electron Devices (EDM). IEEE, 2019. http://dx.doi.org/10.1109/edm.2019.8823513.

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AbdElhafez, Ahmed A., and Ali M. Yousef. "Machine Topology for Integral Starter-Generator in More-Electric Aircraft." In 2019 International Conference on Innovative Trends in Computer Engineering (ITCE). IEEE, 2019. http://dx.doi.org/10.1109/itce.2019.8646631.

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Hu, Xunyao, Hailang Du, He Wang, and Yongfeng Wang. "Study on accelerated life testing method for air turbine starter." In 2016 IEEE/CSAA International Conference on Aircraft Utility Systems (AUS). IEEE, 2016. http://dx.doi.org/10.1109/aus.2016.7748041.

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Dehghani Tafti, Hossein, Ali I. Maswood, Ziyou Lim, Gabriel H. P. Ooi, and Pinkymol Harikrishna Raj. "Proportional-resonant controlled NPC converter for more-electric-aircraft starter-generator." In 2015 IEEE 11th International Conference on Power Electronics and Drive Systems. IEEE, 2015. http://dx.doi.org/10.1109/peds.2015.7203443.

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Reports on the topic "Aircraft starter"

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Gungor, Osman, Imad Al-Qadi, and Navneet Garg. Pavement Data Analytics for Collected Sensor Data. Illinois Center for Transportation, October 2021. http://dx.doi.org/10.36501/0197-9191/21-034.

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The Federal Aviation Administration instrumented four concrete slabs of a taxiway at the John F. Kennedy International Airport to collect pavement responses under aircraft and environmental loading. The study started with developing preprocessing scripts to organize, structure, and clean the collected data. As a result of the preprocessing step, the data became easier and more intuitive for pavement engineers and researchers to transform and process. After the data were cleaned and organized, they were used to develop two prediction models. The first prediction model employs a Bayesian calibration framework to estimate the unknown material parameters of the concrete pavement. Additionally, the posterior distributions resulting from the calibration process served as a sensitivity analysis by reporting the significance of each parameter for temperature distribution. The second prediction model utilized a machine-learning (ML) algorithm to predict pavement responses under aircraft and environmental loadings. The results demonstrated that ML can predict the responses with high accuracy at a low computational cost. This project highlighted the potential of using ML for future pavement design guidelines as more instrumentation data from future projects are collected to incorporate various material properties and pavement structures.
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Webb, Philip, and Sarah Fletcher. Unsettled Issues on Human-Robot Collaboration and Automation in Aerospace Manufacturing. SAE International, November 2020. http://dx.doi.org/10.4271/epr2020024.

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This SAE EDGE™ Research Report builds a comprehensive picture of the current state-of-the-art of human-robot applications, identifying key issues to unlock the technology’s potential. It brings together views of recognized thought leaders to understand and deconstruct the myths and realities of human- robot collaboration, and how it could eventually have the impact envisaged by many. Current thinking suggests that the emerging technology of human-robot collaboration provides an ideal solution, combining the flexibility and skill of human operators with the precision, repeatability, and reliability of robots. Yet, the topic tends to generate intense reactions ranging from a “brave new future” for aircraft manufacturing and assembly, to workers living in fear of a robot invasion and lost jobs. It is widely acknowledged that the application of robotics and automation in aerospace manufacturing is significantly lower than might be expected. Reasons include product variability, size, design philosophy, and relatively low volumes. Also, the occasional reticence due to a history of past false starts plays a role too. Unsettled Issues on Human-Robot Collaboration and Automation in Aerospace Manufacturing goes deep into the core questions that really matter so the necessary step changes can move the industry forward.
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Lever, James, and Jason Weale. High efficiency fuel sleds for Polar traverses. Engineer Research and Development Center (U.S.), March 2022. http://dx.doi.org/10.21079/11681/43445.

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We describe here the evolution of lightweight, high-efficiency fuel sleds for Polar over-snow traverses. These sleds consist of flexible bladders strapped to sheets of high molecular weight polyethylene. They cost 1/6th, weigh 1/10th and triple the fuel delivered per towing tractor compared with steel sleds. An eight-tractor fleet has conducted three 3400-km roundtrips to South Pole with each travers delivering 320,000 kg of fuel while emitting <1% the pollutants, consuming 1/2 the fuel and saving $1.6 M compared with aircraft resupply. A two tractor fleet in Greenland recently delivered 83,000 kg of fuel in bladder sleds to Summit with similar benefits. Performance monitoring has revealed that bladder-sled towing resistance is largely governed by sliding friction, which can start high and drop in half over the first 30 min of travel. Frictional heating probably produces a thin water layer that lubricates the sled–snow interface. Consequently, towing resistance depends on the thermal budget of the sled. For example, black fuel bladders increase solar gain and thus decrease sled resistance; data suggest they could double again the fuel delivered per tractor. The outstanding efficiency and low cost of these sleds has transformed fuel delivery to Polar research stations.
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