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Journal articles on the topic 'Aircraft starter'

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Author: Grafiati

Published: 14 March 2023

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1

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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

Ismagilov, F. R., Sh G. Ismagilov, N. G. Tarasov, and V. V. Ayguzina. "Selecting Optimal Dimensions for a High-Temperature Aircraft Starter Generator." Russian Electrical Engineering 89, no. 1 (January 2018): 21–24. http://dx.doi.org/10.3103/s1068371218010078.

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12

Song, Shoujun, and Weiguo Liu. "Load Effect on Switched Reluctance Starter/Generator System in Aircraft." International Journal of Electrical and Power Engineering 4, no. 1 (January 1, 2010): 19–26. http://dx.doi.org/10.3923/ijepe.2010.19.26.

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13

Zhou, Yue Fei, and Lin Lin. "Fault Analysis and Improvement of Starter Contactor of Cessna 172R Power System." Advanced Materials Research 926-930 (May 2014): 785–88. http://dx.doi.org/10.4028/www.scientific.net/amr.926-930.785.

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The aircraft AC generator is the most important component in the aero-power system, which has close relationship with the flight safety. This paper recorded Cessna 172Rs power system failure, analyzed the cause of this failure, studied the principle and mechanism of contactor in this aircraft. It proposed three measures to eliminate similar fault, to be popularized and applied in the practical application, it was proved that it can reduce the incidence of this kind of trouble.

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14

Mohamed, Mohamed A. A., Seang Shen Yeoh, Jason Atkin, Ahmed M. Diab, Mohsen Khalaf, and Serhiy Bozhko. "Enhanced Starting Control Scheme for PMM-Based Starter/Generator System for MEA." Aerospace 10, no. 2 (February 11, 2023): 168. http://dx.doi.org/10.3390/aerospace10020168.

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A control approach for aircraft Starter/Generator (S/G) with Permanent Magnet Machine (PMM) operating in Flux Weakening (FW) mode is presented. The proposed strategy helps the previous approaches which are adopted for the Variable Voltage Bus (VVB) or Voltage Wild Bus (VWB) concept for an aircraft Electric Power System (EPS), to cover a wide speed range in motoring and generation modes. Compared to prior works, the proposed control approach adjusts the q-axis reference voltage with a single current regulator, and the maximum available voltage provided by the converter is used to evaluate the d-axis voltage. By adopting the proposed approach, the DC bus voltage can be fully utilized, increasing aircraft efficiency by allowing the S/G system to operate at a wide range of speeds. The results of the analytical design and the performance of the system were verified by time-domain simulations using MATLAB/Simulink and experiments and compared to the conventional method.

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15

Nova, Muhammad Andi, Lalu Giat Juangsa Putra, and Zakki Fuadi Emzain. "Komparasi Efektivitas Tiga Tipe Starter Generator yang Digunakan Pada Engine Pesawat ATR." AVITEC 3, no. 2 (July 30, 2021): 131. http://dx.doi.org/10.28989/avitec.v3i2.1027.

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A starter generator (DC generator) is a DC machine that acts as a motor when starting the engine and will become a DC generator when it reaches a certain speed. The DC Starter Generator will function as a starter mode when the speed is <45% NH and will become a DC generator mode when the speed is >61.5%. There are several types of starter generators on ATR aircraft: 8260-121, 8260-123, and 8260-124. The uses and functions of the three types are the same, but the maintenance schedule intervals are different. Therefore, the purpose of this study was to determine the planned maintenance intervals (brush change, bearing change, and overhaul) and the causes of differences in maintenance intervals for the starter generator. The type of research used is comparative research, where this research compares several parameters related to the planned maintenance of the Starter Generator, which will be operated within 10,000 FH. The results of the treatment intervals obtained are that types 8260-121 and 8260-123 each will require 16 times maintenance, while types 8260-124 only need 8 times maintenance. The difference in the number of treatments being less in the 8260-124 type is due to the modification of the brush. In addition, the type 8260-124 has also used a new technology commutator. Therefore, this type is superior to the other two because it can save operational aircraft costs.

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16

Ismagilov, F. R., I. Kh Khairullin, V. E. Vavilov, D. R. Farrakhov, A. M. Yakubov, and V. I. Bekuzin. "A high-temperature frameless starter-generator integrated into an aircraft engine." Russian Aeronautics (Iz VUZ) 59, no. 1 (January 2016): 107–11. http://dx.doi.org/10.3103/s1068799816010177.

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17

Durazo-Cardenas, I., A. Starr, R. Sousa, J. Ferreira, A. Mota, M. Kram, G. Hughes, P. Bytnar, and F. Bel. "Towards health monitoring of hybrid ceramic bearings in aircraft starter/generators." Procedia Manufacturing 19 (2018): 50–57. http://dx.doi.org/10.1016/j.promfg.2018.01.008.

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18

Kennelley, K. J., and R. D. Daniels. "Stress corrosion cracking of 4340 steel in aircraft ignition starter residues." Journal of Materials Engineering 9, no. 1 (March 1987): 35–40. http://dx.doi.org/10.1007/bf02833785.

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19

VAVILOV, V. E., F. R. ISMAGILOV, L. A. FINKELBERG, A. N. KOSTYUCHENKOV, and I. F. SAYAKHOV. "Multidisciplinary design and ground tests of starter-generator for small aircraft." Elektrotekhnika, no. 12 (2022): 4–7. http://dx.doi.org/10.53891/00135860_2022_12_4.

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20

Montazeri-Gh, Morteza, and Seyed Alireza Miran Fashandi. "Bond graph modeling of a jet engine with electric starter." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 9 (August 14, 2018): 3193–210. http://dx.doi.org/10.1177/0954410018793772.

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Following the technological advances in recent decades, advanced electronic systems linked to the gas turbine industry are increasingly considered by the designers of this field. For this purpose, new airborne systems in conjunction with jet engines are developed, which are incorporated in many challenging design problems such as control law and configuration design. Thus, a comprehensive modeling structure is needed that can bolster the integrity of the system development such as the bond graph approach, which is known as an efficient method for modeling complicated mechatronic systems. In this paper, modeling and simulation of a jet engine dynamic performance and aircraft motion are achieved based on the bond graph approach. At first, the electric starter bond graph model is constructed and physical relationships governing each engine component are obtained. In the aftermath, the modulated energy fields are developed for the jet engine components. Subsequently, the bond graph model of the engine is numerically simulated and experimentally tested and verified for a small jet engine. Finally, bond graph modeling and simulation of integrated engine and aircraft system is presented. The test results indicate the acceptable accuracy of the modeling approach which can be applied for innovative diagnosis and control systems design.

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21

Zhang, Zhuoran, Jian Huang, Yunyi Jiang, Weiwei Geng, and Yanwu Xu. "Overview and analysis of PM starter/generator for aircraft electrical power systems." CES Transactions on Electrical Machines and Systems 1, no. 2 (2017): 117–31. http://dx.doi.org/10.23919/tems.2017.7961293.

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22

Ismagilov, Flur, Alexander Gerasin, Vyacheslav Vavilov, Ruslan Karimov, and Nikolay Tarasov. "Experimental Study of High- Temperature Starter-Generator with Integratibility in Aircraft Engine." Известия высших учебных заведений. Электромеханика 61, no. 2 (2018): 34–41. http://dx.doi.org/10.17213/0136-3360-2018-2-34-41.

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23

Ismagilov, F. R., and V. E. Vavilov. "Optimization of a High-Temperature Starter—Generator of Inverted Design for Aircraft." Russian Electrical Engineering 90, no. 5 (May 2019): 391–96. http://dx.doi.org/10.3103/s1068371219050067.

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24

Zhang, Zhuoran, Ye Liu, and Jincai Li. "A HESM-Based Variable Frequency AC Starter-Generator System for Aircraft Applications." IEEE Transactions on Energy Conversion 33, no. 4 (December 2018): 1998–2006. http://dx.doi.org/10.1109/tec.2018.2867906.

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25

Mao, Shuai, Weiguo Liu, Peng Ma, Zan Zhang, and Ying Hu. "Initial rotor position estimation method for aircraft wound-rotor synchronous starter/generators." Journal of Engineering 2018, no. 13 (January 1, 2018): 541–45. http://dx.doi.org/10.1049/joe.2018.0049.

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26

Bozhko, Serhiy, Tao Yang, Jean-Marc Le Peuvedic, Puvan Arumugam, Marco Degano, Antonino La Rocca, Zeyuan Xu, et al. "Development of Aircraft Electric Starter–Generator System Based on Active Rectification Technology." IEEE Transactions on Transportation Electrification 4, no. 4 (December 2018): 985–96. http://dx.doi.org/10.1109/tte.2018.2863031.

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27

Oksuztepe, Eyyup, and Ufuk Kaya. "Performance analysis of more electric aircraft starter/generator by different electric loads." International Journal of Sustainable Aviation 1, no. 1 (2023): 1. http://dx.doi.org/10.1504/ijsa.2023.10051737.

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28

Vavilov, V. E., F. R. Ismagilov, L. A. Finkelberg, A. N. Kostyuchenkov, and I. F. Sayakhov. "Multidisciplinary Designing and Ground Tests of a Starter Generator for Small Aircraft." Russian Electrical Engineering 93, no. 12 (December 2022): 743–46. http://dx.doi.org/10.3103/s1068371222120148.

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29

Ismagilov, F. R., I. Kh Khairullin, V. E. Vavilov, and A. M. Yakupov. "Comparison of two configurations of a starter-generator integrated into the aircraft engine." Russian Aeronautics 60, no. 3 (July 2017): 463–68. http://dx.doi.org/10.3103/s1068799817030217.

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30

Griffo, Antonio, Rafal Wrobel, Phil H. Mellor, and Jason M. Yon. "Design and Characterization of a Three-Phase Brushless Exciter for Aircraft Starter/Generator." IEEE Transactions on Industry Applications 49, no. 5 (September 2013): 2106–15. http://dx.doi.org/10.1109/tia.2013.2269036.

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31

Sadeghi, Ramtin, Seyed M. Madani, Mohammad‐Reza Agha‐kashkooli, and Mohammad Ataei. "Reduced‐order model of cascaded doubly fed induction generator for aircraft starter/generator." IET Electric Power Applications 12, no. 6 (February 27, 2018): 757–66. http://dx.doi.org/10.1049/iet-epa.2017.0579.

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32

Noland, Jonas Kristiansen, Matteo Leandro, Jon Are Suul, and Marta Molinas. "High-Power Machines and Starter-Generator Topologies for More Electric Aircraft: A Technology Outlook." IEEE Access 8 (2020): 130104–23. http://dx.doi.org/10.1109/access.2020.3007791.

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33

Jiao, Ningfei, Weiguo Liu, Tao Meng, Chenghao Sun, and Yu Jiang. "Decoupling control for aircraft brushless wound-rotor synchronous starter-generator in the starting mode." Journal of Engineering 2018, no. 13 (January 1, 2018): 581–86. http://dx.doi.org/10.1049/joe.2018.0024.

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34

Zhao, Dan, Weiguo Liu, Ke Shen, Guodong Zhao, and Xin Wang. "Multi-objective optimal design of passive power filter for aircraft starter/generator system application." Journal of Engineering 2018, no. 13 (January 1, 2018): 636–41. http://dx.doi.org/10.1049/joe.2018.0046.

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35

Li, Jincai, Zhuoran Zhang, Jiawei Lu, Hejie Li, and Zhihui Chen. "Investigation and Analysis of a New Shaded-Pole Main Exciter for Aircraft Starter–Generator." IEEE Transactions on Magnetics 53, no. 11 (November 2017): 1–4. http://dx.doi.org/10.1109/tmag.2017.2717942.

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36

Holle, Michael J., Heath E. Misak, Rizwan A. Malik, Ibrahim M. Alarifi, and Ramazan Asmatulu. "Structural analysis and wear behavior of different graphite-based brushes for aircraft starter generator application." Advanced Composites and Hybrid Materials 4, no. 1 (January 8, 2021): 162–72. http://dx.doi.org/10.1007/s42114-020-00200-1.

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37

Kiselev, M. A., F. R. Ismagilov, V. E. Vavilov, D. Yu Pashali, and N. L. Babikova. "An Intelligent Starter–Generator for Power-Supply Systems of Aircraft with Increased Direct-Current Voltage." Russian Electrical Engineering 89, no. 1 (January 2018): 1–4. http://dx.doi.org/10.3103/s1068371218010091.

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38

Balli, Ozgur. "Turbine wheel fracture analysis of Jet Fuel Starter (JFS) engine used on F16 military aircraft." Engineering Failure Analysis 128 (October 2021): 105616. http://dx.doi.org/10.1016/j.engfailanal.2021.105616.

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39

Zhang, Zan, Weiguo Liu, Dongdong Zhao, Shuai Mao, Tao Meng, and Ningfei Jiao. "Steady‐state performance evaluations of three‐phase brushless asynchronous excitation system for aircraft starter/generator." IET Electric Power Applications 10, no. 8 (September 2016): 788–98. http://dx.doi.org/10.1049/iet-epa.2016.0077.

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40

Shoujun, Song, Liu Weiguo, Dieter Peitsch, and Uwe Schaefer. "Detailed Design of a High Speed Switched Reluctance Starter/Generator for More/All Electric Aircraft." Chinese Journal of Aeronautics 23, no. 2 (April 2010): 216–26. http://dx.doi.org/10.1016/s1000-9361(09)60208-9.

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41

Balachandran, Ajith, Mark Boden, Zhigang Sun, Stephen J. Forrest, Jason D. Ede, and Geraint W. Jewell. "Design, construction, and testing of an aero-engine starter-generator for the more-electric aircraft." Journal of Engineering 2019, no. 17 (June 1, 2019): 3474–78. http://dx.doi.org/10.1049/joe.2018.8235.

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42

Буряченко, Анна Григорьевна, Григорий Федорович Цалимов, and Андрей Анатольевич Царев. "СТЕНД-IМIТАТОР СТАРТЕР-ГЕНЕРАТОРА З ФУНКЦІЄЮ ІМІТАЦІЇ РОБОТИ ДВОХ СТАРТЕР-ГЕНЕРАТОРІВ НА СПІЛЬНУ БОРТОВУ МЕРЕЖУ." Aerospace technic and technology, no. 8 (December 25, 2018): 123–27. http://dx.doi.org/10.32620/aktt.2018.8.19.

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Results of development of the specialized test equipment are described. This equipment (developed by specialists of enterprise “Element”) is the stand-simulator which simulates an electric starter-generator of a direct current and is intended for adjustment and testing in laboratory conditions in full parameters and functions of the block of start and generating which is the development of enterprise “Element” too. The basic characteristics of the stand-simulator are shown and experience and results of its application during development, manufacturing and tests the block of start and generating are covered. This stand-simulator is the hardware-software complex simulating the starter-generator as a system which interacts with the block of start and generating by electrical signals interchange. Questions of formation of mathematical model of the starter-generator which has been integrated in the stand-simulator are reflected. Mathematical model was formed as a result of the starter-generator tests with the real aircraft engine and with the block of start and generating. These tests were fulfilled on the engine test bench of specialized enterprise “Motor Sich”. The structure of the stand is given and is described the same way as the input and output electrical signals which are provided by stand-simulator during the process of the block of start and generating adjustment and testing. The special attention is given to a stage of modernization of the stand-simulator with the purpose of maintenance of checking of cross start and alignment of currents of two starter-generators on two-engine aircraft. Two methods of checking of cross start are applied in the stand-simulator. The one of these methods can be called software-method and the second is so-called hardware-method. The hardware-method is close to the real conditions as much as possible. These two methods are described, advantages and disadvantages of each one are illustrated and the conclusion concerning the using both of them is substantiated. The results of the stand-simulator application for block of start and generating tests are verified by the comparison with the results of the real tests of that block with the starter-generator and with the real engine.

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43

Maalouf, A., L. Idkhajine, S. Le Ballois, and E. Monmasson. "Field programmable gate array-based sensorless control of a brushless synchronous starter generator for aircraft application." IET Electric Power Applications 5, no. 1 (2011): 181. http://dx.doi.org/10.1049/iet-epa.2010.0044.

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44

Wang, Bo, Gaurang Vakil, Ye Liu, Tao Yang, Zhuoran Zhang, and Chris Gerada. "Optimization and Analysis of a High Power Density and Fault Tolerant Starter–Generator for Aircraft Application." Energies 14, no. 1 (December 28, 2020): 113. http://dx.doi.org/10.3390/en14010113.

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Permanent magnet synchronous machines provide many dramatic electromagnetic performances such as high efficiency and high power density, which make them more competitive in aircraft electrification, whereas, designing a permanent magnet starter–generator (PMSG), with given consideration to fault tolerance (FT), is a significant challenge and requires great effort. In this paper, a comprehensive FT PMSG design process is proposed which is applied to power systems of turboprops. Firstly, potential slot/pole combinations were selected based on winding factor, harmonic losses and manufacture issues. Then, pursuing high power density, a multiple objective optimization process was carried out to comprehensively rank performances. To meet a fault tolerance target, electrical, magnetic and thermal isolation topologies were investigated and compared, among which 18 slot/12 pole with dual three-phase was selected as the optimal one, with a power density of 7.9 kW/kg. Finally, a finite element analysis verified the performance in normal and post-fault scenarios. The candidate machine has merits concerning high power density and post-fault performance.

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Li, Jincai, Zhuoran Zhang, Jiawei Lu, Ye Liu, and Zhihui Chen. "Design and Characterization of a Single-Phase Main Exciter for Aircraft Wound-Rotor Synchronous Starter–Generator." IEEE Transactions on Magnetics 54, no. 11 (November 2018): 1–5. http://dx.doi.org/10.1109/tmag.2018.2854289.

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46

Jiao, Ningfei, Weiguo Liu, Tao Meng, Chenghao Sun, and Yu Jiang. "Decoupling start control method for aircraft wound‐rotor synchronous starter‐generator based on main field current estimation." IET Electric Power Applications 13, no. 7 (November 14, 2018): 863–70. http://dx.doi.org/10.1049/iet-epa.2018.5140.

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Ismagilov, Flyur, Lev Finkelberg, Viacheslav Vavilov, Ilnar Yamalov, Danis Farrakhov, Alexander Kostyuchenkov, Ildus Sayakhov, Stanislav Baryshnikov, and Egor Pronin. "Integrated Starter-Generator Based on a Brushless DC Machine for the Aircraft Piston Demonstrator Engine APD-500." International Review of Aerospace Engineering (IREASE) 15, no. 4 (August 31, 2022): 232. http://dx.doi.org/10.15866/irease.v15i4.22227.

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48

Sedky, Mohamed M., Wessam E. Abdel-Azim, Ayman S. Abdel-Khalik, and Ahmed M. Massoud. "Integrated Switched Reluctance Starter/Generator for Aerospace Applications: Particle Swarm Optimization for Constant Current and Constant Voltage Control Designs." Applied Sciences 12, no. 15 (July 28, 2022): 7583. http://dx.doi.org/10.3390/app12157583.

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Extensive efforts have been made to develop reliable and efficient onboard generation systems for electric aircraft. Due to the inherited robustness, Switched Reluctance Machines (SRMs) have attracted attention as a promising candidate for an integrated starter/generator in aerospace applications. This paper presents two modes of operation: Constant Current (CC) and Constant Voltage (CV). A Particle Swarm Optimization (PSO)-based tuning approach is employed to optimize the controller of a Switched Reluctance Generator (SRG). The presented controller is evaluated using a three-phase 6/4 SRG. The Control-Hardware-in-the-loop (CHiL) has been used to elucidate the viability of the explored control concept practically.

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Li, Shan Jun, Liang Meng, Qing Jian Meng, Jun Jun Xing, and Yan Lin Zhang. "Control System Construction of Orchard Transport Test Platform Based on PLC." Applied Mechanics and Materials 220-223 (November 2012): 1606–10. http://dx.doi.org/10.4028/www.scientific.net/amm.220-223.1606.

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In order to solve the problems about testing and analysis for the optimization problem of the mountain orchards transport aircraft operating parameters and structural parameters, we build a transport aircraft control test platform. According to actual needs, for complete the circuit design,select the appropriate frequency conversion motor, frequency converter, PLC, and other critical hardware.Using fuzzy PI controller, in the Step-7 authoring environment to compile, complete the PLC programming design; Complete interface design in the in Eviews editing software EV500.After constantly adjust, in conditions for a variety of conditions like stoping in an emergency, an emergency starter, speed transient change, instantaneous change of goods bias, cargo rolling random, the system can be stable operation, uniform speed, experimental platform vibration is very small, the vibration of the truck itself is also very small,which can meet the test requirements enoughly.

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Popov, Grigory, Vasily Zubanov, Valeriy Matveev, Oleg Baturin, and Anastasia Korneeva. "Method of coordinating air starter and auxiliary power unit joint operation." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 63 (2020): 5–13. http://dx.doi.org/10.15593/2224-9982/2020.63.01.

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The presented work provides a detailed description of the method developed by the authors for coordinating the working process of the main elements of the starting system for a modern gas turbine engine for a civil aviation aircraft: an auxiliary power unit (APU) and an air turbine – starter. This technique was developed in the course of solving the practical problem of selecting the existing APU and air turbine for a newly created engine. The need to develop this method is due to the lack of recommendations on the coordination of the elements of the starting system in the available literature. The method is based on combining the characteristics of the APU and the turbine, reduced to a single coordinate system. The intersection of the characteristic’s lines corresponding to the same conditions indicates the possibility of joint operation of the specified elements. The lack of intersection indicates the impossibility of joint functioning. The calculation also takes into account losses in the air supply lines to the turbine. The use of the developed method makes it possible to assess the possibility of joint operation of the APU and the air turbine in any operating mode. In addition to checking the possibility of functioning, as a result of the calculation, specific parameters of the working process at the operating point are determined, which are then used as initial data in calculating the elements of the starting system, for example, determining the parameters of the turbine, which in turn allow providing initial information for calculating the starting time or the possibility of functioning of the starting system GTE according to strength and other criteria. The algorithm for calculating the start-up time of the gas turbine engine was also developed by the authors and implemented in the form of an original computer program. Keywords: gas turbine engine start-up, GTE starting system, air turbine, methodology, joint work, auxiliary power unit, power, start-up time, characteristics matching, coordination, operational characteristics, computer program.

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