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Journal articles on the topic 'Aerodynamic balancing'

Author: Grafiati
Published: 4 June 2025
Last updated: 1 August 2025

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1

Gennadiy, Filimonikhin, Filimonikhina Irina, Bilyk Yuliia, Krivoblotsky Larisa, and Machok Yurii. "Theoretical study into the aerodynamic imbalance of a propeller blade and the correcting masses to balance it." Eastern-European Journal of Enterprise Technologies 4, no. 7 (112) (2021): 60–66. https://doi.org/10.15587/1729-4061.2021.238289.

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This paper reports the theoretically investigated aerodynamic imbalance of the propeller blade, as well as correcting masses for balancing it. It has been established that the aerodynamic forces acting on the propeller blade can be balanced by the adjustment of masses. This is also true for the case of compressed air (gas) provided that the blades are streamlined by laminar flow. That makes it possible to use rotor balancing methods to study the aerodynamic forces acting on the propeller blade. The rotating blade mainly generates torque aerodynamic imbalance due to a lift force. A much smaller
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2

Filimonikhin, Gennadiy, Irina Filimonikhina, Yuliia Bilyk, Larisa Krivoblotsky, and Yurii Machok. "Theoretical study into the aerodynamic imbalance of a propeller blade and the correcting masses to balance it." Eastern-European Journal of Enterprise Technologies 4, no. 7(112) (2021): 60–66. http://dx.doi.org/10.15587/1729-4061.2021.238289.

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This paper reports the theoretically investigated aerodynamic imbalance of the propeller blade, as well as correcting masses for balancing it. It has been established that the aerodynamic forces acting on the propeller blade can be balanced by the adjustment of masses. This is also true for the case of compressed air (gas) provided that the blades are streamlined by laminar flow. That makes it possible to use rotor balancing methods to study the aerodynamic forces acting on the propeller blade. The rotating blade mainly generates torque aerodynamic imbalance due to a lift force. A much smaller
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3

Чмовж, В. В., К. В. Скомаровський та В. О. Захаренко. "СУМІСНА СХЕМА РОЗРАХУНКУ АЕРОДИНАМІЧНИХ ХАРАКТЕРИСТИК ГЕЛІКОПТЕРА З ОДНИМ НЕСУЧИМ ГВИНТОМ". Open Information and Computer Integrated Technologies, № 103 (1 травня 2025): 85–99. https://doi.org/10.32620/oikit.2025.103.07.

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For a helicopter, interaction with the environment plays a more significant role than for an airplane, because during interaction the geometry of the helicopter changes (the change is largely related to the position of the blades relative to the main rotor hub). In turn, the movement of the blades causes a change in the forces acting on the blades. The aerodynamic forces acting on the articulated blade become dependent not only on the movement of the helicopter, but also on the movement of the blade relative to the hub. The aerodynamic characteristics of the main rotor, and therefore the helic
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Mandel, Savannah. "Aerodynamic vs. acoustic performance: a balancing act." Scilight 2019, no. 43 (2019): 431103. http://dx.doi.org/10.1063/10.0000196.

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Lutsenko, A. Y., D. K. Nazarova, and D. M. Slobodyanyuk. "A Study of the Aerodynamic Characteristics of the Rocket Fairing Door Using Conical Means of Passive Stabilization." Proceedings of Higher Educational Institutions. Маchine Building, no. 7 (712) (July 2019): 66–75. http://dx.doi.org/10.18698/0536-1044-2019-7-66-75.

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In the article, the aerodynamic characteristics of a detachable fairing door model are investigated with the use of passive stabilization means, which are conical bodies with flexible and rigid connections. Two types of experiments were conducted in a subsonic wind tunnel to determine the balancing angles of attack: a visualization experiment (using a video camera) and a measuring experiment (using the angle sensor). Mathematical flow models and aerodynamic quality values were obtained. The change in the balancing angle of attack and the corresponding aerodynamic quality of the studied combina
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Bilous, Illya, Illya Kryvohatko, and Yurii Yakovlev. "Methodology for calculating the efficiency of the rudders of the tandem aircraft." MECHANICS OF GYROSCOPIC SYSTEMS, no. 40 (December 26, 2021): 11–21. http://dx.doi.org/10.20535/0203-3771402020248733.

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As of recent rapid development in the field of UAVs, unusual aerodynamic practices can be used, for example, the tandem scheme. In early planning stages, it’s important to evaluate aerodynamic characteristics of the chosen scheme and to approximate its balancing losses, as it impacts the stability and controllability of the craft.
 The most effective way of aerodynamic characteristics analysis is done using wind tunnels. However, it requires considerable investments in both financial terms and time, when designing the model, conducting the experiment and processing the results. Because of
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7

Silvestrov, Anton, Mykola Ostroverkhov, and Liudmyla Spinul. "Solution of the Problem of Identification of Aerodynamic Coefficients of Aircraft According to the Data of Their Full-Scale Tests." Electronics and Control Systems 2, no. 80 (2024): 28–35. http://dx.doi.org/10.18372/1990-5548.80.18681.

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The methodology of the correct identification of the aerodynamic coefficients of the aircraft is considered, namely the determination of the partial derivatives of the aerodynamic forces and moments of the aircraft according to its state variables. The method of determining static (balancing) dependencies from short-term dynamic modes of a natural experiment is also presented. The effectiveness of the proposed approach is confirmed by the practice of determining the aerodynamic coefficients and aerodynamic characteristics of various aircraft.
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Kapitanova, Liudmyla, Viktor Riabkov та Danylo Kirnoson. "Забезпечення статичного балансування легкого транспортного літака під час зміни його маршових двигунів". Aerospace Technic and Technology, № 6 (6 грудня 2023): 28–37. http://dx.doi.org/10.32620/aktt.2023.6.04.

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The process of improving the existing aircraft fleet through the development of modifications has become widespread in both domestic and foreign aircraft manufacturing. Under modern conditions, no country in the world is capable of simultaneously modernizing all types of aircraft. Economic and scientific-technical resources are usually directed toward developing those types for which there is the greatest demand. Limiting the number of types in conjunction with developing modifications for existing aircraft significantly contributes to increasing the efficiency of the entire air transport syst
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Yuan, Chengen, Dongli Ma, Yuhong Jia, and Liang Zhang. "Stealth Unmanned Aerial Vehicle Penetration Efficiency Optimization Based on Radar Detection Probability Model." Aerospace 11, no. 7 (2024): 561. http://dx.doi.org/10.3390/aerospace11070561.

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Aerodynamic/stealth optimization is a key issue during the design of a stealth UAV. Balancing the weight of different incident angles of the RCS and combining stealth characteristics with aerodynamic characteristics are hotspots of aerodynamic/stealth optimization. To address this issue, this paper introduces a radar detection probability model to solve the weight balance problem of incident angles of the RCS and a penetration efficiency model to transfer the multi-object optimization into single-objective optimization. In this paper, a parameterized model of a flying-wing UAV is selected as t
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10

Ding, Zekun. "Impact of Wing Aspect Ratio on Aerodynamic Performance in Gliding Flight: A Comprehensive Review." Highlights in Science, Engineering and Technology 119 (December 11, 2024): 867–71. https://doi.org/10.54097/8p1hg461.

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The aspect ratio of a wing plays a critical role in determining the aerodynamic performance of gliding flight. As a key design parameter, the aspect ratio influences lift, drag, and overall efficiency, making it essential for optimizing flight characteristics. This review explores the theoretical foundations of aerodynamics, focusing on the interplay between lift, drag, and the glide angle, and highlights the significance of the lift-to-drag ratio as a measure of aerodynamic efficiency. A detailed examination of the role of aspect ratio reveals its impact on aerodynamic properties, supported b
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11

Taghipour, Javad, Jiaying Zhang, Alexander D. Shaw, Mike I. Friswell, Huayuan Gu, and Chen Wang. "Resonant passive energy balancing of morphing helicopter blades with bend–twist coupling." Nonlinear Dynamics 107, no. 1 (2021): 617–39. http://dx.doi.org/10.1007/s11071-021-07067-x.

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AbstractWith increasing demand for rotor blades in engineering applications, improving the performance of such structures using morphing blades has received considerable attention. Resonant passive energy balancing (RPEB) is a relatively new concept introduced to minimize the required actuation energy. This study investigates RPEB in morphing helicopter blades with lag–twist coupling. The structure of a rotating blade with a moving mass at the tip is considered under aerodynamic loading. To this end, a three-degree-of-freedom (3DOF) reduced-order model is used to analyse and understand the com
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12

Montgomery, John, and Robert Haynes. "A Novel Approach to the Dynamic Balancing of Spun/De-spun Spacecraft." Journal of the IEST 48, no. 1 (2005): 12–20. http://dx.doi.org/10.17764/jiet.48.1.u83544726q39470v.

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In response to challenges encountered in the dynamic balancing of the Windsat instrument, a novel approach to dynamic balancing of dual-spin spacecraft was developed. The Windsat instrument is a 675-lb microwave radiometer consisting of a small, 200-lb stationary module topped by a large rotating truss structure approximately nine feet in height. A 72-in.-diameter reflector atop the truss, designed to direct microwave energy into the Windsat radiometer, was a significant source of aerodynamic lift and drag during spin balance testing. The approach developed in this study allows the spacecraft
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13

Karpukhin, K. E., and PabloItturalde Iturralde Bakero. "Aerodynamics as a Method of Improvement of Stability and Balancing of Weight Distribution for a Formula SAE Car." Izvestiya MGTU MAMI 4, no. 1 (2010): 19–22. http://dx.doi.org/10.17816/2074-0530-69530.

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The article considers questions of aerodynamic research for the purpose of improvement of stability and balancing of weight distribution for a car of the Formula SAE type. The authors give concrete examples on the described researches.
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14

Ahmed, Abdul Mateen Manzoor, B. Vamshi Krishna, and D. Manoj. "Advancements In UAV Wing Design: Aerodynamic Performance, Structural Integrity And Optimization Techniques." IOSR Journal of Mechanical and Civil Engineering 21, no. 6 (2024): 34–37. http://dx.doi.org/10.9790/1684-2106013437.

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The aerodynamic performance and optimization of unmanned aerial vehicles (UAVs) have garnered significant research interest, driven by the need for enhanced efficiency, stability, and adaptability in various flight conditions. This paper reviews current research on UAV wing configurations, focusing on aerodynamic optimization, structural integrity, and computational fluid dynamics (CFD) analysis. Studies on innovative wing designs, such as blended-wing-body and fixed-wing configurations, demonstrate improvements in lift, drag, and maneuverability through precise airfoil selection and wing para
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15

Cacciola, S., C. E. D. Riboldi, and A. Croce. "Monitoring rotor aerodynamic and mass imbalances through a self-balancing control." Journal of Physics: Conference Series 1037 (June 2018): 032041. http://dx.doi.org/10.1088/1742-6596/1037/3/032041.

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16

Kudashov, E. V., I. A. Grachev, and M. A. Bolotov. "Methodology for assessing and reducing the aerodynamic imbalance of the impellers of GTE fans." VESTNIK of Samara University. Aerospace and Mechanical Engineering 22, no. 1 (2023): 85–97. http://dx.doi.org/10.18287/2541-7533-2023-22-1-85-97.

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The reasons for the occurrence of increased vibration of the engine rotor due to aerodynamic imbalance of the fan of the first stage of the impeller are determined. A method for estimating the aerodynamic imbalance of the gas turbine engine fan is proposed, taking into account the influence of the following factors: geometric errors in the manufacture of blade airfoils and their positioning in the disk; deformation of the blade airfoil during the assembly of the impeller, as well as the factors of the working process occurring in the impeller. The use of the technique makes it possible to eval
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17

Silva, Lucilene, Tomas Grönstedt, Carlos Xisto, Luiz Whitacker, Cleverson Bringhenti, and Marcus Lejon. "Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance." Aerospace 11, no. 4 (2024): 276. http://dx.doi.org/10.3390/aerospace11040276.

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The ratio between blade height and chord, named the aspect ratio (AR), plays an important role in compressor aerodynamic design. Once selected, it influences stage performance, blade losses and the stage stability margin. The choice of the design AR involves both aerodynamic and mechanical considerations, and an aim is frequently to achieve the desired operating range while maximizing efficiency. For a fixed set of aerodynamic and geometric parameters, there will be an optimal choice of AR that achieves a maximum efficiency. However, for a state-of-the-art aero-engine design, optimality means
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18

Xiang, Yu Hua, Jia Yuan Zhang, and Xiao Hui Zhang. "Research of Cold Test in 170t/h Tangentially Fired Boiler." Advanced Materials Research 516-517 (May 2012): 180–86. http://dx.doi.org/10.4028/www.scientific.net/amr.516-517.180.

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The characteristics of the WGZ170/9.8-3 pulverized coal boiler were obtained based on cold test，Including the air velocity distribution in tangential firing boiler and the relation between air distribution with opening of each secondary air dampe，The test results had determined that the baffle of blower at around 40% and two parallel draft fan about 45% were relatively appropriate. and the air distribution and opening of each secondary air dampe and balancing the distribution of primary air and second air along the width direction of the boiler hearth were confirmed through test，and the aerody
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19

IJRAME, Journal. "Shape Optimization in Low-Observable Aerodynamic Design." International Journal of Research in Aeronautical and Mechanical Engineering 12, no. 9 (2024): 15–28. https://doi.org/10.5281/zenodo.13829005.

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This research explores the development of airfoils optimized for low-observable aerodynamic applications, balancing stealth characteristics with aerodynamic performance. A comprehensive analysis of over 100 NACA airfoils identified NACA 2412 and NACA 0012 as the optimal choice due to its favorable radar cross-section (RCS) and high lift-to-drag ratio (L/D), essential for subsonic efficiency. Initial aero-dynamic evaluations using XFLR5 supported the NACA 0012 2412’s performance, aligning with previous findings (Li et al., 2016; Ander- son, 2011). Detailed CFD simulations with ANSYS Fluen
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20

Olijnichenko, Lubov, Gennadiy Filimonikhin, Andrey Nevdakha, and Vladimir Pirogov. "Patterns in change and balancing of aerodynamic imbalance of the low­pressure axial fan impeller." Eastern-European Journal of Enterprise Technologies 3, no. 7 (93) (2018): 71–81. http://dx.doi.org/10.15587/1729-4061.2018.133105.

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21

Ameduri, Salvatore. "A SMA Based Morphing Leading Edge Architecture." Advanced Materials Research 1016 (August 2014): 383–88. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.383.

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This paper analyses a morphing leading edge device, activated by a Shape Memory Alloy (SMA) actuator. The objective is to achieve the Droop Nose effect for particular phases of the flight (e.g. take-off, landing), both obtaining an increased lift and preserving the laminar flow. The device is constituted of: a kinematic chain at the level of the wing section, transmitting motion to the skin, this way fitting the Droop Nose target shape; a span-wise architecture integrated with a SMA actuator, ensuring both a reduction of the actuation forces and the balancing of the aerodynamic external load.
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22

Dolgov, Oleg, Sergey Bibikov, and Irina Pocebneva. "Elements of the synthesis method for the layout of a front-line aircraft." E3S Web of Conferences 110 (2019): 01068. http://dx.doi.org/10.1051/e3sconf/201911001068.

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The article describes a technique that allows to form a planned projection of the aircraft using the minimum number of iterations (refinements based on aerodynamic and weight calculations results). The elements of the technique are described via example of the development (synthesis) of the layout scheme of a front-line aircraft with two engines and internal cargo compartments, performed according to the normal balancing scheme. Synthesis is carried out on the basis of certain predesign parameters, limitations, as well as solutions set by the designer, based on the analysis of parametric ratio
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23

Urbiola-Soto, Leonardo, and Marcelo Lopez-Parra. "Liquid Self-Balancing Device Effects on Flexible Rotor Stability." Shock and Vibration 20, no. 1 (2013): 109–21. http://dx.doi.org/10.1155/2013/742163.

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Nearly a century ago, the liquid self-balancing device was first introduced by M. LeBlanc for passive balancing of turbine rotors. Although of common use in many types or rotating machines nowadays, little information is available on the unbalance response and stability characteristics of this device. Experimental fluid flow visualization evidences that radial and traverse circulatory waves arise due to the interaction of the fluid backward rotation and the baffle boards within the self-balancer annular cavity. The otherwise destabilizing force induced by trapped fluids in hollow rotors, becom
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Gnepie-Takam, Nicolas, Choupo Yuego, Tientcheu-Nsiewe Max-well, Balbine Matuam Tamdem, and Kuitche Alexis. "Enhanced wind turbine blade design for improved power output and reduced noise." MJ Engineering Sciences 1, no. 1 (2025): 31–48. https://doi.org/10.63156/mjes03.

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Current wind turbine optimization studies primarily employ either the Blade Element Method (BEM) or Computational Fluid Dynamics (CFD) to evaluate rotor aerodynamic performance. While BEM remains widely used due to its simplicity and low computational cost, it depends heavily on empirical correction factors that can limit its accuracy in complex flow conditions. Conversely, although CFD provides highly accurate results by solving the Navier-Stokes equations, it is computationally expensive and often impractical for large-scale parametric studies. Vortex methods—particularly the prescribed wake
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Singh, Jobanpreet. "Advancements in Understanding and Mitigating Shock Wave Boundary Layer Interaction (SWBLI) Effects on Hypersonic Airfoil Performance: A Comprehensive Review." FMDB Transactions on Sustainable Energy Sequence 2, no. 2 (2024): 102–9. https://doi.org/10.69888/ftses.2024.000310.

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Complex aerodynamic processes like Shock Wave Boundary Layer Interaction (SWBLI) affect hypersonic vehicle efficiency and safety. This comprehensive research examines SWBLI's effects on hypersonic aerofoil performance, revealing new causes and mitigating methods. This study begins with SWBLI concepts and how the boundary layer moves with flow and compression shock waves interacting with the aerofoil. We concentrate on crucial techniques for surprise wave diffraction, reflected image, and turbulent boundary layer interaction on hypersonic aerofoils. Research simulates SWBLI incidents using turb
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26

Fan, Linhao. "Levitational Dynamics: Analyzing the Performance of Lightweight Objects over a Vertical Jet." Highlights in Science, Engineering and Technology 119 (December 11, 2024): 432–43. https://doi.org/10.54097/rhfxcn71.

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This paper explores the phenomenon of aerodynamic levitation, concentrating on the performance of various lightweight objects as they are positioned over a vertical air jet emitted by a standard household hair dryer. The study meticulously analyzes levitation, which is achieved by balancing gravitational pull with aerodynamic forces that act counteractively, utilizing objects of different masses, volumes, and geometric shapes. The experimental framework is crafted using easily accessible household items, which include a hair dryer for generating air jets and various lightweight objects. The pr
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27

Loginov, Vasyl, Yevgen Ukrainets, Viktor Popov, and Yevgen Spirkin. "Determining the Aerodynamic Characteristics of a Propeller-Driven Anti-UAV Fighter While Designing Air Propellers." Transactions on Aerospace Research 2021, no. 4 (2021): 53–67. http://dx.doi.org/10.2478/tar-2021-0023.

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Abstract Given the rising importance of unmanned aerial vehicles (UAVs), this article addresses the urgent scientific problem of determining the aerodynamic characteristics of a UAV while laying out the propellers for the wings. We discuss the methodology for experimental wind-tunnel studies of aircraft configurations with propellers. It is shown that a characteristic feature of the configuration small-elongation wing with propellers is the absence of elements that are not affected by propellers. This feature makes it difficult to implement and automate a wind tunnel experiment, since there ar
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28

S, Shivani, Amar Murthy A, and Srinivas G. "Aerodynamic performance enhancement of centrifugal compressor using numerical techniques." F1000Research 13 (May 17, 2024): 480. http://dx.doi.org/10.12688/f1000research.145060.1.

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Background Centrifugal compressors are dynamic machines utilizing a rotating impeller, efficiently accelerate incoming gases, transforming kinetic energy into pressure energy for compression. They serve a wide range of industries, including air conditioning, refrigeration, gas turbines, industrial processes, and applications such as air compression, gas transportation, and petrochemicals, demonstrating their versatility. Designing a centrifugal compressor poses challenges related to achieving high aerodynamic efficiency, surge and choke control, material selection, rotor dynamics, cavitation,
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29

Lopuhov, A. V. "An improved combined method of creating control forces and moments for an unmanned aerialvehicle." «System analysis and applied information science», no. 1 (June 8, 2022): 27–33. http://dx.doi.org/10.21122/2309-4923-2022-1-27-33.

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improved combined (aerodynamic and gas-dynamic) method of creating control forces and moments.The objectives of the study are to analyze the basic model of the combined control method and the possibility of using an improved model of the combined control method, at which the invariability of the mass and dimensional characteristics of the upgraded control object will be achieved with a simultaneous increase in the target quality (reduction of the final miss).Research is based on the use of an improved method for creating control forces and moments, where the optimization of mass characteristic
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30

Hancock, Rebecca. "Management of Functional Aphonia and Related Severe Muscle Tension Disorders: A Practical Approach with Historical Underpinnings." Perspectives on Voice and Voice Disorders 24, no. 2 (2014): 55–63. http://dx.doi.org/10.1044/vvd24.2.55.

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Management of functional aphonia and severe muscle tension dysphonia requires a skilled and flexible treatment approach. Key components of management include accurate diagnosis, clinical probing, and targeting underlying physiological processes inherent in voice production. Diagnostic factors include laryngeal imaging, acoustic and aerodynamic testing (when appropriate), as well as perceptual and therapeutic potential assessment. This article explores historical management techniques in the context of modern approaches, demonstrating management approaches that focus on balancing respiration an
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31

Sirenko, V. N., А. S. Levin, I. V. Mashtak, and А. D. Sheptun. "Terminal guidance of the aircraft being maneuvering while descending in the atmosphere under conditions of aerodynamic balancing." Kosmičeskaâ tehnika. Raketnoe vooruženie 2020, no. 1 (2020): 34–43. http://dx.doi.org/10.33136/stma2020.01.034.

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Karali, Hasan, Gokhan Inalhan, and Antonios Tsourdos. "Advanced UAV Design Optimization Through Deep Learning-Based Surrogate Models." Aerospace 11, no. 8 (2024): 669. http://dx.doi.org/10.3390/aerospace11080669.

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The conceptual design of unmanned aerial vehicles (UAVs) presents significant multidisciplinary challenges requiring the optimization of aerodynamic and structural performance, stealth, and propulsion efficiency. This work addresses these challenges by integrating deep neural networks with a multiobjective genetic algorithm to optimize UAV configurations. The proposed framework enables a comprehensive evaluation of design alternatives by estimating key performance metrics required for different operational requirements. The design process resulted in a significant improvement in computational
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Ye, Bobo, Juan Li, Jie Li, Chang Liu, Ziyi Wang, and Yachao Yang. "Computational Fluid Dynamics (CFD)-Enhanced Dynamic Derivative Engineering Calculation Method of Tandem-Wing Unmanned Aerial Vehicles (UAVs)." Drones 9, no. 4 (2025): 231. https://doi.org/10.3390/drones9040231.

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Dynamic derivatives are critical for evaluating an aircraft’s aerodynamic characteristics, dynamic modeling, and control system design during the design phase. However, due to the multiple iterations of the design phase, a method for calculating dynamic derivatives that balances computational efficiency and accuracy is required. This work presents a CFD-enhanced engineering calculation method (CEHM) for calculating tandem-wing UAVs’ dynamic derivatives. A coupling-effect-driven estimation strategy is proposed to incorporate the contribution of the rear wing to the longitudinal dynamic derivati
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34

Филимонихин, Геннадий Борисович, and Любовь Сергеевна Олийниченко. "Investigation of the possibility of balancing aerodynamic imbalance of the impeller of the axial fan by correction of masses." Eastern-European Journal of Enterprise Technologies 5, no. 7(77) (2015): 30. http://dx.doi.org/10.15587/1729-4061.2015.51195.

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35

Takovitskii, S. A. "On the role of a balancing load in the problem of aerodynamic drag minimization in the supersonic flight regime." Fluid Dynamics 49, no. 2 (2014): 238–48. http://dx.doi.org/10.1134/s0015462814020124.

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36

Qiao, Nanxuan, Tielin Ma, Jingcheng Fu, Ligang Zhang, Xiangsheng Wang, and Pu Xue. "Rapid Blade Shape Optimization for Contra-Rotating Propellers for eVTOL Aircraft Considering the Aerodynamic Interference." Aerospace 10, no. 1 (2023): 54. http://dx.doi.org/10.3390/aerospace10010054.

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The rising interest in the evolvability of electric vertical takeoff and landing (eVTOL) promises substantial potential in the field of urban air mobility (UAM). Challenges in energy storage density and geometry restriction both emphasize the propeller efficiency for endurance and takeoff weight, whereas the contra-rotating propellers (CRP) advantage is balancing high thrust and efficiency over a single propeller. The aim of this paper is twofold: (i) to present a novel rapid CRP blade shape optimization framework and (ii) to study the impact of the dual propellers revolution speed allocations
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37

Boriak, K. F., S. V. Lienkov, O. A. Nazarenko, and O. V. Sieliukov. "IMPROVEMENT IN QUALITY OF MANUFACTURING THE LARGE-CALIBER ARTILLERY PROJECTILES (122, 152, 155) FOR GUNS WITH A RIFLED TUBE." Collection of scientific works of the Military Institute of Kyiv National Taras Shevchenko University, no. 78 (2023): 7–17. http://dx.doi.org/10.17721/2519-481x/2023/78-01.

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An analysis of the technique of manufacturing the large-caliber artillery projectiles (122, 152,155 mm) on modern screw-cutting lathes was carried out taking into account normalized tolerances for metalworking of the projectile components in accordance with international standards in force. It has been established that regardless of the qualifications of the personnel and the use of modern machines in compliance with the requirements of international standards for metalworking, the quality of projectiles from one batch can differ significantly in the value of drift. The reason for the drift of
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Wang, Chunyang, Zhou Zhou, and Rui Wang. "Research on Dynamic Modeling and Transition Flight Strategy of VTOL UAV." Applied Sciences 9, no. 22 (2019): 4937. http://dx.doi.org/10.3390/app9224937.

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A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) can meet both VTOL and horizontal flight performance, but how to achieve a safe and stable transition is a research focus of this type of aircraft. According to the overall configuration characteristics of VTOL UAV, aerodynamic models of lift fan, lift duct and induced wing surface of VTOL UAV were established. Three flight modes of induced VTOL UAV are studied, including hover, transition and horizontal flight. The method of longitudinal flight balance of UAV in transition mode is also studied. Finally, a UAV is taken as an
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39

Lehmann, Fritz-Olaf, Dimitri A. Skandalis, and Ruben Berthé. "Calcium signalling indicates bilateral power balancing in the Drosophila flight muscle during manoeuvring flight." Journal of The Royal Society Interface 10, no. 82 (2013): 20121050. http://dx.doi.org/10.1098/rsif.2012.1050.

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Manoeuvring flight in animals requires precise adjustments of mechanical power output produced by the flight musculature. In many insects such as fruit flies, power generation is most likely varied by altering stretch-activated tension, that is set by sarcoplasmic calcium levels. The muscles reside in a thoracic shell that simultaneously drives both wings during wing flapping. Using a genetically expressed muscle calcium indicator, we here demonstrate in vivo the ability of this animal to bilaterally adjust its calcium activation to the mechanical power output required to sustain aerodynamic c
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40

Mikhailov, Evgenii, and Viktor Fedorov. "EXTERNAL AND INTERNAL MECHANICS OF THE AIRCRAFT WITH THE SYSTEM OF DISPLACEMENT OF THE CENTER OF MASS." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 70 (2022): 18–28. http://dx.doi.org/10.15593/2224-9982/2022.70.02.

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Axisymmetric aircraft can be adversely affected by asymmetries of various types, such as mass asymmetry, aerodynamic and combinations thereof. This influence can manifest itself in off-design modes of motion, increased overloads, and trajectory deviation. On the other hand, the deliberate introduction of asymmetry, in particular mass asymmetry, can compensate for the neg-ative impact of both mass-inertial and aerodynamic asymmetries, and will also allow the creation of aerodynamic forces for spatial maneuvering. This can be implemented using the center of mass displacement system installed on
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41

Sit, Mihail, and Anatoliy Juravliov. "Hybrid Carbon Dioxide Heat Pump for the Multifamily Residential Buildings in the Heat Supply System Based on CHP." Problems of the Regional Energetics, no. 3(51) (August 2021): 91–98. http://dx.doi.org/10.52254/1857-0070.2021.3-51.08.

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The work is devoted to centralized heat supply systems based on CHP plants and the use with them heat pumps (HP) on carbon dioxide as refrigerant. Heat pumps are used in heat supply systems for buildings and use the heat of the outside air and, at the same time, the heat of the return network water (WWR) as a source of low-grade heat (LHP). The aim of the study is to develop a structural diagram of such a heat pump, where the outside air is heated by a heat exchanger installed in the return water line of the heating system, to develop a hydraulic circuit of a heat pump taking into account the
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42

Kuprikov, Mikhail, Leonid Ponyaev, and Nikita Kuprikov. "DECREASE OF SOUND PRESSURE LEVEL AND NOISE INSIDE HYBRID ELECTRIC WING BODY PLANES AND DIRIDGABLES." Akustika 34 (November 1, 2019): 170–73. http://dx.doi.org/10.36336/akustika201934170.

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The analysis of the find Optimal Structure of the Large Aircraft and Airship for decrease of Sound/Noise Pressure Level inside and outside the Cabin Saloon are very actually today for Worldwide Ecology Program. The Method of Aircraft layout from the virtual mass center is given, which allows us to obtain the Aircraft layout from the conditions of Infrastructural Constraints in the terminal configurations of the Modern Air Transportation Infrastructure and IATA/ICAO Regulation. A Method is proposed for the synthesis of new circuit solutions for an Aircraft passenger compartment and may be use t
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43

Kumar, A., S. C. Sati, and A. K. Ghosh. "Design, Testing, and Realisation of a Medium Size Aerostat Envelope." Defence Science Journal 66, no. 2 (2016): 93. http://dx.doi.org/10.14429/dsj.66.9291.

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<p>The design, testing and realisation aspects during the development of a medium size aerostat envelope in the present work. The payload capacity of this aerostat is 300 kg at 1 km above mean sea level. The aerostat envelope is the aerodynamically shaped fabric enclosure part of the aerostat which generally uses helium for lifting useful payloads to a specified height. The envelope volume estimation technique is discussed which provides the basis for sizing. The design, material selection, testing and realisation aspects of this aerostat envelope are also discussed. The empirical formul
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44

Aljuhaishi, Saif, Yaseen K. Al-Timimi, and Basim I. Wahab. "Comparing Turbulence Models for CFD Simulation of UAV Flight in a Wind Tunnel Experiments." Periodica Polytechnica Transportation Engineering 52, no. 3 (2024): 301–9. http://dx.doi.org/10.3311/pptr.24004.

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Wind tunnel tests are costly and time-consuming, and the accuracy of the tests is limited by the size of the tunnel, to solve this problem, researchers use computational fluid dynamics (CFD) to conduct wind tunnel experiments using a computer because it is less timely and less costly. Computerized testing of drone's models using wind tunnel experiment simulation in computational fluid dynamic (CFD) software requires knowledge of the most suitable turbulence model for this drone. In this paper ANSYS fluent program has been used to test four most common turbulence models for use (Spalart-Allmara
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Pinto, Joseph Ciano, Siva Marimuthu, Parvathy Rajendran, Manikandan Natarajan, and Rajadurai Murugesan. "Computational Analysis of Blended Winglet Designs to Reduce the Wake Turbulence on the Airbus A380 Wingtip." Eng 6, no. 4 (2025): 68. https://doi.org/10.3390/eng6040068.

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The aviation sector faces a significant challenge in balancing the rising demand for air travel with the need to reduce its environmental impact. Because air travel accounts for approximately 2.5% of global carbon emissions, there is a need to find sustainable solutions to reduce its environmental impact. Improving aerodynamic performance is a crucial area for reducing fuel consumption and emissions. Nowadays, more focus is given to commercial aviation, which contributes to global aviation emissions. The A380 is the largest passenger aircraft in the world at the moment. It was observed in real
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46

L, Ponyaev. "Optimal Design of Green Tech Hybrid Electric Integrated Aircraft and Solar Disk Airships for Short Arctic Air Transport Corridors." Environmental Sciences and Ecology: Current Research (ESECR 2, no. 6 (2021): 1–4. http://dx.doi.org/10.54026/esecr/1036.

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The Ecology Decarburization issues decision may focus priority to the complex Design Analysis of the more Optimal Structure of the Large E-Aircraft and E-Airship for decrease of the Weight and Engine Power with Hybrid Electric Propulsion (HEP) systems are very actually today for Worldwide Ecology Program. The Method of Aircraft layout from the virtual mass center is given, which allows us to obtain the Aircraft layout from the conditions of Infrastructural Constraints in the terminal configurations of the Modern Air Transportation Infrastructure and IATA/ICAO Regulation. Calculate Method is pr
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47

Zhang, Xu, Haiquan Bi, Honglin Wang, et al. "A Mathematical Method for Predicting Tunnel Pressure Waves Based on Train Wave Signature and Graph Theory." Mathematics 13, no. 15 (2025): 2360. https://doi.org/10.3390/math13152360.

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Previous research has demonstrated that the Train Wave Signature (TWS) method enables rapid calculation of pressure waves in straight tunnels. However, its application to subway tunnels with complex structural features remains insufficiently explored. This study proposes a generalized mathematical method integrating TWS with graph theory for the simulation of pressure wave generation, propagation, and reflection in complex tunnel systems. A computational program is implemented using this method for efficient simulation. The proposed method achieves high-accuracy prediction of pressure waves in
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48

Keane, A. J., and J. P. Scanlan. "Design search and optimization in aerospace engineering." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 365, no. 1859 (2007): 2501–29. http://dx.doi.org/10.1098/rsta.2007.2019.

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In this paper, we take a design-led perspective on the use of computational tools in the aerospace sector. We briefly review the current state-of-the-art in design search and optimization (DSO) as applied to problems from aerospace engineering, focusing on those problems that make heavy use of computational fluid dynamics (CFD). This ranges over issues of representation, optimization problem formulation and computational modelling. We then follow this with a multi-objective, multi-disciplinary example of DSO applied to civil aircraft wing design, an area where this kind of approach is becoming
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Mr., Kothara Srinivasa Rao*1 Dr.A.Gopalakrishna 2. "NEURAL NETWORKS FOR ROTOR TRACK AND BALANCE OF HELICOPTER." INTERNATIONAL JOURNAL OF ENGINEERING SCIENCES & RESEARCH TECHNOLOGY 9, no. 5 (2020): 162–72. https://doi.org/10.5281/zenodo.3865858.

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Rotor Track & Balance (RTB) process is performed to bring the Vibrations to acceptable limits in identified steady flight regimes of a helicopter. Vibrations at 1/rev (1P, 1R) manifests due to mass differences between the Main Rotor blades and differences in aerodynamic forces on the blades. The process of correcting the mass differences between the blades (in plane vibrations) and the aerodynamic forces (out of plane vibrations) of the blades is called the Rotor Tracking and Balancing process. The RTB process can be optimised using Artificial Neural Networks. Number of vibration flights w
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SUN, Ying, Mikhail Yu KUPRIKOV, and Elena L. KUZNETSOVA. "Effect of flight range on the dimension of the main aircraft." INCAS BULLETIN 12, S (2020): 201–9. http://dx.doi.org/10.13111/2066-8201.2020.12.s.19.

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The purpose of the article is to analyze the characteristics of aircraft, including aircraft of the Boeing and Airbus families, as well as to highlight the factors affecting the flight range depending on the dimension of the main aircraft. The possibilities of competition with Boeing and Airbus were considered and options for solving this problem were proposed. Formulas were used to identify the economic excellence of the aircraft and an analysis was made of the distribution of flights and major airports around the globe. A graphical model for the search for the rational appearance of the aero
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