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Journal articles on the topic 'Four rotor helicopter'

Author: Grafiati

Published: 3 June 2025

Last updated: 20 July 2025

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1

Dai, Yuting, Linpeng Wang, Chao Yang, and Xintan Zhang. "Dynamic Gust Load Analysis for Rotors." Shock and Vibration 2016 (2016): 1–12. http://dx.doi.org/10.1155/2016/5727028.

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Dynamic load of helicopter rotors due to gust directly affects the structural stress and flight performance for helicopters. Based on a large deflection beam theory, an aeroelastic model for isolated helicopter rotors in the time domain is constructed. The dynamic response and structural load for a rotor under the impulse gust and slope-shape gust are calculated, respectively. First, a nonlinear Euler beam model with 36 degrees-of-freedoms per element is applied to depict the structural dynamics for an isolated rotor. The generalized dynamic wake model and Leishman-Beddoes dynamic stall model

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2

Toledo, J., L. Acosta, M. Sigut, J. Felipe, N. Morales, and S. Torres. "FOUR ROTOR HELICOPTER CONTROL LABORATORY PLANT." IFAC Proceedings Volumes 41, no. 2 (2008): 9779–84. http://dx.doi.org/10.3182/20080706-5-kr-1001.01654.

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3

Fujimoto, Keigo, Makoto Yokoyama, and Yuji Tanabe. "2B12 Adaptive control of a four-rotor mini helicopter." Proceedings of the Symposium on the Motion and Vibration Control 2010 (2010): _2B12–1_—_2B12–13_. http://dx.doi.org/10.1299/jsmemovic.2010._2b12-1_.

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4

Wang, Jialiang, Jianli Ding, Weidong Cao, Quanfu Li, and Hai Zhao. "Neural network fuzzy control for enhancing the stability performance of quad-rotor helicopter." Transactions of the Institute of Measurement and Control 40, no. 11 (2017): 3333–44. http://dx.doi.org/10.1177/0142331217713837.

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Recently, the quad-rotor helicopter has gained increasing attention owing to its very good flexibility, its ability to execute various flight missions even in harsh environments. The quad-rotor helicopter can implement different fight attitudes, which is attributed to the effective control of the motor speed about four propellers. In order to make the quad-rotor helicopter can better finish flight mission, the performance of flight stability then becomes particularly important. A neural network fuzzy control algorithm is proposed in this paper so as to guarantee the stability performance of th

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OTSUKA, Yuki, and Makoto YOKOYAMA. "543 Speed Control of Four-Rotor Mini Helicopter." Proceedings of the Dynamics & Design Conference 2006 (2006): _543–1_—_543–4_. http://dx.doi.org/10.1299/jsmedmc.2006._543-1_.

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6

Lu, Fei Fei, Fu Yang Chen, and Ling Cai. "A Developed Adaptive Tracking Control Technique for a Four-Rotor Helicopter with External Disturbance." Advanced Materials Research 846-847 (November 2013): 18–21. http://dx.doi.org/10.4028/www.scientific.net/amr.846-847.18.

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This paper deals with the tracking control problem of attitude angles for a four-rotor helicopter with external disturbance. A new direct adaptive compensation controller and its parameter adaptive laws are designed based on the Lyapunov stability theory, and the designed contorller can not only compensate the disturbance efficiently, but also can make the attitude angles of the four-rotor helicopter track a given reference output. By using the Barbalat lemma, the systems state tracking performance is proofed. Finally, the proposed adaptive technique is evaluated by a simulation example.

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7

Fahimi, Farbod. "Full formation control for autonomous helicopter groups." Robotica 26, no. 2 (2008): 143–56. http://dx.doi.org/10.1017/s0263574707003670.

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SUMMARYThis paper reports the design of sliding-mode control laws for controlling multiple small-sized autonomous helicopters in arbitrary formations. Two control schemes, which are required for defining arbitrary three-dimensional formation meshes, are discussed. In the presented leader–follower formation control schemes, each helicopter only needs to receive motion information from at most two neighboring helicopters. A nonlinear six-degree-of-freedom dynamic model has been used for each helicopter. Four control inputs, the main and the tail rotor thrusts, and the roll and pitch moments, are

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Panayotov, Filip, Ivan Dobrev, Fawaz Massouh, and Michael Todorov. "Experimental study of a helicopter rotor model in hover." MATEC Web of Conferences 234 (2018): 01002. http://dx.doi.org/10.1051/matecconf/201823401002.

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This paper presents the results from an experimental study of the aerodynamic performance and efficiency of a model helicopter rotor in steady hover at Reynolds numbers below 70000. Results are shown for a two-, three- and four-bladed rotor configuration for various pitch angles and speeds of rotation. The influence of the rotor solidity on the aerodynamic efficiency in terms of the Figure of Merit is highlighted. The profile drag component is evaluated as a function of the Reynolds number. The internal friction losses of the test stand are estimated and taken into account in all measurements.

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Beltran-Carbajal, Francisco, Hugo Yañez-Badillo, Ruben Tapia-Olvera, Antonio Favela-Contreras, Antonio Valderrabano-Gonzalez, and Irvin Lopez-Garcia. "On Active Vibration Absorption in Motion Control of a Quadrotor UAV." Mathematics 10, no. 2 (2022): 235. http://dx.doi.org/10.3390/math10020235.

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Conventional dynamic vibration absorbers are physical control devices designed to be coupled to flexible mechanical structures to be protected against undesirable forced vibrations. In this article, an approach to extend the capabilities of forced vibration suppression of the dynamic vibration absorbers into desired motion trajectory tracking control algorithms for a four-rotor unmanned aerial vehicle (UAV) is introduced. Nevertheless, additional physical control devices for mechanical vibration absorption are unnecessary in the proposed motion profile reference tracking control design perspec

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10

Cai, Guowei, Ben M. Chen, Tong H. Lee, and Kai-Yew Lum. "Comprehensive Nonlinear Modeling of a Miniature Unmanned Helicopter." Journal of the American Helicopter Society 57, no. 1 (2012): 1–13. http://dx.doi.org/10.4050/jahs.57.012004.

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A nonlinear flight dynamics model that can be adopted by small-scale unmanned aerial vehicle (UAV) helicopters is presented. To minimize structural complexity, the proposed nonlinear model contains only four essential components, i.e., kinematics, rigid-body dynamics, main rotor flapping dynamics, and yaw rate feedback controller dynamics. A five-step parameter determination procedure is proposed to estimate the unknown parameters of the flight dynamics model. Based on the time-domain evaluations conducted, the nonlinear model is proven to be accurate in capturing the flight dynamics of our UA

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11

Tuck, Loughlin E., Claire Samson, Jeremy Laliberté, and Michael Cunningham. "Magnetic interference mapping of four types of unmanned aircraft systems intended for aeromagnetic surveying." Geoscientific Instrumentation, Methods and Data Systems 10, no. 1 (2021): 101–12. http://dx.doi.org/10.5194/gi-10-101-2021.

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Abstract. Magnetic interference source identification is a critical preparation step for magnetometer-mounted unmanned aircraft systems (UAS) used for high-sensitivity geomagnetic surveying. A magnetic field scanner was built for mapping the low-frequency interference that is produced by a UAS. It was used to compare four types of electric-powered UAS capable of carrying an alkali-vapour magnetometer: (1) a single-motor fixed-wing, (2) a single-rotor helicopter, (3) a quad-rotor helicopter, and (4) a hexa-rotor helicopter. The scanner's error was estimated by calculating the root-mean-square d

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12

OGUCHI, Kazuki, and Manabu YAMADA. "112 Adaptive Stabilization Control of Four-Rotor Mini Helicopter." Proceedings of Conference of Tokai Branch 2012.61 (2012): _112–1_—_112–2_. http://dx.doi.org/10.1299/jsmetokai.2012.61._112-1_.

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13

Ma, Y. H., T. H. Shieh, L. C. Hung, and L. C. Tsai. "The design of a new type coaxial multilayer rotor helicopter vehicle." Journal of Physics: Conference Series 2345, no. 1 (2022): 012005. http://dx.doi.org/10.1088/1742-6596/2345/1/012005.

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Abstract Today’s small rotor helicopter vehicles mostly use electric motors and batteries as power sources. Most helicopter power configurations are either front powered or rear powered, causing the center of the helicopter to be offset. This kind of offset should be overcome by structural compensation or by adjusting the angle of attack of the blades, but some lift of the angle of attack will be sacrifice at the same time. This paper proposes a new type of electric helicopter powertrain design. The advantage of new type helicopter design is setting the centre of gravity at the centre position

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14

Ignatkin, Yurii M., Pavel V. Makeev, and Alexander I. Shomov. "CALCULATED RESEARCH OF INFLUENCE OF HELICOPTER MAIN ROTORS GEOMETRY ON THE EFFICIENCY IN HOVER MODE BASED ON THE NONLINEAR VORTEX MODEL." Civil Aviation High TECHNOLOGIES 21, no. 6 (2018): 43–53. http://dx.doi.org/10.26467/2079-0619-2018-21-6-43-53.

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The efficiency of the helicopter main rotor in the hover mode is very important, because this mode essentially determines the performance characteristics of the helicopter. A feature of the helicopter rotor aerodynamics is a significant inductive blade influence that highly defines its aerodynamic characteristics. The problem of the influence of the blade twist and spatial geometric layout of the main rotor on its aerodynamic characteristics in the hover mode for a fixed value of the rotor solidity has been considered in this article. As a criterion of efficiency of the rotor in the hover mode

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15

Gennaretti, Massimo, Giovanni Bernardini, Jacopo Serafini, and Marco Molica Colella. "Helicopter Vibratory Loads Alleviation through Combined Action of Trailing-Edge Flap and Variable-Stiffness Devices." International Journal of Aerospace Engineering 2015 (2015): 1–10. http://dx.doi.org/10.1155/2015/485964.

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The aim of this paper is the assessment of the capability of controllers based on the combined actuation of flaps and variable-stiffness devices to alleviate helicopter main rotor vibratory hub loads. Trailing-edge flaps are positioned at the rotor blade tip region, whereas variable-stiffness devices are located at the pitch link and at the blade root. Control laws are derived by an optimal control procedure based on the best trade-off between control effectiveness and control effort, under the constraint of satisfaction of the equations governing rotor blade aeroelastic response. The numerica

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16

Meng, De, Pinqi Xia, and Laishou Song. "MIMOMH feed-forward adaptive vibration control of helicopter fuselage by using piezoelectric stack actuators." Journal of Vibration and Control 24, no. 23 (2018): 5534–45. http://dx.doi.org/10.1177/1077546318757840.

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The vibration of a helicopter fuselage is mainly produced by the rotor exciting loads which are three forces and three moments containing harmonics in three directions at rotor hub center, and has the characteristic of large, steady and harmonic vibration. The active control of helicopter fuselage vibration by using inertia actuator needs to pay a heavy weight cost for achieving a good control effect. In this paper, a method for multi-input multi-output multi-harmonic (MIMOMH) feed-forward adaptive control of helicopter fuselage vibration by using piezoelectric stack actuators is presented. Th

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17

White, G. "Design study of a split-torque helicopter transmission." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 212, no. 2 (1998): 117–23. http://dx.doi.org/10.1243/0954410981532180.

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A helicopter transmission with split-torque drive trains to the main rotor and tail rotor drive shaft is described. A design based on two 1200 kW engines supplying torque to a 350 r/min main shaft demonstrates a weight reduction of 40 per cent, extreme low height and reduced losses. Four double-helical pinions drive a combining gear and provide a 10:1 reduction ratio to the main shaft; flexible torque tubes, set by fine-difference splines, control the division of torque between pairs of pinions. Rotor loads bypass the transmission housings and pass to the fuselage through a large-diameter mast

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18

Gibertini, G., A. Zanotti, G. Droandi, F. Auteri, and G. Crosta. "Experimental investigation of a helicopter rotor with Gurney flaps." Aeronautical Journal 121, no. 1236 (2017): 191–212. http://dx.doi.org/10.1017/aer.2016.120.

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ABSTRACTThe present work describes an experimental activity carried out to investigate the performance of Gurney flaps on a helicopter rotor model in hovering. The four blades of the articulated rotor model were equipped with Gurney flaps positioned at 95% of the aerofoil chord, spanning 14% of the rotor radius. The global aerodynamic loads and torque were measured for three Gurney flap configurations characterised by different heights. The global measurements showed an apparent benefit produced by Gurney flaps in terms of rotor performance with respect to the clean blade configuration. Partic

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19

Promkajin, Nicom, and Manukid Parnichkun. "Development of a robust attitude control for nonidentical rotor quadrotors using sliding mode control." International Journal of Advanced Robotic Systems 15, no. 1 (2018): 172988141775355. http://dx.doi.org/10.1177/1729881417753554.

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This work proposes a novel development of sliding mode control (SMC) for quadrotor helicopters utilizing offset cancellation technique. Most of the works on sliding mode control for quadrotors assumed that all rotors were identical, but in fact, the rotors even from the same factory are not exactly the same in aerodynamics properties. In addition, rotor deformation due to shock or heavy usage during operation may cause changes in parameters such as lift and drag coefficients, and so on, which, lead to offset error in the responses of attitude control. By applying the proposed offset cancellati

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20

Guerrero-Castellanos, J. F., N. Marchand, S. Lesecq, and J. Delamare. "Bounded attitude stabilization: Real-time application on four-rotor mini-helicopter." IFAC Proceedings Volumes 41, no. 2 (2008): 3167–73. http://dx.doi.org/10.3182/20080706-5-kr-1001.00538.

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21

Sheppard, Daniel J., Joyce Madden, and Sherrie A. Jones. "Simulator Design Features for Helicopter Shipboard Landings." Proceedings of the Human Factors Society Annual Meeting 31, no. 2 (1987): 233–37. http://dx.doi.org/10.1177/154193128703100222.

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The Vertical Takeoff and Landing Simulator (VTOL) at the Naval Training Systems Center's (NTSC) Visual Technology Research Simulator (VTRS) was used to study the effects of simulator design features on pilot performance in helicopter shipboard landings. The research was designed to evaluate the effects of current design features on the SH—60B Operational Flight Trainer (OFT) used to train helicopter shipboard landing and four proposed simulator design modifications. These were: (1) scene detail (SH—60B OFT scene versus an upgraded VTRS scene), (2) field-of-view (VTRS wide versus a smaller SH—6

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22

Wang, Jing Ying. "Helicopter Maneuver Flight Simulation and Control Law Design." Applied Mechanics and Materials 232 (November 2012): 517–20. http://dx.doi.org/10.4028/www.scientific.net/amm.232.517.

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This paper presents a solution to helicopter maneuver flight simulation according to ADS33 flying qualities requirement standard. Associated with aerodynamics and control law design methodology, the proposed scheme achieved satisfactory control performance by analyzing helicopter attitude and control parameter variation law at certain operating condition. To level flight acceleration, method based on force and moment balance is analyzed. To pirouette maneuver, a segment linear approximated trajectory is developed for attitude and velocity stability. All objective function is based on minimizin

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23

Nerubaskyi, Vadym. "Ринок та перспективи газотурбінних двигунів для надважких транспортних гелікоптерів". Aerospace Technic and Technology, № 4sup1 (29 серпня 2024): 5–11. http://dx.doi.org/10.32620/aktt.2024.4sup1.01.

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The introductory part of the article provides brief information about the main activity of Element JSC – the development and production of electronic control systems for aircraft engines, in particular, the RDC-450M ECU family for turboshaft gas turbine engines AI-450M, MS-500V, TV3-117VMA-SBM-1V, and others, created by SE Ivchenko-Progres and Motor Sich JSC. Element JSC, with its partners, has been involved in Ukrainian helicopter industry for more than 25 years. In the next section, the classification of helicopters is given, and the segment of super-heavy helicopters with gas turbine engine

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(Kevin) Li, Sicheng, and Seongkyu Lee. "Prediction of Urban Air Mobility Multirotor VTOL Broadband Noise Using UCD-QuietFly." Journal of the American Helicopter Society 66, no. 3 (2021): 1–13. http://dx.doi.org/10.4050/jahs.66.032004.

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This paper investigates broadband noise of multirotor urban air mobility (UAM) vertical take-off and landing (VTOL) vehicles. Based on an earlier single-rotor trailing-edge noise prediction method, a multirotor broadband noise prediction program is developed, where the multirotor coordinate transformation is included, and the amplitude modulation capability is introduced. Thereafter, the program is used to predict broadband noise from three UAM VTOL conceptual designs and a vertiport conceptual design. It is found that UAM VTOL vehicles' broadband noise is important in the high-frequency range

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Zhao, Ying, and Jian Xu Yang. "The Design of Mini Quad-Rotor Unmanned Aerial Vehicle Control System." Advanced Materials Research 383-390 (November 2011): 569–73. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.569.

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In this paper we describe a small four-rotor UAV's autonomous flight control system. A comprehensive plan of flight control system was designed base on the remote control model aircraft for flight platform, and Completed with AVR microcontroller core flight control system software and hardware design. It including device type, hardware circuit design and software design. Preliminary study of the four rotor while the helicopter flight control program design, For the future to perform more complex tasks such as fixed-point flight, obstacle avoidance and coordination of multiple aircraft flying a

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Mylapore, Anand Radhakrishnan, and Fredric H. Schmitz. "An Experimental Investigation of Ground Effect on a Quad Tilt Rotor in Hover." Journal of the American Helicopter Society 60, no. 1 (2015): 1–14. http://dx.doi.org/10.4050/jahs.60.012002.

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The performance of a 0.031 geometrically scaled fuselage/wing model of a Quad Tilt Rotor (QTR) operating in helicopter mode while hovering in-ground effect (IGE) and out-of-ground effect (OGE) was experimentally studied. The effect of ground proximity was tested by varying the height of the model above the ground. Measurements included download on the airframe; thrust, torque, and rpm of the rotors; and static pressures along the centerline of the bottom of the fuselage. Fixedpitch propellers were used to model the rotors. The downwash distributions of the rotors were measured and compared wel

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27

Liu, Yang, Yongjie Shi, Aqib Aziz, and Guohua Xu. "Numerical Study on Rotor–Building Coupled Flow Field and Its Influence on Rotor Aerodynamic Performance under an Atmospheric Boundary Layer." Aerospace 11, no. 7 (2024): 521. http://dx.doi.org/10.3390/aerospace11070521.

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In urban settings, buildings create complex turbulent conditions, affecting helicopter flight performance during missions and increasing safety risks during takeoff and landing. A numerical study on rotor–building coupled flow field is carried out to address rotor aerodynamic performance under building interferences in natural atmospheric conditions. A high-fidelity atmospheric boundary layer (ABL) model described by an exponential law is established herein. The solution of the coupled flow field is based on the Reynolds-averaged Navier–Stokes (RANS) equations, with the rotor’s rotation achiev

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28

Fujimoto, Keigo, and Makoto Yokoyama. "Robust Velocity Tracking Control with an Observer for Four-rotor Mini Helicopter." IFAC Proceedings Volumes 42, no. 16 (2009): 38–43. http://dx.doi.org/10.3182/20090909-4-jp-2010.00009.

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29

FUJIMOTO, Keigo, Makoto YOKOYAMA, and Yuji TANABE. "C304 Position and yaw angle control for a four rotor mini helicopter." Proceedings of the Symposium on the Motion and Vibration Control 2011.12 (2011): 576–81. http://dx.doi.org/10.1299/jsmemovic.2011.12.576.

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30

Wu, Qing Bo, Fu Yang Chen, and Chang Yun Wen. "A Self-Repairing Control Scheme for Quadrotor Helicopter via Active Disturbance Rejection Control." Applied Mechanics and Materials 404 (September 2013): 603–8. http://dx.doi.org/10.4028/www.scientific.net/amm.404.603.

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In this paper, a self-repairing control scheme for attitude control of a quadrotor helicopter via active disturbance rejection control is proposed. Firstly, a model of the quadrotor helicopter is gained by its dynamic equations with pitch, roll and yaw axis. Then the active disturbance rejection controller is introduced, which is used to design the control system. The control system consists of PID controller in inner-loop and ADRC controller in outer-loop. Disturbances and uncertainties can be compensated by the ADRC to achieve smaller tracking error. Finally, the simulation results of the fo

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31

Fahmizal, Daffa Yanu Kharisma, and Subuh Pramono. "Implementation of Fuzzy Logic Control on a Tower Copter." Journal of Fuzzy Systems and Control 1, no. 1 (2023): 14–17. http://dx.doi.org/10.59247/jfsc.v1i1.25.

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Air transport has become a major attraction for scientists in the last decade, to carry out developments in the fields of firefighting, military, and commercial purposes. A quadcopter is a helicopter with four rotors. There are four arms connected to the main control and each arm has a motor with a rotor. In this study, the position control of a tower control is presented. A Fuzzy Logic Controller (FLC) is proposed, and it performance is compared with PID control. The hardware implementation test shows that FLC is superior to PID. The hardware testing shows that the settling time of the FLC co

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32

Samad, Abdallah, Gitsuzo B. S. Tagawa, François Morency, and Christophe Volat. "Predicting Rotor Heat Transfer Using the Viscous Blade Element Momentum Theory and Unsteady Vortex Lattice Method." Aerospace 7, no. 7 (2020): 90. http://dx.doi.org/10.3390/aerospace7070090.

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Calculating the unsteady convective heat transfer on helicopter blades is the first step in the prediction of ice accretion and the design of ice-protection systems. Simulations using Computational Fluid Dynamics (CFD) successfully model the complex aerodynamics of rotors as well as the heat transfer on blade surfaces, but for a conceptual design, faster calculation methods may be favorable. In the recent literature, classical methods such as the blade element momentum theory (BEMT) and the unsteady vortex lattice method (UVLM) were used to produce higher fidelity aerodynamic results by coupli

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33

Mihara, Yusuke, Tsubasa Nakamura, Aki Nakamoto, and Masaru Nakano. "Airframe Design Optimization and Simulation of a Flying Car for Medical Emergencies." International Journal of Automation Technology 16, no. 2 (2022): 183–96. http://dx.doi.org/10.20965/ijat.2022.p0183.

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In terms of future transportation, flying cars are envisioned not only as air taxis but also as air ambulances. Flying cars such as urban air mobility vehicles, passenger drones, and electrical vertical take-off and landing (eVTOL) aircrafts have the potential to relieve seriously congested ground traffic in cities via direct point-to-point air movements. To date, conventional research in which the airframe of a flying car is optimized for use in medical emergencies has not identified a sustainable solution. The purpose of this study is to verify the technical applicability of a flying car for

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Petermann, Jannik, Yong Su Jung, James Baeder, and Jürgen Rauleder. "Validation of Higher-Order Interactional Aerodynamics Simulations on Full Helicopter Configurations." Journal of the American Helicopter Society 64, no. 4 (2019): 1–13. http://dx.doi.org/10.4050/jahs.64.042002.

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Time-accurate numerical predictions of the interactional aerodynamics between NASA's generic ROBIN fuselage and its four-bladed rotor were performed using the recently developed Reynolds-averaged Navier–Stokes solver HAMSTR. Two stencil-based reconstruction schemes (MUSCL, WENO), a second-order temporal accuracy, and the Spalart–Allmaras turbulence model were used. Three-dimensional volume meshes were created in a robust manner from two-dimensional unstructured surface grids using Hamiltonian paths and strands on nearbody domains. Grid connectivity was established between nearbody and backgrou

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Thirumaleshwar Hegde, Navya, V. I. George, C. Gurudas Nayak, and Kamlesh Kumar. "Transition flight modeling and robust control of a VTOL unmanned quad tilt-rotor aerial vehicle." Indonesian Journal of Electrical Engineering and Computer Science 18, no. 3 (2020): 1252. http://dx.doi.org/10.11591/ijeecs.v18.i3.pp1252-1261.

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<span>The development of fully autonomous Unmanned Aerial Vehicles (UAV) plays a major contribution towards reducing the risk to human life in various applications including rescue teams, border patrol, police and inspection of buildings, pipelines, coasts, and terrains. Tiltrotor hybrid UAV exhibit special application value due to its unique rotor structure. The variation in the model dynamics and aerodynamics due to the tilting rotors are the major key issues and challenges which attracted the attention of many researchers. This vehicle combines the hovering capabilities of a helicopte

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HOTTA, Katsuya, Manabu YAMADA, and Tatsushi OOBA. "Adaptive Tracking Control of a Four-rotor Mini Helicopter Based on Backstepping Technique." Transactions of the Society of Instrument and Control Engineers 50, no. 2 (2014): 177–84. http://dx.doi.org/10.9746/sicetr.50.177.

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FUJIMOTO, Keigo, Makoto YOKOYAMA, and Yuji TANABE. "333 I&I-based adaptive control of a four-rotor mini helicopter." Proceedings of the Dynamics & Design Conference 2010 (2010): _333–1_—_333–6_. http://dx.doi.org/10.1299/jsmedmc.2010._333-1_.

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Szulc, O., T. Suresh, and P. Flaszyński. "Rotorcraft thickness noise control by tip ventilation." Journal of Physics: Conference Series 2367, no. 1 (2022): 012002. http://dx.doi.org/10.1088/1742-6596/2367/1/012002.

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Abstract The paper explains further developments of a new concept called TNC (Thickness Noise Control) of the application of surface ventilation to the reduction of helicopter rotor low-frequency in-plane harmonic (LF-IPH) noise. The TNC method is based on introduction of four cavities covered by perforated plates (connected to low and high pressure reservoirs) and positioned symmetrically at the front and rear extremities of the blade tip. Two operational modes are analyzed: constant (steady) and periodically varying (unsteady) transpiration mass-fluxes. For exemplary two-bladed model helicop

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Rosales, Claudio, Daniel Gandolfo, Gustavo Scaglia, Mario Jordan, and Ricardo Carelli. "Trajectory tracking of a mini four-rotor helicopter in dynamic environments - a linear algebra approach." Robotica 33, no. 08 (2014): 1628–52. http://dx.doi.org/10.1017/s0263574714000952.

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SUMMARYThis paper presents the design of a controller that allows a four-rotor helicopter to track a desired trajectory in 3D space. To this aim, a dynamic model obtained from Euler-Lagrange equations describes the robot. This model is represented by numerical methods, with which the control actions for the operation of the system are obtained. The proposed controller is simple and presents good performance in face of uncertainties in the model of the system to be controlled. Zero-convergence proof is included, and simulation results show a good performance of the control system.

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Ma, Yimin, Ming Chen, Qiang Wang, and Fang Wang. "Main helicopter rotor trimming using computational fluid dynamics method in forward flight." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 1 (2016): 169–79. http://dx.doi.org/10.1177/0954410016673394.

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In this paper, a computational fluid dynamics trimming method is proposed and compared with wind tunnel experiment and the blade element method. The NASA’s generic ROBIN helicopter model is adopted for transient simulations to obtain the final main rotor trimming conditions. Totally three steps were applied to the computational fluid dynamics method. The first step is associated with no cyclic pitch motion, the second is regarding pure longitudinal cyclic pitch motion and the last is concerning with pure lateral cyclic pitch motion. At the same time, a simple linear equation system between the

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YAMASHITA, Shuhei, Katsuya HOTTA, Keita MORI, and Manabu YAMADA. "D23 Adaptive Tracking Control of Four-rotor Mini Helicopter Based on Exact Feedback Linearization." Proceedings of the Symposium on the Motion and Vibration Control 2013.13 (2013): _D23–1_—_D23–10_. http://dx.doi.org/10.1299/jsmemovic.2013.13._d23-1_.

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Austruy, Julien, Farhan Gandhi, and Nick Lieven. "Rotor Vibration Reduction Using an Embedded Spanwise Absorber." Journal of the American Helicopter Society 57, no. 2 (2012): 49–60. http://dx.doi.org/10.4050/jahs.57.022008.

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This paper examines the effectiveness of an embedded spanwise Coriolis absorber in a rotor blade in reducing the in-plane vibratory hub loads. Simulations based on a light, four-bladed, hingeless rotor helicopter similar to the BO-105 showed that in high-speed flight (140 kt), over 85% reductions in both 4/rev longitudinal and lateral hub shears could nominally be achieved using an absorber mass 3% of the blade mass situated at 60% span, oscillating at 3/rev with an amplitude of about 0.03 ft. If the baseline in-plane vibration levels of the helicopter are increased to 0.1–0.12 g, the reductio

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Derafa, L., A. Ouldali, T. Madani, and A. Benallegue. "Non-linear control algorithm for the four rotors UAV attitude tracking problem." Aeronautical Journal 115, no. 1165 (2011): 175–85. http://dx.doi.org/10.1017/s0001924000005571.

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Abstract This paper deals with the design and implementation of the nonlinear control algorithm for the attitude tracking of a four-rotor helicopter known as quadrotor. The choice of this algorithm, which is based on the Backstepping sliding mode technique with adaptive gain, was justified by the fact that it ensures robustness with respect to modelling errors and external disturbances while reducing the chattering phenomenon caused by the sign function in the first order sliding mode based controllers with fixed gains. In order to show the effectiveness of the controller, experimental tests w

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Toda, Hideki. "Experimental Study of Problem of Estrangement of AR. Drone Four Rotor Helicopter Velocity Parameter Calculated by the Internal IMU." International Journal of Engineering Research and Science 3, no. 8 (2017): 123–29. http://dx.doi.org/10.25125/engineering-journal-ijoer-aug-2017-26.

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Vershkov, V. A., B. S. Kritsky, and R. M. Mirgazov. "FEATURES OF MODELING THE FLOW AROUND THE HELICOPTER MAIN ROTOR TAKING INTO ACCOUNT ARBITRARY BLADES MOTION." Civil Aviation High TECHNOLOGIES 22, no. 3 (2019): 25–34. http://dx.doi.org/10.26467/2079-0619-2019-22-3-25-34.

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The article considers the problem of the flow around the helicopter main rotor taking into account blades flapping in the plane of rotation and in the plane of thrust as well as the elastic blades deformation. The rotor rotation is modeled by the method of converting Navier-Stokes equations from a fixed coordinate system associated with the incoming flow into a rotating system associated with the rotor hub. For axial flow problems, this makes it possible to formulate the problem as stationary at a constant rotational speed of rotor. For a mode of skewed flow around the rotor in the terms of in

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Gennaretti, M., M. Molica Colella, and G. Bernardini. "Analysis of helicopter vibratory hub loads alleviation by cyclic trailing-edge blade flap actuation." Aeronautical Journal 113, no. 1146 (2009): 549–56. http://dx.doi.org/10.1017/s0001924000003201.

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Abstract The aim of the present work is the investigation about the use of blade trailing-edge flaps for the reduction of vibratory loads arising at the hub of helicopter main rotors in forward flight. The alleviation of these loads is achieved through multicyclic higher harmonic actuation of the blade flaps, which is related to measured vibratory loads amplitude. The feedback control law is obtained by an optimal control process based on the minimisation of a cost function, under the constraint of compatibility with the nonlinear equations governing blade aeroelasticity. In the numerical inve

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TIAN, SHULING, YIZHAO WU, and JIAN XIA. "NUMERICAL SIMULATION OF UNSTEADY FLOW FIELD AROUND HELICOPTER IN FORWARD FLIGHT USING A PARALLEL DYNAMIC OVERSET UNSTRUCTURED GRIDS METHOD." Modern Physics Letters B 23, no. 03 (2009): 325–28. http://dx.doi.org/10.1142/s021798490901831x.

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A parallel Navier-Stokes solver based on dynamic overset unstructured grids method is presented to simulate the unsteady turbulent flow field around helicopter in forward flight. The grid method has the advantages of unstructured grid and Chimera grid and is suitable to deal with multiple bodies in relatively moving. Unsteady Navier-Stokes equations are solved on overset unstructured grids by an explicit dual time-stepping, finite volume method. Preconditioning method applied to inner iteration of the dual-time stepping is used to speed up the convergence of numerical simulation. The Spalart-A

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Ramli, Hanif, Wahyu Kuntjoro, and Ahmad Khushairy Makhtar. "Advanced Autonomous Multirotor Response System." Applied Mechanics and Materials 393 (September 2013): 299–304. http://dx.doi.org/10.4028/www.scientific.net/amm.393.299.

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Autonomous Unmanned Aerial Vehicle (UAV) in the form of multi-rotor system is having a great potential in various applications such as disaster management (as first response system) and surveillance. It is known that conventional helicopter system, capable of hovering, is practical and reliable as many applications have confirmed its capabilities. However it is only achievable once highly optimized control architecture is realized. The objective of the research presented in this paper is, to develop a small multi rotor UAV system that is able to autonomously flying from one way point to anothe

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FUJIMOTO, Keigo, Makoto YOKOYAMA, and Yuji TANABE. "I&I-Based Adaptive Control of a Four-Rotor Mini Helicopter with Uncertain Aerodynamic Parameters." TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series C 77, no. 782 (2011): 3721–36. http://dx.doi.org/10.1299/kikaic.77.3721.

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FUJIMOTO, Keigo, Makoto YOKOYAMA, and Yuji TANABE. "Position and Yaw Angle Control for a Four Rotor Mini Helicopter Based on a Geometric Approach." TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series C 78, no. 785 (2012): 126–37. http://dx.doi.org/10.1299/kikaic.78.126.

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