Relevant bibliographies by topics / Rotors (Helicopters)

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Rotors (Helicopters)'

Author: Grafiati
Published: 4 June 2021
Last updated: 29 March 2025

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Journal articles on the topic "Rotors (Helicopters)"

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Frey, Felix, Jakob Thiemeier, Constantin Öhrle, Manuel Keßler, and Ewald Krämer. "Aerodynamic Interactions on Airbus Helicopters' Compound Helicopter RACER in Cruise Flight." Journal of the American Helicopter Society 65, no. 4 (October 1, 2020): 1–14. http://dx.doi.org/10.4050/jahs.65.042001.

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With the pursuit of extending the flight envelopes of helicopters toward higher cruise speed, helicopter manufacturers increasingly have come up with nonconventional configurations in recent years. Among these, Airbus Helicopters' RACER (Rapid And Cost-Efficient Rotorcraft) is a compound helicopter equipped with a boxwing and lateral pusher rotors. In combination with the main rotor, these additional components determine the aerodynamic characteristics of the helicopter. Thereby, depending on the flight conditions, their individual performance is influenced by a variety of interactions. As the understanding of these interactions is vital for the evaluation of the overall system, the respective mutual influence of main rotor, wings, and lateral rotors is analyzed in this paper for cruise flight. For this reason, high-fidelity coupled aerodynamic simulations are conducted not only for the full RACER configuration but also for reduced setups omitting individual components to isolate the effect of these components on the helicopter's aerodynamic performance.
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Stalewski, Wienczyslaw, and Wieslaw Zalewski. "Performance improvement of helicopter rotors through blade redesigning." Aircraft Engineering and Aerospace Technology 91, no. 5 (May 13, 2019): 747–55. http://dx.doi.org/10.1108/aeat-01-2018-0009.

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Purpose The purpose of this paper is to determine dependencies between a rotor-blade shape and a rotor performance as well as to search for optimal shapes of blades dedicated for helicopter main and tail rotors. Design/methodology/approach The research is conducted based on computational methodology, using the parametric-design approach. The developed parametric model takes into account several typical blade-shape parameters. The rotor aerodynamic characteristics are evaluated using the unsteady Reynolds-averaged Navier–Stokes solver. Flow effects caused by rotating blades are modelled based on both simplified approach and truly 3D simulations. Findings The computational studies have shown that the helicopter-rotor performance may be significantly improved even through relatively simple aerodynamic redesigning of its blades. The research results confirm high potential of the developed methodology of rotor-blade optimisation. Developed families of helicopter-rotor-blade airfoils are competitive compared to the best airfoils cited in literature. The finally designed rotors, compared to the baselines, for the same driving power, are characterised by 5 and 32% higher thrust, in case of main and tail rotor, respectively. Practical implications The developed and implemented methodology of parametric design and optimisation of helicopter-rotor blades may be used in future studies on performance improvement of rotorcraft rotors. Some of presented results concern the redesigning of main and tail rotors of existing helicopters. These results may be used directly in modernisation processes of these helicopters. Originality/value The presented study is original in relation to the developed methodology of optimisation of helicopter-rotor blades, families of modern helicopter airfoils and innovative solutions in rotor-blade-design area.
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Fletcher, T. M., and R. E. Brown. "Modelling the interaction of helicopter main rotor and tail rotor wakes." Aeronautical Journal 111, no. 1124 (October 2007): 637–43. http://dx.doi.org/10.1017/s0001924000004814.

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Abstract The mutual interaction between the main rotor and tail rotor wakes is central to some of the most problematic dynamic phenomena experienced by helicopters. Yet achieving the ability to model the growth and propagation of helicopter rotor wakes with sufficient realism to capture the details of this interaction has been a significant challenge to rotorcraft aerodynamicists for many decades. A novel computational fluid dynamics code tailored specifically for rotorcraft applications, the vorticity transport model, has been used to simulate the interaction of the rotors of a helicopter with a single main rotor and tail rotor in both hover and low-speed quartering flight, and with the tail rotor rotating both top-forward and top-aft. The simulations indicate a significant level of unsteadiness in the performance of both main and tail rotors, especially in quartering flight, and a sensitivity to the direction of rotation of the tail rotor. Although the model thus captures behaviour that is similar to that observed in practice, the challenge still remains to integrate the information from high fidelity simulations such as these into routine calculations of the flight dynamics of helicopters.
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Ishiki, Takahiro, Kai Washizaki, and Makoto Kumon. "Evaluation of Microphone Array for Multirotor Helicopters." Journal of Robotics and Mechatronics 29, no. 1 (February 20, 2017): 168–76. http://dx.doi.org/10.20965/jrm.2017.p0168.

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[abstFig src='/00290001/16.jpg' width='300' text='UAV with a microphone array whose performance is evaluated' ] High expectations are placed on the use of unmanned aerial vehicles (UAVs) in such tasks as rescue operations, which require a system that makes use of visual or auditory information to recognize the surrounding environment. As an example of such a system, this study examines the recognition of the environment using a helicopter mounted with a microphone array. Because the rotors of a helicopter generate high noise during operation, it is necessary to reduce the effects of this noise and those from other sources to record the audio signals coming from the ground with onboard microphones. In particular, because of helicopter body control, the rotor speed changes continuously and causes an unsteady rotor noise, which implies that it would be effective to arrange the microphones at a sufficient distance from the rotors. When a large microphone array is employed, however, the array weight may alter the helicopter’s flight characteristics and increase the noise, presenting a dilemma. This paper presents a model of rotor noise that takes into account the effect of the microphone array on the helicopter’s dynamic characteristics and proposes a method of evaluating the optimality of the array configuration, which is necessary for design. The validity of the proposed method is investigated using a multirotor helicopter mounted with a microphone array previously developed by the authors. In addition, an application example for locating sound sources on the ground using this helicopter is presented.
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Stanisławski, Jarosław. "Performance of Quiet Helicopter." Transactions on Aerospace Research 2020, no. 1 (March 1, 2020): 1–17. http://dx.doi.org/10.2478/tar-2020-0001.

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AbstractNoise generated by helicopters is one of the main problems associated with the operation of rotorcrafts. Requirements for reduction of helicopter noise were reflected in the regulations introducing lower limits of acceptable rotorcraft noise. A significant source of noise generated by helicopters are the main rotor and tail rotor blades. Radical noise reduction can be obtained by slowing down the blade tips speed of main and tail rotors. Reducing the rotational speed of the blades may decrease rotor thrust and diminish helicopter performance. The problem can be solved by attaching more blades to main rotor. The paper presents results of calculation regarding improvement of the helicopter performance which can be achieved for reduced rotor speed but with increased number of rotor blades. The calculations were performed for data of hypothetical light helicopter. Results of simulation include rotor loads and blade deformations in chosen flight conditions. Equations of motion of flexible rotor blades were solved using the Galerkin method which takes into account selected eigen modes of the blades. The simulation analyzes can help to determine the performance and loads of a quiet helicopter with reduced rotor speed within the operational envelope of helicopter flight states.
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Dudnik, Vitaly. "DETERMINATION OF LOADS IN THE ULTRALIGHT HELICOPTER BLADES." Aviation 27, no. 4 (November 28, 2023): 242–47. http://dx.doi.org/10.3846/aviation.2023.20236.

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The article describes research that was carried out on coaxial a single-seat ultralight helicopter Rotorschmiede VA-115 which is manufactured by German firm RS Helikopter GmbH. The purpose of the work was to determine the blades’ loads necessary for further blade fatigue analysis and ground bench tests. The methodology for the load determination consisted of deformation measurements using strain gauges in various flight modes from hovering to maximum speed flight, including climb, descent, acceleration, and braking. Ultralight helicopters occupy the smallest cost niche and, as a rule, full-fledged fatigue studies are not performed for such helicopters. The requirements for ultralight helicopters are also quite loyal, allowing them to pass such experiments. Analysis of the data shows that the amplitude of bending moments on the lower rotor is higher by 1.2 to 2 times the value on the upper rotor. The absolute maximum value of the bending moment is significantly greater at the minimum weight, although the oscillation amplitude becomes smaller. The presented data can be useful for designers of ultralight and UAV helicopters with teetering hinge rotors.
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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 are applied to calculate the nonlinear unsteady aerodynamic forces on rotors. Then, we transformed the differential aeroelastic governing equation to an algebraic one. Hence, the widely used Newton-Raphson iteration algorithm is employed to simulate the dynamic gust load. An isolated helicopter rotor with four blades is studied to validate the structural model and the aeroelastic model. The modal frequencies based on the Euler beam model agree well with published ones by CAMRAD. The flap deflection due to impulse gust with the speed of 2m/s increases twice to the one without gust. In this numerical example, results indicate that the bending moment at the blade root is alleviated due to elastic effect.
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Aleksandrov, Dmitri, and Igor Penkov. "Optimization of Lift Force of Mini Quadrotor Helicopter by Changing of Gap Size between Rotors." Solid State Phenomena 198 (March 2013): 226–31. http://dx.doi.org/10.4028/www.scientific.net/ssp.198.226.

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This paper describes comparison between virtual simulation of quadrotor flying platforms (mini UAV - Unmanned Aerial Vehicle) and real experiments. In quadrotor helicopter (quadrocopter) air flows that are going out from rotors and affecting each other were simulated. Analysis of several helicopters that have different distances between rotors on different angular velocities were compared. During virtual simulation (with CFD Computational Fluid Dynamics software) there were conducted similar to real experiments with the use of scanned rotors (with 3D scanner) and same environment conditions. These experiments were compared with real experiments. Optimal gap distance between rotors is determined, when helicopter mass is minimum and rotors are creating maximum lifting force and consuming minimum energy (minimum impact on air flows to each other).
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KACHEL, Stanisław, Robert ROGÓLSKI, and Jakub KOCJAN. "Review of Modern Helicopter Constructions and an Outline of Rotorcraft Design Parameters." Problems of Mechatronics Armament Aviation Safety Engineering 12, no. 3 (September 30, 2021): 27–52. http://dx.doi.org/10.5604/01.3001.0015.2427.

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This work contains the results of a modern helicopter construction analysis. It includes the comparison of almost seventy rotorcraft constructions in terms of size in line with EASA requirements – large and small helicopters. The helicopters are also divided because of a mission purpose. The proposed division for large aircrafts is: transport, multipurpose, attack and for small aircrafts: observation, training, and utility. The aircraft construction features are described. Average dimension values of airframes and rotors are shown. Helicopter rotor arrangements are presented in terms of an operational purpose. Next, the rotorcraft design inputs are described. The mathematical formulas for design inputs are given. The ratios are calculated and gathered for the compared aircrafts. Correlation between the analysed parameters is presented on charts. Design inputs are also presented in the paper as a function of MTOW. The function trends are determined to provide an evaluation tool for helicopter designers. In addition, the parameters are presented as possible optimisation variables.
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Tran, Ngoc Khanh, Van Quang Dao, Phu Khanh Nguyen, Thi Kim Dung Hoang, and Van Khang Nguyen. "Numerical Investigations of Aerodynamics Characteristics of Main Rotors in Helicopter UAV Used for Pesticide Spraying in Agriculture." Applied Mechanics and Materials 889 (March 2019): 425–33. http://dx.doi.org/10.4028/www.scientific.net/amm.889.425.

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In the last several decades past, Helicopters UAVs (Unmanned Aerial Vehicles) have quickly developed and day by day, they play an important role in human life. As it is well-known, helicopters UAV make some outstanding characteristics such as light weight, flexibility and particularly automatically controlled. By applying these characteristics, we research and manufacture Helicopter UAV using for spraying pesticide in agriculture. One of the most important components is main rotor because main rotor generated thrust, drag and momentum. Helicopters UAV efficient changed depending on main rotor. The research works focus on aerodynamics characterization of main rotor in helicopter UAV. This work uses CFD tool in ANSYS CFX software to calculate the aerodynamics parameters generated by main rotor using in UAV. The aim is to characterize the aerodynamics characteristics such as thrust, drag, pressure, aerodynamics quality on the different flight modes (hover, vertical and forward flight). Firstly, the simulations are carried out in hover flight mode with different blade pitch angles. The results are compared to experiment date in another research to validate numerical results. Then, the simulations are carried out in vertical flight mode and forward flight mode. The results showed that thrust and drag coefficient creased with increasing blade pitch angle. When blade pitch angle started from 1800, thrust coefficient decreased but drag coefficient increased sharply. The rotor performance was measured by aerodynamics quality and numerical results showed that the best rotor performance was at 900. In the vertical flight mode, the thrust and drag coefficient decreased with increasing vertical velocity but rotor performance increased slightly. The best vertical velocity for vertical flight is around 2 m/s and 3 m/s. Finally, in forward flight mode, the aerodynamics characterizations of rotors depended on azimuthal angular position of blade or time. Our helicopter operates in environment with light gust. The results showed the change of aerodynamics coefficient to time. Both thrust and drag coefficient changed but the rotor performance did not change much.
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Dissertations / Theses on the topic "Rotors (Helicopters)"

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Atilgan, Ali Rana. "Towards a unified analysis methodology for composite rotor blades." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/15403.

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Taylor, Dana J. "A method for the efficient calculation of elastic rotor blade dynamic response in forward flight." Diss., Georgia Institute of Technology, 1987. http://hdl.handle.net/1853/12396.

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Ozturk, Dogan. "Development of a Myklestad's rotor blade dynamic analysis code for application to JANRAD." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FOzturk.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, September 2002.
Thesis advisor(s): E. Roberts Wood, Mark A. Couch. Includes bibliographical references (p. 213-214). Also available online.
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Van, Riper Steven G. "Investigation of increased forward flight velocities of helicopters using second harmonic control and reverse velocity rotor concept." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Dec%5FVanRiper.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, December 2003.
Thesis advisor(s): E. Roberts Wood, Raymond Shreeve. Includes bibliographical references (p. 145-146). Also available online.
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Akin, Hakki E. "A computer code for rapid calculation of bending frequencies of rotor blades." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2002. http://library.nps.navy.mil/uhtbin/hyperion-image/02sep%5FAkin.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 2002.
Thesis advisor(s): E. Roberts Wood, Mark A. Couch. Includes bibliographical references (p. 195-196). Also available online.
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Collins, Kyle Brian. "A multi-fidelity framework for physics based rotor blade simulation and optimization." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2008. http://hdl.handle.net/1853/26481.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2009.
Committee Co-Chair: Dr. Dimitri Mavris; Committee Co-Chair: Dr. Lakshmi N. Sankar; Committee Member: Dr. Daniel P. Schrage; Committee Member: Dr. Kenneth S. Brentner; Committee Member: Dr. Mark Costello. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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Sturisky, Selwyn H. "A linear system identification and validaton of an AH-64 apache aeroelastic simulation model." Diss., Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/13402.

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Teare, David Alan. "Modeling and system identification for rotorcraft." Thesis, Georgia Institute of Technology, 1988. http://hdl.handle.net/1853/17088.

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Tatossian, Charles A. "Aerodynamic shape optimization via control theory of helicopter rotor blades using a non-linear frequency domain approach." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112586.

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This study presents a discrete adjoint-based aerodynamic optimization algorithm for helicopter rotor blades in hover and forward flight using a Non-Linear Frequency Domain approach. The goal is to introduce a Mach number variation into the Non-Linear Frequency Domain (NLFD) method and implement a novel approach to present a time-varying cost function through a multi-objective adjoint boundary condition. The research presents the complete formulation of the time dependent optimal design problem. The approach is firstly demonstrated for the redesign of a NACA 0007 and a NACA 23012 helicopter rotor blade section in forward flight. A three-dimensional inviscid Aerodynamic Shape Optimization (ASO) algorithm is then employed to validate and redesign the Caradonna and Tung experimental blade. The results in determining the optimum aerodynamic configurations require an objective function which minimizes the inviscid torque coefficient and maintains the desired thrust level at transonic conditions.
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Su, Ay. "Application of a state-space wake model to elastic blade flapping in hover." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/11965.

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Books on the topic "Rotors (Helicopters)"

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Gilliand, Harry E. Dancing rotors. Arlington, Tex: Aerofax, 1994.

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Ralph, Jolly J., Marcolini Michael A, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Helicopter main-rotor noise: Determination of source contributions using scaled model data. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Brooks, Thomas F. Helicopter main-rotor noise: Determination of source contributions using scaled model data. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Brooks, Thomas F. Helicopter main-rotor noise: Determination of source contributions using scaled model data. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Brooks, Thomas F. Helicopter main-rotor noise: Determination of source contributions using scaled model data. Hampton, Va: Langley Research Center, 1988.

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Martin, R. M. Acoustic test of a model rotor and tail rotor: Results for the isolated rotors and combined configuration. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

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Runyan, Harry L. Compressible, unsteady lifting-surface theory for a helicopter rotor in forward flight. Washington: NASA, 1985.

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H, Tai, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Compressible, unsteady, lifting-surface theory for a helicopter rotor in forward flight. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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B, Maskew, Langley Research Center, and Analytical Methods Inc, eds. Inviscid analysis of unsteady blade tip flow correlation studies. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. Application of higher harmonic blade feathering on the OH-6A helicopter for vibration reduction. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Book chapters on the topic "Rotors (Helicopters)"

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Introduction." In Smart Helicopter Rotors, 1–40. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_1.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Airfoil-Section Rotor Blades." In Smart Helicopter Rotors, 189–219. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_10.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Dynamic Stall Alleviation Using Active Twist." In Smart Helicopter Rotors, 221–49. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_11.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Mathematical Modeling." In Smart Helicopter Rotors, 41–70. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_2.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Preliminary Studies with Active Flaps." In Smart Helicopter Rotors, 71–80. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_3.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Flap Configuration and Control Law." In Smart Helicopter Rotors, 81–101. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_4.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Active Flap Controller Evaluation." In Smart Helicopter Rotors, 103–11. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_5.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Trailing-Edge Flap Placement." In Smart Helicopter Rotors, 113–27. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_6.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Piezoceramic Actuator Hysteresis." In Smart Helicopter Rotors, 129–64. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_7.

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Ganguli, Ranjan, Dipali Thakkar, and Sathyamangalam Ramanarayanan Viswamurthy. "Active Rotating Beams." In Smart Helicopter Rotors, 165–76. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-24768-7_8.

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Conference papers on the topic "Rotors (Helicopters)"

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Swartz, Kenneth. "Canadian Rotors: Evolution of the Canadian Helicopter Industry." In Vertical Flight Society 74th Annual Forum & Technology Display, 1–20. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12797.

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This paper tracks the development of the Canadian helicopter industry from its birth to present day highlighting the role that helicopter manufacturers played in the industry's development. Canada has been the home for the world's second largest civil helicopter market for almost seven decades, but the creation of a domestic helicopter manufacturing capability took much longer to achieve. In 2018, there are more than 5,000 Canadian-assembled helicopters flying throughout the world and thousands more helicopters take off every day powered by Canadian made gas turbine engines.
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Schatzman, Natasha, Athena Chan, Michael Fillman, Vinod Gehlot, Larry Meyn, Paulina Ridland, Kenneth Glazebrook, and Diego Santillan. "Performance Analysis and Data Processing for the Mars Sample Recovery Helicopter in the Jet Propulsion Laboratory 25-ft Space Simulator." In Vertical Flight Society 80th Annual Forum & Technology Display, 1–11. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1357.

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On April 19, 2021, Ingenuity became the first helicopter to fly on Mars at Jezero Crater, completing a total of 72 flights by the end of its mission. The success of Ingenuity resulted in various research efforts to further exploreMars via vertical flight, including two optimized Ingenuity-sized helicopters proposed to retrieve samples for the 2028 Mars Sample Return mission. To aid in the design process for the two proposed Sample Retrieval Helicopters, both heritage and optimized, increased diameter rotors were tested at the NASA Jet Propulsion Laboratory in the 25-ft Space Simulator. Three test campaigns were performed using the Ingenuity rotors and optimized Sample Retrieval Helicopter (SRH) rotors for several rotor speeds, densities, configurations, and collectives to identify performance limitations. These three test campaigns included the Ingenuity Engineering Design Model 1 (EDM-1) with and without a cruciform box, Transonic Rotor Test (TRT) rig, and SRH Dual Rotor Test (DRT). Experimental setup, test matrix, data processing, data quality, and performance results for EDM-1, TRT, and DRT campaigns are presented and discussed. Experimental results from the test campaigns will aid in future experimental methods and validation efforts for planetary rotorcraft exploration.
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McGuire, Dennis. "The Revolution in Rotor Design An Historical Review of Elastomeric Bearing Development." In Vertical Flight Society 74th Annual Forum & Technology Display, 1–10. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12796.

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This paper summarizes the early developments that led to laminated elastomeric bearings becoming the principal load-bearing elements in modern helicopter rotor heads. Early helicopters used conventional ball or roller bearings to allow the rotor blade pitch, flap, and lead-lag motions. These rolling element bearings were not well-suited to the small, oscillatory motions required in helicopter rotors. Laminated elastomeric bearings were conceived in the mid-1950s as a better alternative. The basic operating principles of elastomeric bearings for helicopters are explained. Five key innovations, developments, and milestone achievements are identified. These include patents issued to Hinks, Schmidt, and Gorndt et al. The first successful helicopter elastomeric bearing projects are also described. These include the Enstrom F-28 centrifugal force thrust bearing, the Scheutzow Flexhub rotor head, and the Boeing-Vertol Triskelion rotor head. These key early developments led to the first production spherical elastomeric bearing rotor heads and eventually revolutionized helicopter rotor design. Almost all modern helicopter rotor heads use spherical elastomeric bearings to accommodate the blade pitch, flap, and lead-lag motions.
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Richter, Kai, and Erich Schülein. "Boundary Layer Transition Measurements on Hovering Helicopter Rotors by Infrared Thermography." In Vertical Flight Society 70th Annual Forum & Technology Display, 1–13. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9435.

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High speed infrared thermography was applied for boundary layer transition measurements on the upper side of helicopter rotors. The transition detection is based on the analysis of a single instantaneous thermal image of the rotating blade and allows the determination of both the locations of the onset and of the end of the transition region. Measurements were performed on a Mach scaled BO105 model rotor for different rotation frequencies. The transition characteristics are presented and compared to two-dimensional numerical simulations, and the measurement scatter is discussed. Additional transition measurements were performed on the main rotors of the DLR research helicopters Eurocopter BO105 and EC135. The transition behavior of the EC135 rotor blade is presented for different cases and the effect of the contamination of the rotor blade leading edge on the laminar flow is discussed.
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Giovanetti, Eli, and Kenneth Hall. "Optimal Design of Compound Helicopters Using Higher Harmonic Control." In Vertical Flight Society 70th Annual Forum & Technology Display, 1–12. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9553.

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We investigate the optimal design of a compound helicopter comprised of counter-rotating coaxial rotors, a propeller, and optionally a fixed wing. We determine the blade geometry, azimuthal blade pitch inputs, optimal shaft angle (rotor angle of attack), and division of propulsive and lifting forces among the components that minimize the total power for a given flight condition. The optimal design problem is cast as a variational statement that minimizes the sum of induced and viscous power losses for a prescribed lift, propulsive force, and vehicle trim condition. The rotor, propeller, and wing geometry and control inputs are related to the far-field circulation through a lifting line model that accounts for experimentally or computationally determined nonlinear lift and drag polars. The variational statement is discretized using a vortex lattice wake, and the resulting nonlinear constrained optimization problem is solved via Newton iteration. We show that varying the prescribed propulsive force of the system affects the optimal shaft angle and rotor design, and that higher harmonic control reduces total vehicle power loss (inefficiency) in high speed flight by as much as 15 percent. We also show that imposing a maximum allowable lateral lift offset can greatly increase the power loss of the coaxial rotors.
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Ivler, Christina, and Ondrej Juhasz. "Evaluation of Control Allocation Techniques for a Medium Lift Tilt-Rotor." In Vertical Flight Society 71st Annual Forum & Technology Display, 1–20. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10169.

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In a traditional single main rotor helicopter, only 4 controls are available - lateral cyclic, longitudinal cyclic, main rotor collective pitch and tail rotor collective pitch. As such, redundancy is not available as all four controls are needed to maneuver the aircraft in the four control axes - pitch, roll, yaw and heave. In contrast, high speed rotorcraft configurations (such as tilt-rotors and compound helicopters) have multiple redundant control effectors. The strategy for applying these control effectors, and in which proportion, is called 'control allocation'. This paper provides an evaluation and comparison of different control allocation methods, applied to a medium lift tilt rotor. The control allocation methods are evaluated based on a comprehensive set of time and frequency domain metrics, as well as robustness criteria. In addition to evaluation of standard control allocation methods, several control allocation methods are further developed and evaluated for reducing flap motion of the rotors. A piloted fixed base simulation is performed, and pilot comments and data are presented. The paper concludes with discussion of the results and trade-offs of the most effective control allocation techniques.
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Ahci, Elif, Ulrich Denecke, Stefan Emmerling, Gerald Kuntze-Fechner, and Patrice Rauch. "Evolution of Fenestron Development in Terms of Safety, Design and Substantiation Characteristics." In Vertical Flight Society 71st Annual Forum & Technology Display, 1–13. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10250.

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Since the installation on Gazelle in 1968, great experience has been acquired by Airbus Helicopters on Fenestron™ technology. The experience gained after 18.5 million flight hours during the past decades allowed defining clear guidelines for the enhancement of design and substantiation principles applied on this technology. This is a progression which automatically serves as a safety improvement and contributes strongly in reduction of the number of accidents caused by conventional tail rotors. This paper summarizes the evolution of design technologies applied for the Fenestron™ tail rotors in Airbus Helicopters and specifies the results of recent research and development work conducted in this area. First part of the paper mainly focuses on operational safety improvement by the Fenestron™ concept and makes comparisons with aircrafts equipped with a conventional tail rotor. The second part gives detailed information about the design features and strength substantiation of the EC145 T2 Fenestron™ rotor. The composite Fenestron™ blade with the newest technology is chosen as an exemplary part to describe the design improvements and to show the application of the new substantiation rules. The development and certification logic is presented mainly from the perspective of strength substantiation. The development approach followed by Airbus Helicopters which primarily bases on mixture of analysis and tests by taking into account the previous in-service experience is described subsequently.
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Mercier, Christian, Marc Gazzino, and Marc Mugnier. "State of the Art of Helicopter Hybrid Propulsion." In Vertical Flight Society 72nd Annual Forum & Technology Display, 1–6. The Vertical Flight Society, 2016. http://dx.doi.org/10.4050/f-0072-2016-11519.

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State of the art of Helicopter hybrid Propulsion perspectives is presented. As done in the car industry, it can be envisaged replacing thermal energy necessary for helicopter propulsion and sustentation by electrical energy. Improvements on electrical technologies allow proposing electrical systems with attractive power to mass ratio to complement the thermal engine providing the mechanical power necessary for the helicopter propulsion. The differences between automotive functions devoted to hybridization and these possible in the case of a helicopter are explained. The different architectures (on turbine or on helicopter side) are reviewed and examples of possible applications on classical architecture helicopters (with main and antitorque rotors) are given, not only the case of AH light helicopter autorotation management improver successfully tested in 2011. The requirements on the electrical system for industrial applications are reviewed: electrical motor and power electronics, cooling systems, energy storage, resulting in development priorities.
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Kus, Adrian, Sascha Schneider, Martin Hollands, Raphael Rammer, Oliver Dieterich, and Martijn Priems. "GRC1: An Advanced Five-Bladed Bearingless Main Rotor Dynamics and Acoustics from Draft to Flight Test." In Vertical Flight Society 74th Annual Forum & Technology Display, 1–13. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12754.

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Funded by the European research program Clean Sky Green Rotorcraft (GRC), a new five-bladed bearingless main rotor demonstrator has been developed and tested between 2014 and 2016 at Airbus Helicopters, hereafter denoted as GRC1 rotor. While inheriting rotor controls, control cuff, flexbeam and lead-lag damper from the Bluecopter™ main rotor, the rotor blade itself was developed from scratch within the research project. Main target was to achieve an ecofriendly design by simultaneously reducing acoustic signature, fuel consumption and vibratory loads while optimizing manufacturing costs. This could be achieved by proper balancing the requirements of the technical disciplines acoustics, aerodynamics, dynamics, loads, performance and handling qualities. While these targets have been achieved, demonstrated by ground and flight tests, excellent agreement between numerical predictions and test results was achieved. This paper provides an overview on the aeromechanics, acoustics and performance aspects after summarizing the evolution of bearingless main rotors at Airbus Helicopters.
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Skladanek, Yan, Laurent Boucherie, Bernard Benoit, and Paul Cranga. "Advanced Beam Modeling Applied to Articulated Rotor - Implementation in HOST Aeromechanic Simulation Tool." In Vertical Flight Society 70th Annual Forum & Technology Display, 1–12. The Vertical Flight Society, 2014. http://dx.doi.org/10.4050/f-0070-2014-9496.

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Advanced beam modeling is one of the main research topics for Rotorcraft Comprehensive Analysis (RCA) simulation tools enhancement. HOST is the aeromechanic code developed by AIRBUS HELICOPTERS over the last 25 years and it is continuously upgraded to fit to the new needs. To study the most recent evolutions of rotors and blades (such as Blue Edge™ blades) new modeling strategies must be foreseen including an advanced model featuring all geometric and coupling effects of beam in centrifugal environment and a global modeling approach within the RCA software hosting all the simulation tools required for aircraft development. In this scope Airbus Helicopters has launched the development of Beam Advance Model (BAM) and its integration in HOST. After a short recall of BAM theoretical basis, this paper discusses the implementation strategy chosen for such an advanced model, presents the validation of the method and provides the first available results coming from a full integrated trim calculation on articulated rotor. Dynamic results on Blue Edge™ blade whirl tower test demonstrate the relevancy of BAM model while the validation of its implementation in HOST is presented on full-scale straight bladed rotors.
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Reports on the topic "Rotors (Helicopters)"

1

Pogorzelski, Ronald J., and Vaughn P. Cable. Helicopter Rotor Antenna. Fort Belvoir, VA: Defense Technical Information Center, June 2001. http://dx.doi.org/10.21236/ada395307.

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Allen, Luke, Joon Lim, Robert Haehnel, and Ian Dettwiller. Helicopter rotor blade multiple-section optimization with performance. Engineer Research and Development Center (U.S.), June 2021. http://dx.doi.org/10.21079/11681/41031.

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This paper presents advancements in a surrogate-based, rotor blade design optimization framework for improved helicopter performance. The framework builds on previous successes by allowing multiple airfoil sections to designed simultaneously to minimize required rotor power in multiple flight conditions. Rotor power in hover and forward flight, at advance ratio 𝜇 = 0.3, are used as objective functions in a multi-objective genetic algorithm. The framework is constructed using Galaxy Simulation Builder with optimization provided through integration with Dakota. Three independent airfoil sections are morphed using ParFoil and aerodynamic coefficients for the updated airfoil shapes (i.e., lift, drag, moment) are calculated using linear interpolation from a database generated using C81Gen/ARC2D. Final rotor performance is then calculated using RCAS. Several demonstrative optimization case studies were conducted using the UH-60A main rotor. The degrees of freedom for this case are limited to the airfoil camber, camber crest position, thickness, and thickness crest position for each of the sections. The results of the three-segment case study show improvements in rotor power of 4.3% and 0.8% in forward flight and hover, respectively. This configuration also yields greater reductions in rotor power for high advance ratios, e.g., 6.0% reduction at 𝜇 = 0.35, and 8.8% reduction at 𝜇 = 0.4.
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Wenren, Yonghu, Joon Lim, Luke Allen, Robert Haehnel, and Ian Dettwiler. Helicopter rotor blade planform optimization using parametric design and multi-objective genetic algorithm. Engineer Research and Development Center (U.S.), December 2022. http://dx.doi.org/10.21079/11681/46261.

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In this paper, an automated framework is presented to perform helicopter rotor blade planform optimization. This framework contains three elements, Dakota, ParBlade, and RCAS. These elements are integrated into an environment control tool, Galaxy Simulation Builder, which is used to carry out the optimization. The main objective of this work is to conduct rotor performance design optimizations for forward flight and hover. The blade design variables manipulated by ParBlade are twist, sweep, and anhedral. The multi-objective genetic algorithm method is used in this study to search for the optimum blade design; the optimization objective is to minimize the rotor power required. Following design parameter substitution, ParBlade generates the modified blade shape and updates the rotor blade properties in the RCAS script before running RCAS. After the RCAS simulations are complete, the desired performance metrics (objectives and constraints) are extracted and returned to the Dakota optimizer. Demonstrative optimization case studies were conducted using a UH-60A main rotor as the base case. Rotor power in hover and forward flight, at advance ratio 𝜇𝜇 = 0.3, are used as objective functions. The results of this study show improvement in rotor power of 6.13% and 8.52% in hover and an advance ratio of 0.3, respectively. This configuration also yields greater reductions in rotor power for high advance ratios, e.g., 12.42% reduction at 𝜇𝜇 = 0.4.
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4

Morino, Luigi, Slobodan Sipcic, and Mark Downey. Unsteady Free-Wake Viscous Aerodynamic Analysis of Helicopter Rotors. Fort Belvoir, VA: Defense Technical Information Center, November 1989. http://dx.doi.org/10.21236/ada217166.

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Fries, Joseph. The Effect of Helicopter Main Rotor Blade Damage on the Rotor Disk (Whole Rotor) Motion. Fort Belvoir, VA: Defense Technical Information Center, June 2000. http://dx.doi.org/10.21236/ada378211.

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Rivera-Casillas, Peter, and Ian Dettwiller. Neural Ordinary Differential Equations for rotorcraft aerodynamics. Engineer Research and Development Center (U.S.), April 2024. http://dx.doi.org/10.21079/11681/48420.

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High-fidelity computational simulations of aerodynamics and structural dynamics on rotorcraft are essential for helicopter design, testing, and evaluation. These simulations usually entail a high computational cost even with modern high-performance computing resources. Reduced order models can significantly reduce the computational cost of simulating rotor revolutions. However, reduced order models are less accurate than traditional numerical modeling approaches, making them unsuitable for research and design purposes. This study explores the use of a new modified Neural Ordinary Differential Equation (NODE) approach as a machine learning alternative to reduced order models in rotorcraft applications—specifically to predict the pitching moment on a rotor blade section from an initial condition, mach number, chord velocity and normal velocity. The results indicate that NODEs cannot outperform traditional reduced order models, but in some cases they can outperform simple multilayer perceptron networks. Additionally, the mathematical structure provided by NODEs seems to favor time-dependent predictions. We demonstrate how this mathematical structure can be easily modified to tackle more complex problems. The work presented in this report is intended to establish an initial evaluation of the usability of the modified NODE approach for time-dependent modeling of complex dynamics over seen and unseen domains.
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Crespo da Silva, Marcelo R. Response and Stability Analysis of Helicopter Rotor Blades Using Computerized Symbolic Manipulation. Fort Belvoir, VA: Defense Technical Information Center, May 1991. http://dx.doi.org/10.21236/ada238660.

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8

Hayes, Christoper D. Joint Helicopter Command: The `Purple' Evolution of Rotary-Wing Aviation. Fort Belvoir, VA: Defense Technical Information Center, October 2006. http://dx.doi.org/10.21236/ada463638.

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9

Kim, Ki C. Analytical Calculation of Helicopter Main Rotor Blade Flight Loads in Hover and Forward Flight. Fort Belvoir, VA: Defense Technical Information Center, April 2004. http://dx.doi.org/10.21236/ada423149.

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10

Srinivasan, Ganapathi R. A Free-Wake Euler and Navier-Stokes CFD Method and its Application to Helicopter Rotors Including Dynamic Stall. Fort Belvoir, VA: Defense Technical Information Center, November 1993. http://dx.doi.org/10.21236/ada278000.

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