Design and Development of a Four-Bladed Tail Rotor System for the USMC H-1 Upgrade Program

Sehgal, Ajay Kumar; Boyle, Eric

doi:10.4050/jahs.49.99

Cited by 2 publications

(3 citation statements)

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“…In equation ( 34), iqxv n is the sound pressure gradient that is obtained from equation (25). The sound pressure gradient can be calculated by equation (35) [23]…”

Section: Calculation Of the Sound Pressure Gradientmentioning

confidence: 99%

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Acoustic scattering effect prediction of helicopter fuselage based on BEM and convective FW–H equation

Wang

Huang

2022

Acta Acust.

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The main acoustic noise source of helicopters is supposed to be the rotor blades, but the scattering effect of the helicopter fuselage sometimes cannot be ignored. For the accuracy of acoustic noise prediction and the research on the scattering affections of the helicopter fuselage, an FWH–BEM Method (FBM) based on convective FW–H equation and boundary element method (BEM) is presented for the prediction of the noise scattering effects of helicopter fuselage and the approach to the calculation of a helicopter’s acoustic noise field. In this paper, different fuselage models are adopted for the comparisons of the acoustic noise scattered by different types of fuselages. According to the discovery that helicopter fuselages with sharp edges can bring more significant acoustic scattering effects, a research on the influence of radius of curvature (RC), which reflects the sharpness of fuselage sharp edges, is also carried out. In addition, the acoustic scattering effects of the same type of fuselage but with different length, width and height ratios are also compared for discovering the influences of the fuselage size. The presented FBM is efficient to analyze the acoustic scattering effects of the helicopter fuselage and predict the acoustic noise field, taking both the rotor and the fuselage into account. Besides, the research in this paper leads to the discovery of the influence factors of the acoustic scattering effects and helps the proper selection of the fuselage in a helicopter stealth design.

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“…In equation ( 34), iqxv n is the sound pressure gradient that is obtained from equation (25). The sound pressure gradient can be calculated by equation (35) [23]…”

Section: Calculation Of the Sound Pressure Gradientmentioning

confidence: 99%

“…The HUEY fuselage model established in this paper is shown in Figure 3, according to the design of the HUEY helicopter [25]. The fuselage model mainly includes the main part of the OH-6 fuselage while the tail of the fuselage is simplified.…”

Section: Models and Simulation Environments 31 Geometry Models Of The...mentioning

confidence: 99%

Acoustic scattering effect prediction of helicopter fuselage based on BEM and convective FW–H equation

Wang

Huang

2022

Acta Acust.

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“…The tail rotor operates in an adverse aerodynamic environment with various cyclic loads and moments, which makes it vulnerable to damage, and in extreme cases, result in its complete failure. In fact, tail rotor design is an important area of helicopter structural design (Banerjee, 1984;Zion, 1997;Sehgal and Boyle, 2004). In the absence of sufficient tail rotor thrust to counteract the main rotor torque, the helicopter becomes very unstable, leading to catastrophic failure.…”

Section: Introductionmentioning

confidence: 99%

On the effect of mass and stiffness unbalance on helicopter tail rotor system behavior

Singh

Pawar

Ganguli

et al. 2008

Aircraft Engineering and Aerospace Technology

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2008),"On the effect of mass and stiffness unbalance on helicopter tail rotor system behavior", Aircraft Engineering and Aerospace Technology, Vol. 80 Iss 2 pp. 129 -138 Permanent link to this document: http://dx. Access to this document was granted through an Emerald subscription provided by emerald-srm:448207 [] For AuthorsIf you would like to write for this, or any other Emerald publication, then please use our Emerald for Authors service information about how to choose which publication to write for and submission guidelines are available for all. Please visit www.emeraldinsight.com/authors for more information. About Emerald www.emeraldinsight.comEmerald is a global publisher linking research and practice to the benefit of society. The company manages a portfolio of more than 290 journals and over 2,350 books and book series volumes, as well as providing an extensive range of online products and additional customer resources and services.Emerald is both COUNTER 4 and TRANSFER compliant. The organization is a partner of the Committee on Publication Ethics (COPE) and also works with Portico and the LOCKSS initiative for digital archive preservation. AbstractPurpose -This study aims to investigate the effects of mass and stiffness imbalance in a tail rotor induced by damage in forward flight. Design/methodology/approach -An aeroelastic analysis based on finite element in space and time and capable of modeling dissimilar blades is carried out to study the effect of damage occurring in one, two, and three blades in a four-bladed tail rotor system in forward flight. The effect of damage growth on vibratory hub loads and blade responses is studied using a comprehensive aeroelastic code. Findings -The diagnostic chart which is the summary of damage analysis of tail rotor shows that the root hub vibration spectrum gives enough indication to predict damage growth in the tail rotor blade. Hence, this can be useful towards development of health monitoring system for tail rotor blades. Originality/value -The proposed analysis helps in understanding the basic physics behind the damaged tail rotor and also gives qualitative assessment of damaged tail rotor where obtaining the flight test data with damaged tail rotor is difficult.

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Design and Development of a Four-Bladed Tail Rotor System for the USMC H-1 Upgrade Program

Cited by 2 publications

References 1 publication

Acoustic scattering effect prediction of helicopter fuselage based on BEM and convective FW–H equation

Acoustic scattering effect prediction of helicopter fuselage based on BEM and convective FW–H equation

On the effect of mass and stiffness unbalance on helicopter tail rotor system behavior

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