Results 181 to 190 of about 15,230 (231)
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The Journal of the Acoustical Society of America, 1993
Flow separation behind the notch region of a swept tip of a helicopter rotor blade is reduced by features of the geometry and aerodynamic characteristics of the notch region itself. In particular it has been found beneficial for a forwardly swept leading edge portion to extend at an angle between 30 degrees and 55 degrees from a reference line parallel
Frederick J. Perry, Alan Brocklehurst
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Flow separation behind the notch region of a swept tip of a helicopter rotor blade is reduced by features of the geometry and aerodynamic characteristics of the notch region itself. In particular it has been found beneficial for a forwardly swept leading edge portion to extend at an angle between 30 degrees and 55 degrees from a reference line parallel
Frederick J. Perry, Alan Brocklehurst
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Alloys for spars of rotor blades of helicopters
Metal Science and Heat Treatment, 1974Alloys of the AD33T1, AD35, and V91 types have better corrosion-fatigue properties than alloy AVT1.
E. I. Kutaitseva +3 more
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1973
The development of fiber reinforced resin-bonded structural composite materials has created a new degree of design flexibility for the helicopter engineer. The development and commercial availability of glass fibers, carbon or graphite fibers, and boron fibers, with their attendant widely varying stiffness properties and material densities, enable the ...
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The development of fiber reinforced resin-bonded structural composite materials has created a new degree of design flexibility for the helicopter engineer. The development and commercial availability of glass fibers, carbon or graphite fibers, and boron fibers, with their attendant widely varying stiffness properties and material densities, enable the ...
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Orthogonal Blade-Vortex Interaction on a Helicopter Tail Rotor
AIAA Journal, 2008The orthogonal blade-vortex interaction has been simulated using unsteady Reynolds-averaged Navier-Stokes equations with turbulence closure equations. The cases investigated are relative to an interaction between a lifting blade at a high angle of attack and an orthogonal vortex that travels either head-on or at 45 deg to the leading edge.
Filippone, Antonio; id_orcid 0000-0002-6512-6566 +1 more
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Modeling of Bird Strike on a Composite Helicopter Rotor Blade
58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2017Bird strike is one of the most important concerns about safety in the aviation industry. Bird strikes have been the cause of significant damage to aircraft and rotorcraft structures and the loss of life. In this study, the transient response of a Lagrangian composite helicopter blade impacted by a bird is simulated in LS-DYNA software.
Balkan, Demet +3 more
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A Study of the Aerodynamics of a Helicopter Rotor Blade
Volume 1: Advances in Aerospace Technology, 2019Abstract In any congested area, where a fixed-wing aircraft cannot perform, rotary-wing counterparts are the best-suited option for its vertical take-off and landing capacity. The vibration induced by the rotor blade is a significant problem in helicopter performances.
Uttam K. Chakravarty +1 more
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Helicopter Rotor Blade Flapping and Bending
Aircraft Engineering and Aerospace Technology, 1957THE problem of calculating the motion of a helicopter blade presents many difficulties. Probably the most serious is the lack of knowledge of the aerodynamic forces acting on a blade, but a second major difficulty arises when the equations of motion have to be solved.
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Helicopter Rotor Blade Radar Antenna
Journal of the American Helicopter Society, 1966The helicopter main rotor blade can be used as a scanning radar antenna. Its large aperture gives a narrow azimuth beam‐width and the natural rotor scanning motion provides a fast scan. It is much lighter than conventional antennas and since it is integral with the rotor blade, it induces no additional drag.
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Failure of a Helicopter Main Rotor Blade
1992Abstract A Marine Corps helicopter crash was investigated. Efforts were directed to the failure of one of the main rotor blades that had apparently separated in the air. The apparent failure of a blade integrity monitor (BIM) system was also considered.
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Detection of Density Gradients at Helicopter Rotor Blades in Flight
2002Application of a novel schlieren technique, referred as Background Oriented Schlieren (BOS), with two different helicopter tests are presented. Additionally, another extended method, called Reference free Background Oriented Stereoscopic Schlieren (BOSS), and the differences between these two techniques will be discussed. Experimental studies have been
Raffel, M.,,, Richard, H.
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