Results 251 to 260 of about 231,082 (310)

Investigation on rub-impact response characteristics of gas generator rotor system under external excitation. [PDF]

Sci Rep
Zhang H, Liu T, Zhao H, Wang Q.
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Particle swarm optimization of synergetic controller and sliding-mode extreme seeking controller for wind power generation system. [PDF]

Sci Rep
Khatir A, Dida A, Babes B, Albalawi F, Awoke YA.   +4 more
europepmc   +1 more source

Winding fault detection based on current information of induction motors. [PDF]

Sci Rep
Liu F, Hou C, Liang L, Zhang X, Liu D, Wang X.   +5 more
europepmc   +1 more source

Experimental and numerical investigation of endwall flow control through air injection in a contra rotating fan. [PDF]

Sci Rep
Sadoddin M, Khaleghi H.
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Helicopter Main-Rotor/Tail-Rotor Interaction

Journal of the American Helicopter Society, 2000
Preliminary results from a study to model the interaction aerodynamics and aeroacoustics of the main and tail rotor of a helicopter in subsonic flow are presented. The configurations studied are: 1) two bladed main and tail rotors in hover, and 2) a four-bladed main rotor and two-bladed tail rotor in climbing flight.
Yin, J., Ahmed, S.R.
openaire   +3 more sources

Aerodynamics and aeroacoustics of helicopter main-rotor/tail-rotor interaction

5th AIAA/CEAS Aeroacoustics Conference and Exhibit, 1999
Preliminary results from an ongoing effort to model the interaction aerodynamics and aeroacoustics of main- and tail rotor of a helicopter in subsonic flow are presented. The configurations studied are a) a two-blade main- and tail rotor in hover, and b) a four-blade main- and a two-blade tail rotor in climb flight.
Ahmed, S.R., Yin, J.
openaire   +2 more sources

Titanium UTTAS Main Rotor Blade

Journal of the American Helicopter Society, 1976
A description of the design philosophy leading to the development of a high performance rotor blade for the Army UTTAS helicopter is presented. The Army mission requirements of 550 fpm rate‐of‐climb at 4000 ft, 95° conditions and a 1.75 g maneuver at 150 knots translate into Figure of Merit and aeroelastic achievements beyond those of existing rotors.
Peter Arcidiacono, Robert Zincone
openaire   +1 more source

Main Rotor Gearbox Oil Cooling System Design

Proceedings of the Vertical Flight Society 79th Annual Forum, 2023
This paper details the design process for a Main Rotor Gearbox Oil Cooling System and recommends techniques to optimise future designs. It covers the drive methods which must be considered in the design, along with the optimum heat exchanger and airflow path arrangements to meet the design requirements.
David Gore, John Kerr
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Main Rotor Yoke Cracking

1992
Abstract The 4340 steel main rotor yoke of a helicopter failed during a hovering exercise. Visual examination of the yoke revealed no evidence of gross external damage. Visual fracture surface examination, macrofractography, scanning electron micrography, and metallography of a section cut from the yoke in the region of the cracking ...
S.R. Lamb, G. Clerk
openaire   +1 more source