Under normal operating flight procedures, a helicopter main rotor revolves at a strictly controlled speed. The centrifugal forces generated keep balance with the aerodynamic loads with the result that the rotor blade motion, in particular the blade flapping, is maintained under control. To reach the normal rotational speeds the rotor must of course pass through lower speeds, both during acceleration and deceleration, and during these periods the blades can fall prey to the phenomenon of blade sailing. With this, not inconsiderable aerodynamic loads can be generated when the helicopter is operating in high winds and with the reduced centrifugal forces because of the lower rotor speeds, the blade flapping motion can build up to dangerously large deflections.
Theoretical and Experimental Investigation into the Rotor Blade Aeroelastic Behaviour of a Shipborne Helicopter During Rotor Engagement and Braking
1995
10 pages
Report
Keine Angabe
Englisch
Aircraft , Test Facilities & Equipment , Aeroelasticity , Air flow , Aircraft carriers , Flow distribution , Helicopters , Rotary wings , Rotor blades , Wind effects , Wind tunnel tests , Blade-vortex interaction , Braking , Centrifugal force , Flapping , Helicopter performance , Scale models , Wind velocity , Foreign technology
British Library Conference Proceedings | 1995
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Online Contents | 2012
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