Tapered/segmented flaps for rotor blade-vortex interaction (BVI) noise and vibration reduction
Number of patents in Portfolio can not be more than 2000
United States of America Patent
Stats
-
Nov 12, 2002
Grant Date -
N/A
app pub date -
Aug 16, 2001
filing date -
Aug 16, 2001
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a segmented trailing edge flap located near the tip of each of the rotorcraft's rotor blades. The various flap segments may be independently actuated according to flap deflections schedules which are tailored to address a particular operating regime with maximum efficiency and effectiveness. Through the careful azimuth-dependent independent actuation of the flap segments, blade tip vortices which are the primary source for BVI noise are (a) made weaker and (b) pushed farther away from the rotor disk (that is, larger blade-vortex separation distances are achieved), resulting in lower BVI noise.
First Claim
Family
International Classification(s)
Cited Art Landscape
Patent Citation Ranking
Recipient Email Address
Recipient Email Address
Comment
Recipient Email Address
Add to Portfolio(s)
To add this patent to one, or more, of your portfolios, simply click the add button.
This Patent is in these Portfolios:
Add to additional portfolios:
Last Refreshed On:
Changes done successfully