Multi-hedral rotary wing

Abstract

A rotary-wing includes a multi-hedral tip section which utilizes a distribution of anhedral and/or dihedral angles that cause a tip vortex to be axially displaced relative to a region on a following blade such that the tip vortex generally avoids influence upon the following blade.

1 . A rotary aerodynamic member comprising: 
 a first segment which defines a first axis;    a second segment which defines a second axis transverse said first axis; and    a third segment which defines a third axis transverse said second axis.    
   
   
       2 . The rotary aerodynamic member as recited in  claim 1 , wherein said first axis is defined parallel to a leading edge of said first segment.  
   
   
       3 . The rotary aerodynamic member as recited in  claim 1 , wherein said first axis is parallel to a trailing edge of said first segment.  
   
   
       4 . The rotary aerodynamic member as recited in  claim 1 , wherein said first axis is parallel to a feathering axis of said first segment.  
   
   
       5 . The rotary aerodynamic member as recited in  claim 1 , wherein said second axis extends at least partially above said first axis.  
   
   
       6 . The rotary aerodynamic member as recited in  claim 1 , wherein said second axis extends toward a first side of said first axis and said third axis extends toward a second side of said first axis.  
   
   
       7 . The rotary aerodynamic member as recited in  claim 1 , wherein said second axis extends toward a first side of said first axis and said third axis extends toward said first side of said first axis.  
   
   
       8 . The rotary aerodynamic member as recited in  claim 1 , wherein said second segment is a dihedral segment and said third segment is an anhedral segment.  
   
   
       9 . The rotary aerodynamic member as recited in  claim 1 , wherein said second segment and said third segment form a rotor blade tip section.  
   
   
       10 . The rotary aerodynamic member as recited in  claim 1 , wherein said second segment and said third segment form a propeller tip section.  
   
   
       11 . The rotary aerodynamic member as recited in  claim 1 , further comprising a fourth segment generally parallel to said first segment.  
   
   
       12 . The rotary aerodynamic member as recited in  claim 1 , wherein said second segment and said third segment are two of an infinite number of sections.  
   
   
       13 . A rotor blade assembly comprising: 
 a first rotor blade segment which defines a first axis;    a second segment which defines a dihedral relative said first axis; and    a third segment which defines an anhedral relative said first axis.    
   
   
       14 . The rotor blade assembly as recited in  claim 13 , wherein said first rotor blade segment comprises a rotor blade root section.  
   
   
       15 . The rotor blade assembly as recited in  claim 13 , wherein said third rotor blade segment comprises a distal end of a rotor blade tip section.  
   
   
       16 . The rotor blade assembly as recited in  claim 13 , further comprising a fourth rotor blade segment between said second rotor blade segment and said third rotor blade segment.  
   
   
       17 . A method of minimizing an influence of a tip vortex formed by a preceding rotary-wing upon a following rotary-wing comprising the step of: 
 (1) axially displacing a multiple of segments of the preceding and receding rotary-wings relative a first axis to axially displace a tip vortex formed by the preceding rotary-wing relative the following rotary-wing.    
   
   
       18 . A method as recited in  claim 17 , wherein step (1) further comprises the step of: 
 displacing at least one of the multiple of segments above the first axis and at least one of the multiple of segments below the first axis.