초록 ▼

A main rotor blade assembly with a high negative pitching moment airfoil section having a pitching moment coefficient beyond (more negative than)-0.035 at Mach Numbers below 0.80 and a blade taper of 1:5 or greater.. The main rotor blade preferably limits blade torsional bending and an aft loaded t

A main rotor blade assembly with a high negative pitching moment airfoil section having a pitching moment coefficient beyond (more negative than)-0.035 at Mach Numbers below 0.80 and a blade taper of 1:5 or greater.. The main rotor blade preferably limits blade torsional bending and an aft loaded tip airfoils to approximately 'no more' than that of conventional effective rotor blade designs based on conventional tip airfoil sections.

대표청구항 ▼

What is claimed is: 1. A main rotor blade assembly comprising: an inboard section, an intermediate section outboard of said inboard section, and an outboard section outboard of said intermediate section, said outboard section includes an airfoil section having over an entire length a pitching momen

What is claimed is: 1. A main rotor blade assembly comprising: an inboard section, an intermediate section outboard of said inboard section, and an outboard section outboard of said intermediate section, said outboard section includes an airfoil section having over an entire length a pitching moment coefficient more negative than-0.035 at Mach numbers below 0.80 and a chord taper section having a taper ratio of at least 3:1, said airfoil section and said chord taper section each extends to a distal end of a blade tip. 2. The main rotor blade assembly as recited in claim 1, wherein said blade tip comprises a straight tip. 3. The main rotor blade assembly as recited in claim 1, wherein said blade tip comprises a sheared tip. 4. The main rotor blade assembly as recited in claim 1, wherein said blade tip comprises a swept tip. 5. The main rotor blade assembly as recited in claim 4, wherein said swept tip includes an approximately 30 degree sweep. 6. The main rotor blade assembly as recited in claim 4, wherein said swept tip extends over an outer 8% of a main rotor blade span defined from said inboard section to said distal end of said blade tip. 7. The main rotor blade assembly as recited in claim 5, wherein said swept tip includes a mass balance counterweight forward of an airfoil section elastic axis. 8. The main rotor blade assembly as recited in claim 1, wherein said chord taper is applied to an outer 8% of a main rotor blade span defined from said inboard section to said distal end of said blade tip. 9. The main rotor blade assembly as recited in claim 1, wherein said chord taper section comprises a chord taper applied to an outer 10% of a main rotor blade span defined from said inboard section to said distal end of said blade tip. 10. The main rotor blade assembly as recited in claim 1, wherein said chord taper section comprises a progressive non-linear taper. 11. The main rotor blade assembly as recited in claim 1, wherein said chord taper section comprises a linear compound taper. 12. The main rotor blade assembly as recited in claim 1, wherein said chord taper section is defined relative to an inboard tapered blade chord dimension of said chord taper section divided by a smaller outboard tapered blade chord dimension of said chord taper section, said inboard tapered blade chord dimension generally equivalent to a maximum blade chord dimension of said intermediate section. 13. The main rotor blade assembly as recited in claim 12, wherein said chord taper section is defined relative to an inboard tapered blade chord dimension of said chord taper section divided by a smaller outboard tapered blade chord dimension of said chord taper section, said outboard tapered blade chord dimension less than said maximum blade chord dimension of said intermediate section. 14. The main rotor blade assembly as recited in claim 1, wherein said outboard section comprises said distal end of said main rotor blade assembly. 15. The main rotor blade assembly as recited in claim 1, wherein said smaller blade chord dimension of said outboard section is at said distal end of said main rotor blade assembly. 16. The main rotor blade assembly of claim 1, wherein said airfoil section extends along a first outer percentage of a main rotor blade span defined from said inboard section to said distal end of said blade tip and said chord taper section extends along said first outer percentage of said main rotor blade span. 17. The main rotor blade assembly of claim 1, wherein said airfoil section extends along a first outer percentage of a main rotor blade span defined from said inboard section to said distal end of said blade tip while said chord taper section extends along a second outer percentage of said main rotor blade span, said first outer percentage of said main rotor blade span different than said second outer percentage of said main rotor blade span. 18. The main rotor blade assembly as recited in claim 1, wherein said outboard section transitions into said blade tip. 19. The main rotor blade assembly of claim 1, wherein said inboard section defines an inboard section maximum chord, said intermediate section defines an intermediate section maximum chord, and said outboard section defines an outboard section maximum chord, said outboard section maximum chord no greater than equivalent to said inboard section maximum chord and said intermediate section maximum chord. 20. A main rotor blade assembly for a rotary wing aircraft comprising: an inboard section, an intermediate section outboard of said inboard section, and an outboard section outboard of said intermediate section, said outboard section comprises an airfoil section having over an entire length a pitching moment coefficient more negative than-0.035 at mach numbers below 0.80 and a chord taper section having a taper ratio of at least 3 to 1, said chord taper section defined relative to an inboard tapered blade chord dimension of said chord taper section divided by a smaller outboard tapered blade chord dimension of said chord taper section, said inboard tapered blade chord dimension generally equivalent to a maximum blade chord dimension of said intermediate section, said airfoil section and said chord taper section each extends to a distal end of a blade tip. 21. The main rotor blade assembly of claim 20, wherein said airfoil section extends along an outer 25% of said main rotor blade span while said chord taper section extends along an outer 20% of a main rotor blade span defined from said inboard section to said distal end of said blade tip. 22. The main rotor blade assembly of claim 20, wherein said airfoil section extends along an outer 15% of said main rotor blade span while said chord taper section extends along an outer 10% of a main rotor blade span defined from said inboard section to said distal end of said blade tip. 23. The main rotor blade assembly of claim 20, wherein said airfoil section extends along an outer 10% of said main rotor blade span while said chord taper section extends along an outer 8% of a main rotor blade span defined from said inboard section to said distal end of said blade tip. 24. The main rotor blade assembly as recited in claim 20, wherein said chord taper section comprises a progressive non-linear taper 25. The main rotor blade assembly as recited in claim 20, wherein said chord taper section comprises a linear compound taper. 26. The main rotor blade assembly as recited in claim 20, wherein said outboard section comprises said distal end of said main rotor blade assembly. 27. The main rotor blade assembly of claim 20, wherein said smaller blade chord dimension of said outboard section is at said distal end of said main rotor blade assembly. 28. The main rotor blade assembly of claim 20, wherein said airfoil section extends along a first outer percentage of a main rotor blade span defined from said inboard section to said distal end of said blade tip and said chord taper section extends along said first outer percentage of said main rotor blade span. 29. The main rotor blade assembly of claim 20, wherein said airfoil section extends along a first outer percentage of a main rotor blade span defined from said inboard section to said distal end of said blade tip while said chord taper section extends along a second outer percentage of said main rotor blade span, said first outer percentage of said main rotor blade span different than said second outer percentage of said main rotor blade span. 30. The main rotor blade assembly of claim 20, wherein said inboard section defines an inboard section maximum chord, said intermediate section defines an intermediate section maximum chord, and said outboard section defines an outboard section maximum chord, said outboard section maximum chord no greater than equivalent to said inboard section maximum chord and said intermediate section maximum chord. 31. A method of fabricating a rotary-wing aircraft main rotor blade comprising the steps of: providing the main rotor blade with an inboard section, an intermediate section outboard of said inboard section, and an outboard section outboard of said intermediate section said outboard section comprising an outer airfoil section having over an entire length a pitching moment coefficient more negative than-0.035 at Mach numbers below 0.80 over a prescribed length, said airfoil section extends to a distal end of a blade tip; and tapering a blade chord of the main rotor blade over at least a portion of the prescribed length to define a chord taper section with a taper ratio of at least 3:1 of the outboard section, the chord taper section defined relative to an inboard tapered blade chord dimension of the chord taper section divided by a smaller outboard tapered blade chord dimension of the chord taper section, the inboard tapered blade chord dimension generally equivalent to a maximum blade chord dimension of the intermediate section and said outboard tapered blade chord dimension located at the distal end of the blade tip. 32. A method as recited in claim 31, wherein the prescribed length for the pitching moment coefficient is approximately the outer 25% of a main rotor blade span defined from said inboard section to said distal end of said blade tip and the blade taper occurs over approximately the outer 20% of said main rotor blade span, the prescribed length and the chord taper section each extends to the distal end of a blade tip. 33. The method as recited in claim 31, wherein the prescribed length for the pitching moment coefficient is approximately the outer 15% of a main rotor blade span defined from said inboard section to said distal end of said blade tip and the blade taper occurs over approximately the outer 10% of said main rotor blade span, the prescribed length and the chord taper section each extends to the distal end of a blade tip. 34. A method as recited in claim 31, further comprising locating a mass balance counterweight within the main rotor blade forward of an airfoil section elastic axis to counterbalance the tapered airfoil section. 35. A method as recited in claim 31, wherein the inboard section defines an inboard section maximum chord, the intermediate section defines an intermediate section maximum chord and the outboard section defines an outboard section maximum chord, the outboard section maximum chord no greater than equivalent to the inboard section maximum chord and the intermediate section maximum chord. 36. A main rotor blade assembly comprising: an inboard section, an intermediate section outboard of said inboard section, and an outboard section outboard of said intermediate section, said outboard section comprising an airfoil section having over an entire length a pitching moment coefficient more negative than-0.035 at Mach numbers below 0.80 and a chord taper section at least partially overlapping said airfoil section and having a taper ratio of at least 3:1. 37. The main rotor blade assembly of claim 36, wherein said inboard section defines an inboard section maximum chord, said intermediate section defines an intermediate section maximum chord, and said outboard section defines an outboard section maximum chord, said outboard section maximum chord no greater than equivalent to said inboard section maximum chord and said intermediate section maximum chord.