Rotorcraft rotor blade assembly
A rotorcraft rotor blade assembly includes a stub spar extending less than a full span of the rotor blade assembly. An upper skin portion extends substantially the full span of the rotor blade assembly. A lower skin portion extends substantially the full span of the rotor blade assembly. The stub spar is positioned between the upper skin portion and the lower skin portion.
1. A rotorcraft rotor blade assembly comprising:
a stub spar extending less than 80% of a full span of the rotor blade assembly;
an upper skin portion extending substantially the full span of the rotor blade assembly;
a lower skin portion extending substantially the full span of the rotor blade assembly, wherein the stub spar is positioned between the upper skin portion and the lower skin portion; and
the stub spar tapers as the stub spar extends away from an inboard end of the rotor blade assembly such that:
at a cross-section located closer to the inboard end of the rotor blade assembly, a thickness of the stub spar is substantially greater than a thickness of the upper skin portion or a thickness of the lower skin portion,
at a cross-section located away from to the inboard end of the rotor blade assembly, the thickness of the stub spar is substantially equal to or less than a thickness of the upper skin portion or a thickness of the lower skin portion, and
at a cross-section located nearer to the outboard end of the rotor blade assembly, there is no stub spar.
2. The rotor blade assembly of claim 1 , wherein the stub spar extends only up to 50% of the full span of the rotor blade assembly.
3. The rotor blade assembly of claim 2 , wherein the stub spar extends only between 10% and 50% of the full span of the rotor blade assembly.
4. The rotor blade assembly of claim 1 , wherein, at a location away from the inboard end of the rotor blade assembly, a thickness of the stub spar is substantially less than the thickness of the upper skin portion or the thickness of the lower skin portion.
5. The rotor blade assembly of claim 1 , wherein the stub spar is configured to join the upper skin portion to the lower skin portion.
6. The rotor blade assembly of claim 1 , wherein the stub spar excludes material configured to support centrifugal loads of a rotorcraft rotor assembly.
7. The rotor blade assembly of claim 6 , wherein a thickness of each of the upper skin portion and the lower skin portion is configured to support substantially 30% or more of the centrifugal loads by substantially 40% or less of the full span of the rotor blade assembly.
8. The rotor blade assembly of claim 1 , wherein the stub spar excludes torsional material or material configured to support centrifugal loads of a rotorcraft rotor assembly.
9. The rotor blade assembly of claim 1 , wherein the stub spar comprises at least one of a closed hollow cross-section of structural composite material, an open hollow cross section of composite material or a non-hollow cross-section.
10. The rotor blade assembly of claim 9 , wherein the stub spar comprises filler material.
11. The rotor blade assembly of claim 1 , wherein each of the upper skin portion and the lower skin portion include a composite material comprising a centrifugal material aligned substantially span-wise from the inboard end to more than 50% of the full span of the full span of the rotor blade assembly, a torque material torsionally wound around the upper skin portion and the lower skin portion from the inboard end to substantially the full span of the rotor blade assembly, and a shearing material aligned chord-wise from the inboard end to substantially all or part of the full span of the rotor blade assembly.