Composite airfoil for an aircraft

1. An apparatus for an aircraft, comprising:

an airfoil body extending spanwise between a base end and a tip end, the airfoil body extending lengthwise between a leading edge and a trailing edge, the airfoil body extending widthwise between a first side and a second side, and the airfoil body including a first skin, a second skin, a plurality of first stiffeners and a plurality of second stiffeners;

the first skin disposed at the first side;

the second skin disposed at the second side;

the plurality of first stiffeners comprising first stiffener composite material, the plurality of first stiffeners extending widthwise between and connected to the first skin and the second skin, and each of the plurality of first stiffeners having a first stiffener longitudinal centerline that extends spanwise along the first skin and the second skin;

the plurality of second stiffeners comprising second stiffener composite material, the plurality of second stiffeners extending widthwise between and connected to the first skin and the second skin, and each of the plurality of second stiffeners having a second stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin;

the airfoil body comprising a first section and a second section that is attached to the first section;

the first section comprising a first portion of the first skin, a first portion of the second skin and the plurality of first stiffeners; and

the second section comprising a second portion of the first skin, a second portion of the second skin and the plurality of second stiffeners;

wherein at least one of

the first section is configured as a first monolithic body; or

the second section is configured as a second monolithic body.

2. The apparatus of claim 1 , wherein the first stiffener composite material and the second stiffener composite material each comprises a fiber reinforced polymer.

3. The apparatus of claim 1 , wherein

the first skin comprises first skin composite material; and

the second skin comprises second skin composite material.

4. The apparatus of claim 1 , wherein

each of the plurality of first stiffeners extends spanwise to a distal first stiffener end at the tip end; and

each of the plurality of second stiffeners extends lengthwise to a distal second stiffener end at the leading edge.

5. The apparatus of claim 1 , wherein

the airfoil body further includes a third stiffener and a plurality of fourth stiffeners;

the third stiffener comprises third stiffener composite material, the third stiffener is spanwise between and adjacent the plurality of first stiffeners and the plurality of fourth stiffeners, the third stiffener is widthwise between the first skin and the second skin, and the third stiffener has a third stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin; and

the plurality of fourth stiffeners comprise fourth stiffener composite material, the plurality of fourth stiffeners are widthwise between the first skin and the second skin, and each of the plurality of fourth stiffeners has a fourth stiffener longitudinal centerline that extends spanwise along the first skin and the second skin.

6. The apparatus of claim 5 , wherein

each of the plurality of first stiffeners extend spanwise from the third stiffener to a distal first stiffener end at the tip end;

each of the plurality of fourth stiffeners extend spanwise from the third stiffener to a distal fourth stiffener end at the base end.

7. The apparatus of claim 5 , wherein

one or more of the plurality of second stiffeners are spanwise aligned with the plurality of first stiffeners; and

one or more of the plurality of second stiffeners are spanwise aligned with the plurality of fourth stiffeners.

8. The apparatus of claim 1 , wherein

the leading edge includes a first segment and a second segment;

the first segment is arranged at the tip end;

the second segment is arranged at the base end and lengthwise recessed inward from the first segment; and

the plurality of second stiffeners are arranged along the second segment.

9. The apparatus of claim 1 , wherein the first section is mechanically attached to the second section.

10. The apparatus of claim 1 , further comprising:

a fitting including a mount and a shaft;

the mount received within a cavity of and attached to the airfoil body; and

the shaft projecting away from the airfoil body to a distal shaft end.

11. The apparatus of claim 1 , further comprising an aircraft stabilizer comprising the airfoil body.

12. An apparatus for an aircraft, comprising:

an airfoil body extending spanwise between a base end and a tip end, the airfoil body extending lengthwise between a leading edge and a trailing edge, the airfoil body extending widthwise between a first side and a second side, and the airfoil body including a first skin, a second skin, a plurality of first stiffeners and a plurality of second stiffeners;

the first skin disposed at the first side;

the second skin disposed at the second side;

the plurality of first stiffeners comprising first stiffener composite material, the plurality of first stiffeners extending widthwise between and connected to the first skin and the second skin, and each of the plurality of first stiffeners having a first stiffener longitudinal centerline that extends spanwise along the first skin and the second skin;

the plurality of second stiffeners comprising second stiffener composite material, the plurality of second stiffeners extending widthwise between and connected to the first skin and the second skin, and each of the plurality of second stiffeners having a second stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin;

the airfoil body comprising a first section and a second section that is attached to the first section;

the first section comprising a first portion of the first skin, a first portion of the second skin and the plurality of first stiffeners;

the second section comprising a second portion of the first skin, a second portion of the second skin and the plurality of second stiffeners;

the airfoil body further comprising a cover;

the cover attached to the first section;

the cover spanwise and lengthwise overlapping a portion of the first section; and

the cover forming a third portion of the first skin.

13. An apparatus for an aircraft, comprising:

an airfoil body extending spanwise between a base end and a tip end, the airfoil body extending lengthwise between a leading edge and a trailing edge, the airfoil body extending widthwise between a first side and a second side, and the airfoil body including a first skin, a second skin, a first section and a second section;

the first skin forming the first side;

the second skin forming the second side;

the first section including a first portion of the first skin, a first portion of the second skin and a plurality of first stiffeners, the plurality of first stiffeners comprising first stiffener polymer material, the plurality of first stiffeners connected to and extending widthwise between the first skin and the second skin, and the first section configured as a first monolithic body; and

the second section mechanically attached to the first section, the second section including a second portion of the first skin, a second portion of the second skin and a plurality of second stiffeners, the plurality of second stiffeners comprising second stiffener polymer material, the plurality of second stiffeners connected to and extending widthwise between the first skin and the second skin, and the second section is configured as a second monolithic body.

14. The apparatus of claim 13 , wherein

each of the plurality of first stiffeners has a first stiffener centerline that extends spanwise along the first skin and the second skin; and

each of the plurality of second stiffeners has a second stiffener centerline that extends lengthwise along the first skin and the second skin.

15. The apparatus of claim 13 , wherein

the first section extends spanwise from the base end to the tip end, and lengthwise from the leading edge to the trailing edge; and

the second section extends spanwise from base end to the first section, and lengthwise from the first section to the leading edge.

16. The apparatus of claim 13 , wherein

the airfoil body further includes a cover mechanically attached to the first section;

the cover spanwise and lengthwise overlaps a portion of the first section; and

the cover forms a third portion of the first skin.