Planked stringers that provide structural support for an aircraft wing
Systems and methods are provided for structurally supporting an aircraft wing. The system comprises a section of aircraft wing that includes skin. The skin surrounds an internal volume of the wing and comprises layers of Carbon Fiber Reinforced Polymer (CFRP) having fiber orientations aligned to bear shear stresses applied to the wing. The section of aircraft wing also includes planked stringers that are laterally oriented within the wing, contact the skin within the internal volume, are attached to the skin, and comprise layers of CFRP having fiber orientations that are aligned to bear bending at the wing. Furthermore, the section includes spars that are positioned between planked stringers on an upper portion of the wing and planked stringers on a lower portion of the wing, wherein the spars are aligned with the planked stringers.
1. A system comprising:
a section of an aircraft wing comprising:
skin that surrounds an internal volume of the wing and comprises layers of Carbon Fiber Reinforced Polymer (CFRP) having fiber orientations aligned to bear shear stresses applied to the wing;
planked stringers that are laterally oriented within the wing, contact the skin within the internal volume, are attached to the skin, and comprise layers of CFRP having fiber orientations that are aligned to bear bending at the wing; and
spars that are positioned between planked stringers on an upper portion of the wing and planked stringers on a lower portion of the wing, wherein the spars are aligned with the planked stringers, wherein
each spar increases in thickness as the spar extends towards a tip of the wing corresponding to an amount of tapering by the planked stringers.
2. The system of claim 1 wherein:
each layer of the planked stringers is planar, and
each layer of the planked stringers is parallel with a layer of the skin.
3. The system of claim 1 wherein:
a cross section of each of the planked stringers, corresponding to a vertical plane extending from fore to aft, is quadrilateral.
4. The system of claim 1 wherein:
a cross section of each of the planked stringers, corresponding to a vertical plane extending from fore to aft, has slopes from fore to aft of a maximum magnitude not exceeding forty five degrees.
5. The system of claim 1 wherein:
a cross section of each of the planked stringers, corresponding to a vertical plane extending from fore to aft, is trapezoidal.
6. The system of claim 1 wherein:
a thickness of each planked stringer tapers from aft to fore and fore to aft at a ratio of at least two parts of fore extension to one part reduction in thickness.
7. The system of claim 1 wherein:
a thickness of each planked stringer tapers off as the planked stringer extends towards a tip of the wing at a ratio of at least ten parts of lateral extension to one part reduction in thickness.
8. The system of claim 1 wherein:
the spars comprise composite parts.
9. The system of claim 1 wherein:
each of the planked stringers is co-cured to the skin.
10. The system of claim 1 wherein:
each of the spars is fixedly attached to the planked stringers via a fixation element.
11. The system of claim 1 wherein:
each of the spars is bonded to the planked stringers.
12. The system of claim 1 wherein:
each of the planked stringers is positioned within the internal volume and covers a portion of the skin extending from fore to aft,
gaps separate the planked stringers from fore to aft, and
access points to internal features of the wing penetrate through the skin at the gaps, without penetrating through a planked stringer.
13. The system of claim 1 wherein:
the skin and the planked stringers comprise layers of Carbon Fiber Reinforced Polymer (CFRP).
14. The system of claim 1 wherein:
a ratio of planked stringer width to planked stringer thickness does not exceed ten.
15. A system comprising:
a composite skin defining a surface of a section of an aircraft wing;
an upper composite planked stringer that contacts the composite skin, is integral with the composite skin, and is laterally oriented within the aircraft wing; and
a spar that is fixedly attached to the upper composite planked stringer, extends vertically beneath a portion of the upper composite planked stringer, and is fixedly attached to a lower composite planked stringer located beneath the spar, wherein the spar increases in thickness as the spar extends towards the tip of the wing corresponding to an amount of tapering by the upper composite planked stringer and the lower composite planked stringer.
16. The system of claim 15 wherein:
a ratio of width to thickness for the upper composite planked stringer does not exceed ten.
17. A method comprising:
laying up a composite skin defining a portion of an aircraft wing;
laying up a composite planked stringer that is laterally oriented within the aircraft wing and contacts the composite skin;
attaching the composite planked stringer to the skin; and
attaching the composite planked stringer to a spar that extends vertically beneath the composite planked stringer, wherein the spar increases in thickness as the spar extends towards a tip of the wing corresponding to an amount of tapering by the composite planked stringer.
18. The method of claim 17 further comprising:
cutting through the composite skin at a gap between the composite planked stringer and another composite planked stringer, thereby creating an access panel for accessing an internal volume of the aircraft wing.
19. The method of claim 17 wherein:
attaching the composite planked stringer to the spar comprises fastening the spar to the planked stringer.
20. The method of claim 17 further comprising:
laying up the composite planked stringer comprises tapering off a thickness of the composite planked stringer from aft to fore at a ratio of at least two parts of fore extension to one part reduction in thickness.