Honeycomb core for a spar of an unmanned aerial vehicle
Systems, devices, and methods including a wing panel; a spar disposed in the wing panel, where the spar comprises: an upper cap; a lower cap; a honeycomb core connected between at least a portion of the upper cap and the lower cap; an inner face sheet; and an outer face sheet, where at least a portion of the honeycomb core is disposed between the inner face sheet and the outer face sheet.
1. A system comprising:
a wing panel;
a spar disposed in the wing panel, wherein the spar comprises:
an upper cap;
a lower cap;
a honeycomb core connected between at least a portion of the upper cap and the lower cap;
an lower surface sheet; and
an upper surface sheet, wherein
at least a portion of the honeycomb core is disposed between the lower surface sheet and the upper surface sheet, and
the spar is thicker at the upper cap than at the lower cap.
2. The system of claim 1 , wherein the wing panel comprises a semi-rigid shell.
3. The system of claim 2 , further comprising an unmanned aerial vehicle (UAV), wherein the wing panel is attached to the UAV.
4. The system of claim 2 , wherein the honeycomb core and upper surface sheet go around an entire circumference of the spar.
5. The system of claim 1 , further comprising an unmanned aerial vehicle (UAV), wherein the wing panel is attached to the UAV.
6. The system of claim 5 , wherein the honeycomb core and upper surface sheet go around an entire circumference of the spar.
7. The system of claim 1 , wherein the honeycomb core and upper surface sheet go around an entire circumference of the spar.
8. The system of claim 1 , wherein the spar has a varying thickness.
9. The system of claim 1 , wherein the honeycomb core provides stabilization to the spar between the upper cap and the lower cap.
10. The system of claim 1 , wherein the honeycomb core stabilizes a cross section of the spar against flexing of a spar walls, such that the spar withstands positive and negative out-of-plane bending loads about a chordwise principal axis of the spar.
11. The system of claim 1 , wherein the upper cap is distal from the lower cap.
12. The system of claim 1 , wherein a cross section of the spar is oval.
13. The system of claim 1 , wherein the upper cap and the lower cap are made of carbon fiber.
14. The system of claim 1 , wherein the honeycomb core is made of aramid fibers.
15. A system comprising:
a wing panel;
a spar disposed in the wing panel, wherein the spar comprises:
an upper cap;
a lower cap;
a honeycomb core connected between at least a portion of the upper cap and the lower cap;
an lower surface sheet; and
an upper surface sheet, wherein
at least a portion of the honeycomb core is disposed between the lower surface sheet and the upper surface sheet, and
at least a portion of the honeycomb core and the upper surface sheet extend past at least one edge of the upper cap and overlap onto the upper cap.
16. The system of claim 15 , wherein the wing panel comprises a semi-rigid shell.
17. The system of claim 15 , further comprising an unmanned aerial vehicle (UAV), wherein the wing panel is attached to the UAV.
18. The system of claim 15 , wherein the honeycomb core and upper surface sheet go around an entire circumference of the spar.
19. A system comprising:
a wing panel;
a spar disposed in the wing panel, wherein the spar comprises:
an upper cap;
a lower cap;
a honeycomb core connected between at least a portion of the upper cap and the lower cap;
an lower surface sheet; and
an upper surface sheet, wherein
at least a portion of the honeycomb core is disposed between the lower surface sheet and the upper surface sheet, and
at least a portion of the honeycomb core and the upper surface sheet extend past at least one edge of the lower cap and overlap onto the lower cap.