Spar for sailwings
View Patent ↗A sail wing for a lightweight aircraft comprising a membrane; a front spar; and a tensioned rear wire attached to a trailing edge of the membrane, such that when the front spar is bent to match a curve of the tensioned trailing edge of the sail wing membrane, the sail wing membrane has substantially little or no twist, and results in substantially little or no induced drag.
1. A sail wing for an aircraft comprising:
a front spar;
a sail wing membrane attached to the front spar; and
a tensioned rear wire attached to a trailing edge of the sail wing membrane, such that when the front spar includes a curve that matches a curve of the tensioned trailing edge of the sail wing membrane, the sail wing membrane has substantially little or no twist along a span of the sail wing membrane, the front spar curve being substantially concave when viewed from below the front of the aircraft, and wherein
the front spar is pre-curved to substantially match the shape of the trailing edge curve so that plural curved sail wing cross sections are at a substantially uniform angle of attack.
2. The sail wing for an aircraft according to claim 1 , wherein the front spar comprises a composite material having a molded pre-curve.
3. The sail wing according to claim 1 , wherein the front spar comprises a metal material having the pre-curve formed therein.
4. The sail wing according to claim 1 , wherein the curve of the front spar is configured to substantially minimize induced drag that results from twisting of the sail wing membrane.
5. The sail wing according to claim 1 , wherein the front spar comprises a wood material having the pre-curve formed therein.
6. The sail wing according to claim 1 , wherein the front spar pre-curve comprises a substantially catenary curve.
7. The sail wing according to claim 1 , wherein the front spar pre-curve comprises a substantially parabolic curve.
8. The sail wing according to claim 1 , wherein the front spar pre-curve comprises a substantially hyperbolic curve.
9. The sail wing according to claim 1 , wherein the front spar pre-curve comprises a substantially circular curve.
10. The sail wing according to claim 1 , wherein the front spar pre-curve comprises a curve that takes into account aircraft design criteria selected from the group consisting of aerodynamic loads, allowable tension in the tensioned rear wire, a type of material the sail wing is made of, one or more wing airfoils, and a twist in the wing.
11. The sail wing according to claim 1 , wherein the front spar pre-curve comprises a curve that takes into account aircraft design criteria comprising: aerodynamic loads; allowable tension in the tensioned rear wire; a type of material the sail wing is made of; one or more wing airfoils, and a twist in the wing.
12. A lightweight aircraft, comprising:
a fuselage; vertical control surfaces appended to the fuselage;
horizontal control surfaces appended to the fuselage; and
a wing structure appended to the fuselage, wherein the wing structure includes a pre-curved front spar; a wing structure membrane attached to the front spar; and a tensioned rear wire attached to a trailing edge of the wing structure membrane, such that when the front spar is pre-curved to match a curve of the tensioned trailing edge of the wing structure membrane, the wing structure membrane has substantially little or no twist, the front spar curve being substantially concave when viewed from below the front of the aircraft, and wherein
the front spar is pre-curved to substantially match the shape of the trailing edge curve so that plural curved sail wing cross sections are at a substantially uniform angle of attack.
13. The lightweight aircraft according to claim 12 , wherein the front spar comprises a composite material having a molded pre-curve.
14. The lightweight aircraft according to claim 12 , wherein the front spar comprises a metal material having the pre-curve formed therein.
15. The lightweight aircraft according to claim 12 , wherein the pre-curve of the front spar is configured to substantially minimize induced drag that results from twisting of the wing structure membrane.
16. The lightweight aircraft according to claim 12 , wherein the front spar comprises a wood material having the pre-curve formed therein.
17. The lightweight aircraft according to claim 12 , wherein the front spar pre-curve comprises a substantially catenary curved shape.
18. The lightweight aircraft according to claim 12 , wherein the front spar pre-curve comprises a substantially parabolic curved shape.
19. The lightweight aircraft according to claim 12 , wherein the front spar pre-curve comprises a substantially hyperbolic curved shape.
20. The lightweight aircraft according to claim 12 , wherein the front spar pre-curve comprises a substantially circular curved shape.
21. The lightweight aircraft according to claim 12 wherein the lightweight aircraft comprises a solar-powered aircraft.
22. The lightweight aircraft according to claim 12 wherein the lightweight aircraft comprises a glider.
23. The lightweight aircraft according to claim 12 wherein the lightweight aircraft comprises an ultra-light aircraft.
24. The lightweight aircraft according to claim 12 , wherein the wing structure further comprises one or more additional tensioned rear wires attached to the trailing edge of the wing structure membrane.
25. A sail wing for an aircraft comprising:
a front spar; and
a tensioned sail wing membrane attached to the front spar, such that when the front spar includes a curve that matches a curve of the tensioned trailing edge of the tensioned sail wing membrane, the tensioned sail wing membrane has substantially little or no twist along a span of the tensioned sail wing membrane, the front spar curve being substantially concave when viewed from below the front of the aircraft, and wherein
the front spar is pre-curved to substantially match the shape of the trailing edge curve so that plural curved sail wing cross sections are at a substantially uniform angle of attack.
26. The sail wing according to claim 25 , wherein the pre-curve of the front spar is configured to substantially minimize induced drag that results from twisting of the tensioned sail wing membrane.