초록 ▼

To optimize the performance of a canard airplane with an engine in front, the canard is mounted forward of its location in existing canard airplanes. Specifically, the canard is located with its leading edge significantly ahead of the firewall. This allows the canard to be mounted higher on the fuse

To optimize the performance of a canard airplane with an engine in front, the canard is mounted forward of its location in existing canard airplanes. Specifically, the canard is located with its leading edge significantly ahead of the firewall. This allows the canard to be mounted higher on the fuselage, providing aerodynamic improvements. The engine may be mounted to, or near, the canard spar, simplifying the structure. The added leverage of the further-forward canard allows the wing to be moved forward also. This makes possible a low wing under the occupants of the airplane. Efficient loading of the lifting surfaces is maintained by using a high aspect ratio canard.

대표청구항 ▼

The invention claimed is: 1. An airplane, comprising: an engine located in a forward one-third of a fuselage, a propeller mounted forward of the engine, a firewall positioned between the engine and a cockpit, a fixed main wing located near a center of the airplane, a vertical stabilizer and rudder

The invention claimed is: 1. An airplane, comprising: an engine located in a forward one-third of a fuselage, a propeller mounted forward of the engine, a firewall positioned between the engine and a cockpit, a fixed main wing located near a center of the airplane, a vertical stabilizer and rudder mounted at a rear of the airplane, and a canard mounted on the airplane to form an intersection with the fuselage such that, at the intersection of the canard with the fuselage, a leading edge of the canard is located forward of the firewall by a distance of at least one-quarter of a chord of the canard. 2. The airplane of claim 1 wherein the canard is located at least 25% of a height of the firewall above a bottom of the firewall and not more than 75% of the height of the firewall above the bottom of the firewall. 3. The airplane of claim 1 wherein the main wing is located in a lower 25% of the fuselage. 4. The airplane of claim 3 wherein the main wing comprises two main spars. 5. The airplane of claim 4 wherein seating for occupants is provided in a space between the two main spars. 6. The airplane of claim 1 wherein the main wing is located to partially overlap a cockpit in the fuselage. 7. The airplane of claim 1 wherein the engine is mounted to a spar of the canard. 8. The airplane of claim 7 wherein a nose wheel is mounted to the canard spar. 9. The airplane of claim 1 wherein a span of the main wing is less than 1.2 times a span of the canard. 10. An airplane, comprising: a fuselage, a single engine located in a forward one-third of the fuselage, a propeller mounted forward of the engine, a fixed main wing located near a center of the airplane that does not move relative to the fuselage, a vertical stabilizer and rudder mounted at a rear of the fuselage, and a canard directly connected to and intersecting the fuselage to not move relative to the fuselage and not connected to any outboard fuel tanks and not part of a vertical array of canards, the canard having a fixed camber and a shadow area smaller than a shadow area of the main wing. 11. The airplane of claim 10 wherein the canard is located at least 25% of a height of a firewall above a bottom of the firewall and not more than 75% of the height of the firewall above the bottom of said firewall. 12. The airplane of claim 10 wherein the main wing is located in a lower 25% of said fuselage. 13. The airplane of claim 12 wherein the main wing comprises two main spars. 14. The airplane of claim 13 wherein seating for occupants is provided between the two main spars in the main wing. 15. The airplane of claim 10 wherein the main wing is located such that it partially overlaps a cockpit of the airplane. 16. The airplane of claim 10 wherein the engine is mounted to a spar of the canard. 17. The airplane of claim 16 wherein the nose wheel is essentially mounted to the canard spar. 18. The airplane of claim 10 wherein a span of the wing is less than 1.2 times a span of said canard. 19. An airplane, comprising: an engine located in a forward one-third of a fuselage, a propeller mounted ahead of the engine, a main wing located near a center of the airplane that does not move relative to the fuselage, a vertical stabilizer and rudder mounted at a rear of the fuselage, and a fixed-camber canard directly connected to and intersecting the fuselage to not move relative to the fuselage and not connected to any outboard fuel tanks and not part of a vertical array of canards, the canard having an aspect ratio of 10:1 or greater. 20. The airplane of claim 19 in which a span of the main wing is less than 1.2 times a span of the canard.