Lifting strut in the shape of a lifting airfoil for aircraft landing gear
The invention provides a landing gear strut for an aircraft which has the cross-section of an airfoil. The strut is mounted to the fuselage of the aircraft, preferably at a shallow downward angle from the horizontal, and preferably presents a positive angle of attack to the oncoming airflow. Due to the combination of an airfoil profile and a positive angle of attack, the strut is enabled to provide lift to the aircraft.
1. A landing gear strut for an aircraft, the landing gear strut
having proximal and distal ends, the proximal end being attached to the fuselage of the aircraft,
the strut projecting outward from the fuselage, and
the strut having landing gear components attached to the distal end thereof, wherein the strut is a weight-bearing structure that has a cross-section in the shape of a lifting airfoil having a positive camber.
2. The lifting landing gear strut of claim 1 , wherein the aircraft is a VTOL aircraft.
3. The landing gear strut of claim 2 , wherein the strut projects downward from the fuselage at an angle θ of less than 45° from the horizontal.
4. The landing gear strut of claim 3 , wherein the strut projects downward from the fuselage at an angle θ of less than 30° from the horizontal.
5. The landing gear strut of claim 4 , wherein the strut projects downward from the fuselage at an angle θ of less than 20° from the horizontal.
6. The landing gear strut of claim 5 , wherein the airfoil presents a positive angle of attack when the aircraft is moving forward.
7. The landing gear strut of claim 4 , wherein the airfoil presents a positive angle of attack when the aircraft is moving forward.
8. The landing gear strut of claim 3 , wherein the airfoil presents a positive angle of attack when the aircraft is moving forward.
9. The landing gear strut of claim 2 , wherein the airfoil presents a positive angle of attack when the aircraft is moving forward.
10. The landing gear strut of claim 1 , wherein the strut projects downward from the fuselage at an angle θ of less than 45° from the horizontal.
11. The landing gear strut of claim 10 , wherein the strut projects downward from the fuselage at an angle θ of less than 30° from the horizontal.
12. The landing gear strut of claim 11 , wherein the strut projects downward from the fuselage at an angle θ of less than 20° from the horizontal.
13. The landing gear strut of claim 12 , wherein the airfoil presents a positive angle of attack when the aircraft is moving forward.
14. The landing gear strut of claim 11 , wherein the airfoil presents a positive angle of attack when the aircraft is moving forward.
15. The landing gear strut of claim 10 , wherein the airfoil presents a positive angle of attack when the aircraft is moving forward.
16. The landing gear strut of claim 1 , wherein the airfoil presents a positive angle of attack when the aircraft is moving forward.