System for rolling landing gear
A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.
1. A system for rolling landing gear on an electric vertical take-off and landing aircraft, the system comprising:
a skid component attached to the aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft;
at least a wheel journaled on a rotational fulcrum; and
at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a spring configured to exert a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube, wherein the at least a spring includes a first quantity of carbon prestressed springs and a second quantity of fiberglass prestressed springs.
2. The system of claim 1 , wherein the first quantity is more than the second quantity.
3. The system of claim 1 , wherein the first quantity and the second quantity are layered to produce a layered spring assembly.
4. The system of claim 1 , wherein the at least a spring includes at least a flex point.
5. The system of claim 1 , wherein the at least a skid tube includes at least a recess.
6. The system of claim 5 , wherein the at least a recess houses the at least a wheel.
7. The system of claim 1 , wherein the at least a spring extends and retracts the at least a wheel as a function of a change in a downward force.
8. The system of claim 7 , wherein the downward force exceeds the recoil force upon landing.
9. The system of claim 1 , wherein the at least a spring has two ends and a central section, wherein the rotational fulcrum is attached to the central section, and wherein the two ends are affixed to the at least a skid tube.
10. The system of claim 9 , wherein at least an end of the at least a spring is attached to the aircraft by a machined aluminum clamp.
11. The system of claim 1 , wherein the at least a wheel has a rating force.
12. The system of claim 11 , wherein the rating force is more than a threshold landing force.
13. The system of claim 11 , wherein the rating force includes a rating load.
14. The system of claim 11 , wherein the rating force is determined as a function of a ply rating.
15. The system of claim 14 , wherein the ply rating is determined as a function of a bias ply.
16. The system of claim 14 , wherein the ply rating is determined as a function of a radial ply.
17. A system for rolling landing gear on an electric vertical take-off and landing aircraft, the system comprising:
a skid component attached to the aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft;
at least a wheel journaled on a rotational fulcrum; and
at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a spring configured to exert a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube, wherein the at least a spring has two ends and a central section, wherein the rotational fulcrum is attached to the central section, and wherein the two ends are affixed to the at least a skid tube.
18. The system of claim 17 , wherein at least an end of the at least a spring is attached to the aircraft by a machined aluminum clamp.
19. The system of claim 17 , wherein the at least a spring includes at least a fiberglass prestressed spring.
20. The system of claim 17 , wherein the at least a spring includes at least a carbon prestressed spring.