Self-orienting aircraft landing gear
An aircraft landing gear self-orients so to align itself within a plane parallel to the plane defined by the aircraft's roll and yaw axis. A nose gear of a tricycle landing gear configuration includes the ability to not only caster 360 degrees but also self-orient itself to be aligned parallel with the plane defined by the aircraft's roll and yaw axis once removed from any interaction with the ground. A simple and efficient mechanical design provides the landing gear with a substantially constant centering torque that neither impedes nor impairs ground movement yet returns the nose gear to a proper alignment for retraction and stowage.
1. A self-orienting aircraft landing gear, comprising:
a landing gear assembly;
a wheel rotatably coupled to a wheel fork wherein the wheel fork is coupled to the landing gear assembly by a cylindrical shaft such that the wheel fork is operable to caster about a longitudinal axis of the shaft;
a cam associated with the wheel fork and circumscribing the cylindrical shaft wherein the cam possesses a planar cardioid shape having a top cam surface, a lower cam surface and a cam sidewall wherein the cam sidewall is substantially perpendicular to the upper cam surface and the lower cam surface; and
a cam follower linked to the landing gear assembly and operable to continually engage the cam sidewall of the cam so as to create a substantially constant centering torque driving the cam follower to a cusp of the planar modified cardioid.
2. The self-orienting aircraft landing gear of claim 1 , wherein the wheel fork is operable to rotate 360 degrees about the longitudinal axis of the shaft.
3. The self-orienting aircraft landing gear of claim 1 , wherein the planar modified cardioid shape is used to create a substantially constant centering torque.
4. The self-orienting aircraft landing gear of claim 1 , responsive to the cam follower coming into contact with the cusp of the planar modified cardioid, the wheel fork is aligned with a longitudinal axis of an aircraft.
5. The self-orienting aircraft landing gear of claim 4 , wherein the centering torque is consistent during ground, air and water operations.
6. The self-orienting aircraft landing gear of claim 4 , wherein the centering torque is independent of whether the wheel is in ground contact, airborne or seaborne.
7. The self-orienting aircraft landing gear of claim 1 , further comprising a cam follower driver interposed between the landing gear assembly and the cam follower and operable to continually deliver a driving force to place the cam follower against the cam sidewall.
8. A landing gear centering mechanism for an aircraft wherein the aircraft possesses a yaw axis, a pitch axis and a roll axis, the landing gear centering mechanism comprising:
a wheel fork housing a landing gear wheel wherein rotation of the wheel within the wheel fork defines a rotation plane;
a wheel fork shaft coupling the wheel fork to a landing gear assembly wherein the wheel fork is operable to caster about a longitudinal axis substantially parallel to the yaw axis;
a cam circumscribing the wheel fork shaft wherein the cam includes a cardioid shape; and
a cam follower interposed between the cam and the landing gear assembly operable to generate, through contact with the cam, a centering torque about the longitudinal axis driving the rotation plane of the wheel to align with a pitch plane defined by the roll axis and the yaw axis.
9. The landing gear centering mechanism of claim 8 , wherein the modified cardioid shape includes two singularities.
10. The landing gear centering mechanism of claim 8 , wherein the wheel fork is fixed to the cam.
11. The landing gear centering mechanism of claim 8 , wherein the wheel fork shaft is fixed to the cam.
12. The landing gear centering mechanism of claim 8 , wherein the wheel fork is fixed to the cam.
13. The landing gear centering mechanism of claim 8 , wherein the cam follower asserts a force against a sidewall of the cam generating the centering torque.
14. The landing gear centering mechanism of claim 8 , wherein the cam follower is coupled to the landing gear assembly by a spring.
15. The landing gear centering mechanism of claim 8 , wherein the cardioid shape includes at least one singularity and responsive to the cam follower being in contact with the at least one singularity, the rotation plane of the wheel is parallel with the pitch plane of the aircraft.
16. The landing gear centering mechanism of claim 8 , wherein the centering torque is consistent during ground, air and water operations.
17. The self-orienting aircraft landing gear of claim 4 , wherein the centering torque is independent of whether the wheel is in ground contact, airborne or seaborne.