Semi-levered shrink landing gear
A landing gear for use on an aircraft, the landing gear including a shock strut and an anti-rotation linkage. The shock strut is positioned at least partially within and guided in movement by a guide member coupled to a frame of the aircraft. The shock strut including an outer cylinder that is shaped and sized to engage the guide member where the guide member guides sliding movement of the outer cylinder, and where the outer cylinder is configured so as to be driven in the sliding movement relative to the guide member, and an inner cylinder disposed at least partly within the outer cylinder. The anti-rotation linkage including a connector plate coupled to the outer cylinder of the shock strut, and an anti-rotation link assembly coupled to both the guide member and the connector plate, the anti-rotation link assembly being configured to maintain the shock strut in a fixed rotational orientation relative to the guide member.
1. A landing gear for use on an aircraft, the landing gear comprising:
a shock strut positioned at least partially within and guided in movement by a guide member coupled to a frame of the aircraft, the shock strut comprising:
an outer cylinder that is shaped and sized to engage the guide member where the guide member guides sliding movement of the outer cylinder, and where the outer cylinder is configured so as to be driven in the sliding movement relative to the guide member, and
an inner cylinder disposed at least partly within the outer cylinder; and
an anti-rotation linkage comprising:
a connector plate coupled to the outer cylinder of the shock strut, and
an anti-rotation link assembly coupled to both the guide member and the connector plate, the anti-rotation link assembly being configured to maintain the shock strut in a fixed rotational orientation relative to the guide member.
2. The landing gear of claim 1 , wherein the anti-rotation link assembly maintains wheels coupled to the shock strut in a predetermined orientation relative to the guide member.
3. The landing gear of claim 1 , wherein the anti-rotation link assembly comprises:
a first scissors link coupled to the guide member; and
a second scissors link coupled to both the first scissors link and the connector plate to connect the guide member to the shock strut.
4. The landing gear of claim 1 , wherein the landing gear is a semi-levered landing gear having a truck link pivotally coupled to the connector plate and at least one wheel rotatably coupled to the truck link.
5. The landing gear of claim 4 , wherein the inner cylinder is movable relative to the outer cylinder.
6. The landing gear of claim 5 , wherein the truck link is pivotally coupled to both the connector plate and the inner cylinder of the shock strut.
7. The landing gear of claim 1 , further comprising:
a shrink mechanism, where the shrink mechanism is coupled to both the guide member and the outer cylinder of the shock strut so as to drive the sliding movement of the outer cylinder relative to the guide member, the shrink mechanism comprising:
a shaft rotatably coupled to the guide member about a shaft rotation axis, the shaft being disposed perpendicular to a centerline of the shock strut;
an anchor arm coupled to the shaft, the anchor arm being configured to couple to a structure within a wing of the aircraft;
a shrink arm coupled to the shaft, the shrink arm and the anchor arm being coupled to the shaft so as to rotate as a unit with the shaft about the shaft rotation axis, relative to the guide member, at least 180° when the anchor arm is coupled to the structure within the wing of the aircraft; and
a shrink link rotatably coupled to the shrink arm, the shrink link being configured to rotatably couple to the outer cylinder of the shock strut.
8. The landing gear of claim 7 , wherein the anchor arm is coupled to the structure with a rod.
9. The landing gear of claim 7 , wherein the shock strut travels within the guide member to extend and retract the landing gear.
10. The landing gear of claim 7 , wherein the shrink arm rotates about the shaft rotation axis and the shrink link travels within the guide member to extend and retract the landing gear.
11. A landing gear for use on an aircraft, the landing gear comprising:
a guide member coupled to a frame of the aircraft;
a shock strut positioned at least partially within the guide member, the shock strut comprising:
an outer cylinder that is shaped and sized to be guided by the guide member in a linear sliding movement, and where the outer cylinder is configured to couple with a shrink mechanism configured to drive the sliding movement of the outer cylinder, and
an inner cylinder disposed at least partly within the unitary outer cylinder; and
an anti-rotation linkage comprising:
a connector plate coupled to the outer cylinder of the shock strut, and
an anti-rotation link assembly coupled to both the guide member and the connector plate, the anti-rotation link assembly being configured to maintain the shock strut in a fixed rotational orientation relative to the guide member.
12. The landing gear of claim 11 , wherein the anti-rotation link assembly maintains wheels coupled to the shock strut in a predetermined orientation relative to the guide member.
13. The landing gear of claim 11 , wherein the anti-rotation link assembly comprises:
a first scissors link coupled to the guide member; and
a second scissors link coupled to both the first scissors link and the connector plate to connect the guide member to the shock strut.
14. The landing gear of claim 11 , wherein the landing gear is a semi-levered landing gear having a truck link pivotally coupled to the connector plate and at least one wheel rotatably coupled to the truck link.
15. The landing gear of claim 14 , wherein the inner cylinder is movable relative to the outer cylinder.
16. The landing gear of claim 15 , wherein the truck link is pivotally coupled to both the connector plate and the inner cylinder of the shock strut.
17. The landing gear of claim 11 , further comprising:
the shrink mechanism, where the shrink mechanism is coupled to both the guide member and outer cylinder of the shock strut, the shrink mechanism comprising:
a shaft rotatably coupled to the guide member about a shaft rotation axis, the shaft being disposed perpendicular to a centerline of the shock strut;
an anchor arm coupled to the shaft, the anchor arm being configured to couple to a structure within a wing of the aircraft;
a shrink arm coupled to the shaft, the shrink arm and the anchor arm being coupled to the shaft so as to rotate as a unit with the shaft about the shaft rotation axis, relative to the guide member, at least 180° when the anchor arm is coupled to the structure within the wing of the aircraft; and
a shrink link rotatably coupled to the shrink arm, the shrink link being configured to rotatably couple to the outer cylinder of the shock strut.
18. The landing gear of claim 17 , wherein the anchor arm is coupled to the structure with a rod.
19. The landing gear of claim 17 , wherein the shock strut travels within the guide member to extend and retract the landing gear.
20. The landing gear of claim 17 , wherein the shrink arm rotates about the shaft rotation axis and the shrink link travels within the guide member to extend and retract the landing gear.