Tripod landing gear assembly

1. A system for use with a tripod landing gear assembly of an aircraft, the system comprising:

a tension strut assembly having a tension strut extending from an upper end to a lower end;

a drag brace assembly having an upper brace and a lower brace, the upper brace pivotably coupled to the lower brace at a center point, the lower brace rotatably coupled to the lower end of the tension strut;

a jury linkage pivotally coupled to the drag brace assembly at the center point and rotatably coupled to a middle portion of the tension strut, the middle portion between the upper end and the lower end; and

a plane defined by a tension strut centerline of the tension strut and a lower drag brace centerline of the lower brace, wherein:

a jury linkage centerline is disposed within the plane,

the plane is configured to shift from a first plane in a down and locked position to a second plane in a stowed position, and

the second plane is different from the first plane.

2. The system of claim 1 , wherein the lower brace defines a lower brace centerline, wherein the tension strut centerline and the lower brace centerline define a rotation plane, wherein the tripod landing gear assembly is configured to rotate in the rotation plane.

3. The system of claim 1 , further comprising a wheel assembly coupled to the lower end of the tension strut.

4. The system of claim 1 , wherein the jury linkage is configured to be in an extended position in which a length of the jury linkage extends in a straight line in response to the tripod landing gear assembly being in the down and locked position and in response to the tripod landing gear assembly being in the stowed position.

5. The system of claim 1 , wherein the system is configured to facilitate locking of the tripod landing gear assembly in the down and locked position and in the stowed position.

6. The system of claim 1 , further comprising:

an upper drag spindle joint configured to rotatably couple a drag brace upper end of the drag brace assembly to the aircraft;

an upper tension strut spindle joint configured to rotatably couple the jury linkage to the middle portion of the tension strut; and

a lower tension strut spindle joint configured to rotatably couple a drag brace lower end of the drag brace assembly to a lower portion of the tension strut, the lower portion between the lower end and the middle portion proximate the lower end.

7. The system of claim 6 , further comprising a shock strut assembly having an outer cylinder configured to be coupled to the aircraft, and an inner cylinder configured to be coupled to the tension strut between the upper tension strut spindle joint and the lower tension strut spindle joint.

8. The system of claim 1 , wherein the upper brace of the drag brace assembly, the lower brace of the drag brace assembly, and the jury linkage are pivotally coupled together at a single location.

9. The system of claim 8 , wherein the upper brace of the drag brace assembly, the lower brace of the drag brace assembly, and the jury linkage are pivotally coupled together at the single location along a pivot axis.

10. A system for use with landing gear of an aircraft, the system comprising:

a drag brace assembly having an upper brace and a lower brace, the upper and lower brace are pivotably coupled at a center point;

a tension strut having an upper end and a lower end, the lower brace rotatably coupled to the tension strut proximate the lower end of the tension strut;

a jury linkage pivotably coupled to the upper brace and the lower brace at the center point and rotatably coupled to the tension strut; and

a plane defined by a tension strut centerline of the tension strut and a lower drag brace centerline of the lower brace, wherein:

a jury linkage centerline is disposed within the plane,

the plane is configured to shift from a first plane in a down and locked position to a second plane in a stowed position, and

the second plane is different from the first plane.

11. The system of claim 10 , wherein the jury linkage is configured to be in an extended position in which a length of the jury linkage extends in a straight line in response to a tripod landing gear assembly of the system being in the down and locked position and in response to the tripod landing gear assembly being in the stowed position.

12. The system of claim 10 , further comprising a wheel assembly coupled to the lower end of the tension strut.

13. The system of claim 10 , further comprising:

an upper drag spindle joint configured to rotatably couple a drag brace upper end of the drag brace assembly to the aircraft;

an upper tension strut spindle joint configured to rotatably couple the jury linkage to a middle portion of the tension strut; and

a lower tension strut spindle joint configured to rotatably couple the lower brace of the drag brace assembly to a lower portion of the tension strut, the lower portion between the lower end and the middle portion proximate the lower end.

14. The system of claim 13 , further comprising a shock strut assembly having an outer cylinder configured to be coupled to the aircraft, and an inner cylinder configured to be coupled to the tension strut between the upper tension strut spindle joint and the lower tension strut spindle joint.

15. The system of claim 10 , wherein the lower brace defines a lower brace centerline, wherein the tension strut centerline and the lower brace centerline define a rotation plane, wherein the system is configured to rotate in the rotation plane.

16. The system of claim 15 , wherein the upper brace of the drag brace assembly, the lower brace of the drag brace assembly, and the jury linkage are pivotally coupled together at a single location.

17. The system of claim 16 , wherein the upper brace of the drag brace assembly, the lower brace of the drag brace assembly, and the jury linkage are pivotally coupled together at the single location along a pivot axis.

18. A tripod landing gear assembly for use with an aircraft, the tripod landing gear assembly comprising:

a shock strut having an outer cylinder configured to be coupled to the aircraft, and an inner cylinder;

a drag brace assembly having an upper brace configured to be rotatably coupled to the aircraft and a lower brace, wherein the upper and lower brace are pivotably coupled at a center point;

a tension strut extending from an upper end to a lower end, the lower brace rotatably coupled to the tension strut proximate the lower end of the tension strut, the lower brace pivotably coupled to a lower portion of the tension strut;

a jury linkage pivotally coupled to the drag brace assembly at the center point and rotatably coupled to the tension strut; and

a plane defined by a tension strut centerline of the tension strut and a lower drag brace centerline of the lower brace, wherein:

a jury linkage centerline is disposed within the plane,

the plane is configured to shift from a first plane in a down and locked position to a second plane in a stowed position, and

the second plane is different from the first plane.

19. The tripod landing gear assembly of claim 18 , further comprising:

an upper drag spindle joint configured to rotatably couple a drag brace upper end of the drag brace assembly to the aircraft;

an upper tension strut spindle joint configured to rotatably couple the jury linkage to a middle portion of the tension strut; and

a lower tension strut spindle joint configured to rotatably couple the lower brace of the drag brace assembly to a lower portion of the tension strut, the lower portion between the lower end and the middle portion proximate the lower end.

20. The tripod landing gear assembly of claim 18 , further comprising a wheel assembly coupled to the lower end of the tension strut.