SWING-ARM PISTON LANDING GEAR SYSTEMS AND METHODS
Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.
1 . An aircraft with a landing gear system comprising:
a nose gear, wherein the nose gear comprises:
a trailing link attached to a wheel of the aircraft at a first position wherein the trailing link is retracted into the aircraft;
a pivot piston configured to support the trailing link; and
an upper master link configured to rotate the trailing link around a point of rotation to rotate the nose gear between a plurality of positions;
a plurality of main gears, mechanically connected to the nose gear through a longitudinal member, wherein:
in a ground position, the nose gear is in a second position wherein the trailing link is parallel to a ground; and
in a pitch angle position, the nose gear is in a third position wherein the trailing link is in an extended position for takeoff.
2 . The aircraft of claim 1 , wherein the longitudinal member comprises a first end connected to a nose linkage and a second end connected to a main linkage.
3 . The aircraft of claim 2 , wherein the main linkage is attached to a lateral shaft at a center of the lateral shaft, wherein the lateral shaft is connected between the plurality of main gears.
4 . The aircraft of claim 1 , wherein the nose gear further comprises a jump strut.
5 . The aircraft of claim 1 , wherein the longitudinal member comprises a plurality of cables located on opposite sides of a centerline of the aircraft.
6 . The aircraft of claim 5 , wherein the plurality of cables comprises a tension cable,
7 . The aircraft of claim 2 , wherein the longitudinal member is configured to thread through a plurality of pulleys disposed on the nose linkage and the main linkage.
8 . The aircraft of claim 1 , wherein rotating the nose gear between a plurality of positions comprises configuring the main gear to remain in a fixed position.
9 . The aircraft of claim 1 , wherein the longitudinal member is configured to transfer a movement of the plurality of main gears to the nose gear.
10 . The aircraft of claim 1 , further comprising a controller configured to communicatively couple the plurality of main gears to the nose gear.
11 . A method of use for an aircraft with landing fear system, wherein the method comprises:
determining that the aircraft has reached a predetermined speed; and
rotating a trailing link of a nose gear supported by a pivot piston, using an upper master link, around a point of rotation between a plurality of positions, wherein the plurality of positions comprises:
a first position wherein the trailing link is retracted into the aircraft;
a second position wherein the trailing link is parallel to a ground while the aircraft is in a ground position; and
a third position wherein the trailing link is in an extended position while the aircraft is in a pitch angle position for takeoff; and
wherein the nose gear is mechanically connected to a plurality of main gears through a longitudinal member.
12 . The method of claim 11 , wherein the longitudinal member comprises a first end connected to a nose linkage and a second end connected to a main linkage.
13 . The method of claim 12 , wherein the main linkage is attached to a lateral shaft at a center of the lateral shaft, wherein the lateral shaft is connected between the plurality of main gears.
14 . The method of claim 11 , wherein the nose gear further comprises a jump strut.
15 . The method of claim 11 , wherein the longitudinal member comprises a plurality of cables on opposite sides of a centerline of the aircraft.
16 . The method of claim 15 , wherein the plurality of cables comprises a tension cable,
17 . The method of claim 12 , wherein the longitudinal member is configured to thread through a plurality of pulleys disposed on the nose linkage and the main linkage.
18 . The method of claim 11 , wherein rotating the nose gear between a plurality of positions comprises configuring the main gear to remain in a fixed position.
19 . The method of claim 11 , wherein the longitudinal member is configured to transfer a movement of the plurality of main gears to the nose gear.
20 . The method of claim 11 , further comprising a controller configured to communicatively couple the plurality of main gears to the nose gear.