초록 ▼

A vertical support system includes a first articulated leg assembly configured to carry a first load, the first articulated leg assembly being selectively movable between a first retracted configuration and a first loaded configuration and a second articulated leg assembly configured to carry a seco

A vertical support system includes a first articulated leg assembly configured to carry a first load, the first articulated leg assembly being selectively movable between a first retracted configuration and a first loaded configuration and a second articulated leg assembly configured to carry a second load substantially kinematically identical to the first articulated leg assembly, the second articulated leg assembly being selectively movable between a second retracted configuration and a second loaded configuration. The arrangement of axis of rotations and offset angles of the first and/or second lees of each articulated leg assembly may produce a lateral width ratio. A first vertical footprint of the first articulated leg assembly overlaps a second vertical footprint of the second articulated leg assembly when the leg assemblies are retracted.

대표청구항 ▼

1. A vertical support system for an aircraft, comprising: a first articulated leg assembly configured to carry a first load, the first articulated leg assembly comprising a first upper leg and a first lower leg configured to carry the first load and rotatably connected to the first upper leg and a f

1. A vertical support system for an aircraft, comprising: a first articulated leg assembly configured to carry a first load, the first articulated leg assembly comprising a first upper leg and a first lower leg configured to carry the first load and rotatably connected to the first upper leg and a first wheel assembly, the first articulated leg assembly being selectively movable between a first refracted configuration and a first loaded configuration using a first actuator connected to the first articulated leg assembly; anda second articulated leg assembly configured to carry a second load substantially kinematically identical to the first articulated leg assembly, the second articulated leg assembly comprising a second upper leg and a second lower leg configured to carry the second load and rotatably connected to the second upper leg and a second wheel assembly, the second articulated leg assembly being selectively movable between a second refracted configuration and a second loaded configuration using a second actuator connected to the second articulated leg assembly;wherein a lateral width ratio is equal to a value of less than about 0.6, the lateral width ratio being defined as a ratio of (1) a minimum lateral width between the lateral extents of a first wheel assembly and a second wheel assembly when the first articulated leg assembly is in the first retracted configuration and the second articulated leg assembly is in the second refracted configuration to (2) a maximum lateral width between the lateral extents of the first wheel assembly and the second wheel assembly when the first articulated leg assembly is in the first loaded configuration and the second articulated leg assembly is in the second loaded configuration;wherein, with the first articulated leg assembly in the first retracted configuration and the second articulated leg assembly in the second refracted configuration, a first vertical footprint of the first articulated leg assembly and first actuator overlaps a second vertical footprint of the second articulated leg assembly and second actuator; andwherein the first upper leg is rotatable about a first primary axis of rotation, the second upper leg is rotatable about a second primary axis of rotation, the first lower leg is rotatable about a first secondary axis of rotation, and the second lower leg is rotatable about a second secondary axis of rotation, wherein the first articulated leg assembly is symmetric to the second articulated leg assembly about a vertical axis through an origin of the vertical support system as the first articulated leg assembly moves between the first retracted configuration and the first loaded configuration and the second articulated leg assembly moves between the second retracted configuration and the second loaded configuration. 2. The vertical support system of claim 1, wherein at least one of (1) the vertical support system is configured for use as a portion of an aircraft landing gear and (2) the first load comprises the first wheel assembly and the second load comprises the second wheel assembly. 3. The vertical support system of claim 1, wherein the second primary axis of rotation is substantially parallel to the first primary axis of rotation and fixed relative to the first primary axis of rotation, and wherein each of the first primary axis of rotation and the second primary axis of rotation intersect a lateral bisection plane at a primary axis longitudinal incident angle. 4. The vertical support system of claim 3: wherein the first upper leg is rotatable about the first primary axis of rotation and the first lower leg is selectively rotatable about the first secondary axis of rotation of the first upper leg; andwherein the second upper leg is rotatable about the second primary axis of rotation and the second lower leg is selectively rotatable about the second secondary axis of rotation of the second upper leg. 5. The vertical support system of claim 4, wherein at least one of (1) the first upper leg generally extends non-orthogonally from the first primary axis of rotation at a first upper leg offset angle relative to the first primary axis of rotation and (2) the second upper leg generally extends non-orthogonally from the second primary axis of rotation at a second upper leg offset angle relative to the second primary axis of rotation. 6. The vertical support system of claim 4, wherein at least one of (1) the first secondary axis of rotation intersects the lateral bisection plane at a first secondary axis longitudinal incident angle while the first articulated leg assembly is in the first loaded configuration as viewed from above and (2) the second secondary axis of rotation intersects the lateral bisection plane at a second secondary axis longitudinal incident angle while the second articulated leg assembly is in the second loaded configuration as viewed from above. 7. The vertical support system of claim 4, wherein at least one of (1) the first lower leg generally extends non-orthogonally from the first secondary axis of rotation at a first lower leg offset angle relative to the first secondary axis of rotation and (2) the second lower leg generally extends non-orthogonally from the second secondary axis of rotation at a second lower leg offset angle relative to the second secondary axis of rotation. 8. The vertical support system of claim 4, wherein at least one (1) the lateral width ratio is equal to a value in a range of about 0.05 to about 0.8, (2) the lateral width ratio is equal to a value in a range of about 0.2 to about 0.6, (3) the lateral width ratio is equal to a value in a range of about 0.3 to about 0.5, or (4) the lateral width ratio is equal to a value of about 0.4. 9. The vertical support system of claim 1, wherein substantially all of the first articulated leg assembly and substantially all of the second articulated leg assembly are configured for being received within an aircraft fuselage when the first articulated leg assembly is in the first retracted configuration and the second articulated leg assembly is in the second refracted configuration, and wherein the aircraft comprises no sponsons or similar structures extending laterally beyond the fuselage for receiving portions of either of the first articulated leg assembly and the second articulated leg assembly. 10. The vertical support system of claim 1, wherein substantially all of the first articulated leg assembly and substantially all of the second articulated leg assembly are configured for being received within an aircraft fuselage when the first articulated leg assembly is in the first retracted configuration and the second articulated leg assembly is in the second refracted configuration, and wherein the aircraft comprises two rotatable doors configured to substantially enclose the first articulated leg assembly and the second articulated leg assembly within the aircraft fuselage when the first articulated leg assembly is in the first retracted configuration and the second articulated leg assembly is in the second refracted configuration. 11. A vertical support system for an aircraft, comprising: a first articulated leg assembly configured to carry a first load, the first articulated leg assembly comprising a first upper leg and a first lower leg configured to carry the first load and rotatably connected to the first upper leg, the first articulated leg assembly being selectively movable between a first refracted configuration and a first loaded configuration using a first actuator connected to the first articulated leg assembly; anda second articulated leg assembly configured to carry a second load substantially kinematically identical to the first articulated leg assembly, the second articulated leg assembly comprising a second upper leg and a second lower leg configured to carry the second load and rotatably connected to the second upper leg, the second articulated leg assembly being selectively movable between a second retracted configuration and a second loaded configuration using a second actuator connected to the second articulated leg assembly;wherein the first articulated leg assembly and the second articulated leg assembly are symmetrical to each other about a vertical axis through an origin of the vertical support system while the first articulated leg assembly is in the first loaded configuration and the second articulated leg assembly is in the second loaded configuration;wherein the first articulated leg assembly and the second articulated leg assembly are symmetrical to each other about a vertical axis through an origin of the vertical support system while the first articulated leg assembly is in the first refracted configuration and the second articulated leg assembly is in the second refracted configuration; andwherein a first vertical footprint of the first actuator and the first articulated leg assembly while the first articulated leg assembly is in the first retracted configuration overlaps a second vertical footprint of the second actuator and the second articulated leg assembly while the second articulated leg assembly is in the second retracted configuration. 12. The vertical support system of claim 11, wherein at least one of (1) the vertical support system is configured for use as a portion of an aircraft landing gear and (2) the first load comprises a first wheel assembly and the second load comprises a second wheel assembly. 13. The vertical support system of claim 11, wherein the first articulated leg assembly comprises a first primary axis of rotation, wherein the second articulated leg assembly comprises a second primary axis of rotation substantially parallel to the first primary axis of rotation and fixed relative to the first primary axis of rotation, and wherein each of the first primary axis of rotation and the second primary axis of rotation intersect a lateral bisection plane at a primary axis longitudinal incident angle. 14. The vertical support system of claim 13: wherein the first upper leg is rotatable about the first primary axis of rotation and the first lower leg is selectively rotatable about a first secondary axis of rotation of the first upper leg; andwherein the second upper leg is rotatable about the second primary axis of rotation and the second lower leg is selectively rotatable about a second secondary axis of rotation of the second upper leg. 15. The vertical support system of claim 14, wherein at least one of (1) the first upper leg generally extends non-orthogonally from the first primary axis of rotation at a first upper leg offset angle relative to the first primary axis of rotation and (2) the second upper leg generally extends non-orthogonally from the second primary axis of rotation at a second upper leg offset angle relative to the second primary axis of rotation. 16. The vertical support system of claim 14, wherein at least one of (1) the first secondary axis of rotation intersects the lateral bisection plane at a first secondary axis longitudinal incident angle while the first articulated leg assembly is in the first loaded configuration as viewed from above and (2) the second secondary axis of rotation intersects the lateral bisection plane at a second secondary axis longitudinal incident angle while the second articulated leg assembly is in the second loaded configuration as viewed from above. 17. The vertical support system of claim 14, wherein at least one of (1) the first lower leg generally extends non-orthogonally from the first secondary axis of rotation at a first lower leg offset angle relative to the first secondary axis of rotation and (2) the second lower leg generally extends non-orthogonally from the second secondary axis of rotation at a second lower leg offset angle relative to the second secondary axis of rotation. 18. A retractable vertical support system for an aircraft, comprising: a first articulated leg assembly comprising a first primary axis of rotation and a first primary plane coincident with the first primary axis, wherein the first articulated leg assembly is selectively movable between a first extended configuration and a first refracted configuration using a first actuator connected to the first articulated leg assembly; anda second articulated leg assembly substantially kinematically similar to the first articulated leg assembly, the second articulated leg assembly comprising a second primary axis of rotation substantially fixed relative to the first primary axis of rotation and substantially parallel to the first primary axis of rotation, the second articulated leg assembly comprising a second primary plane coincident with the second primary axis and substantially parallel to the first primary plane, wherein the second articulated leg assembly is selectively movable between a second extended configuration and a second refracted configuration using a second actuator connected to the second articulated leg assembly;wherein when the first articulated leg assembly is in the first refracted configuration, substantially all of the first articulated leg assembly is located between the first primary plane and the second primary plane;wherein when the second articulated leg assembly is in the second refracted configuration, substantially all of the second articulated leg assembly is located between the first primary plane and the second primary plane;wherein when the first articulated leg assembly is in the first extended configuration, substantially all of the first articulated leg assembly is located exterior to the space between the first primary plane and the second primary plane;wherein when the second articulated leg assembly is in the second extended configuration, substantially all of the second articulated leg assembly is located exterior to the space between the first primary plane and the second primary plane;wherein the first articulated leg assembly extends a first extended maximum radial distance from the first primary axis of rotation to a point on the first articulated leg assembly farthest from the first primary axis of rotation when the first articulated leg assembly is in the first extended configuration, wherein the first articulated leg assembly extends a first retracted maximum radial distance from the first primary axis of rotation to a point on the first articulated leg assembly farthest from the first primary axis of rotation when the first articulated leg assembly is in the first refracted configuration, and wherein the first extended maximum radial distance is greater than the first refracted maximum radial distance;wherein the second articulated leg assembly extends a second extended maximum radial distance from the second primary axis of rotation to a point on the second articulated leg assembly farthest from the second primary axis of rotation when the second articulated leg assembly is in the second extended configuration, wherein the second articulated leg assembly extends a second refracted maximum radial distance from the second primary axis of rotation to a point on the second articulated leg assembly farthest from the second primary axis of rotation when the second articulated leg assembly is in the second refracted configuration, and wherein the second extended maximum radial distance is greater than the second refracted maximum radial distance;wherein the distance between the first primary plane and the second primary plane is less than each of the first extended maximum radial distance and the second extended maximum radial distance; andwherein a first vertical footprint of the first actuator and the first articulated leg assembly while the first articulated leg assembly is in the first retracted configuration overlaps a second vertical footprint of the second actuator and the second articulated leg assembly while the second articulated leg assembly is in the second retracted configuration. 19. The retractable vertical support system of claim 18: the first articulated leg assembly comprising: a first upper leg rotatable about the first primary axis of rotation; anda first lower leg rotatably connected to the first upper leg, the first lower leg being selectively rotatable about a first secondary axis of the first upper leg; andthe second articulated leg assembly comprising: a second upper leg rotatable about the second primary axis of rotation; anda second lower leg rotatably connected to the second upper leg, the second lower leg being selectively rotatable about a second secondary axis of the second upper leg. 20. The retractable vertical support system of claim 19, wherein the retractable vertical support system is configured for use as a portion of an aircraft landing gear. 21. The retractable vertical support system of claim 20, further comprising: a first wheel assembly carried by the first lower leg; anda second wheel assembly carried by the second lower leg;wherein the first wheel assembly and the second wheel assembly are located as mirror images of each other substantially only while the first articulated leg assembly is in the first extended configuration and the second articulated leg assembly is in the second extended configuration.