An aircraft landing gear component having first and second base members, separated along a first longitudinal axis, a plurality of first parallel hoops, each first hoop lying along the first longitudinal axis and aligned in a plane oriented at a first non-zero angle to the first longitudinal axis, and a plurality of second parallel hoops, each second hoop lying along the first longitudinal axis and aligned in a plane oriented at a second non-zero angle to the first longitudinal axis, the second non-zero angle being different from the first non-zero angle, wherein each of the first hoops intersects with and is fixed to at least one of the second hoops, and wherein each of the second hoops intersects with and is fixed to at least one of the first hoops, such that the first and second hoops form a rigid structure extending between the first and second base members.

A landing gear for a vehicle includes a strut configured for reciprocating movement between a stowed position and a deployed position. A shock absorber has a first element slidingly disposed within the strut and a second element slidingly coupled to the first element. A trailing arm is rotatably coupled to the second element. A first linkage is coupled to the first element, wherein the first linkage drives the first element between a raised position when the strut is in the stowed position and a lowered position when the strut is in the deployed position. The landing gear further includes a second linkage coupled to the trailing arm. The second linkage rotates the trailing arm between a first trailing arm position when the strut is in the stowed position and a second trailing arm position when the strut is in the deployed position.

An aircraft landing gear assembly includes a main fitting comprising having a main barrel and a cross beam fixedly positioned relative to the main barrel and extending radially from the main barrel. The main fitting further includes a drag arm with a first end pivotally coupled to the cross beam by a first pivotal connection and a second end pivotally coupled to the main barrel by a second pivotal connection.

An aircraft landing gear assembly includes a main fitting comprising having a main barrel and a cross beam fixedly positioned relative to the main barrel and extending radially from the main barrel. The main fitting further includes a drag arm with a first end pivotally coupled to the cross beam by a first pivotal connection and a second end pivotally coupled to the main barrel by a second pivotal connection.

A mechanical link (100) comprises a shaft (102). A first mounting interface (108) extends from the first end portion (104) of the shaft (102) and is not movable relative to the shaft (102). A second mounting interface (110) is threadably coupled with the second end portion (106) of the shaft (102). A tubular sleeve (114) circumscribes a portion of the shaft (102) and comprises a slot (116). A pin (112) extends from the shaft (102) and passes through the slot (116). A stop (124) is coupled with the second end portion (106) and fixed to the shaft (102). A washer (126) circumscribes a portion of the shaft (102) between the tubular sleeve (114) and the stop (124). A spring (122) biases the tubular sleeve (114) toward the stop (124). A first jam nut (132) is threadably coupled with the second end portion (106) between the second mounting interface (110) and the stop (124).

A mechanical link (100) comprises a shaft (102). A first mounting interface (108) extends from the first end portion (104) of the shaft (102) and is not movable relative to the shaft (102). A second mounting interface (110) is threadably coupled with the second end portion (106) of the shaft (102). A tubular sleeve (114) circumscribes a portion of the shaft (102) and comprises a slot (116). A pin (112) extends from the shaft (102) and passes through the slot (116). A stop (124) is coupled with the second end portion (106) and fixed to the shaft (102). A washer (126) circumscribes a portion of the shaft (102) between the tubular sleeve (114) and the stop (124). A spring (122) biases the tubular sleeve (114) toward the stop (124). A first jam nut (132) is threadably coupled with the second end portion (106) between the second mounting interface (110) and the stop (124).

Systems and methods for folding landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a yoke pivotally coupled with the shock strut via a lower trunnion, and pivotally coupled with an aircraft structure via an upper trunnion. The yoke is configured to pivot about the upper trunnion in a direction back toward a tail of the aircraft and up toward a fuselage of the aircraft, and the shock strut is configured to pivot about the lower trunnion in a direction forward toward a nose of the aircraft and up toward the fuselage of the aircraft to retract the one or more wheels.

Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

A nose landing gear assembly includes an oleo strut, a forward brace including a forward brace first end and a forward brace second end. The forward brace first end is pivotably coupled to the nose gear bay of a high wing aircraft about a first pivot axis. The assembly also includes an aft brace including an aft brace first end and an aft brace second end. The aft brace first end is pivotably coupled to the nose gear bay about a second pivot axis, and the aft brace second end is pivotably coupled to the oleo strut. An actuator includes an actuator first end and an actuator second end. The actuator second end is coupled to the nose gear bay and the actuator first end coupled to the forward brace. The actuator is configured to move the nose landing gear assembly between a retracted position and an extended position.

A landing gear for a vehicle includes a strut configured for reciprocating movement between a stowed position and a deployed position. A shock absorber has a first element slidingly disposed within the strut and a second element slidingly coupled to the first element. A trailing arm is rotatably coupled to the second element. A first linkage is coupled to the first element, wherein the first linkage drives the first element between a raised position when the strut is in the stowed position and a lowered position when the strut is in the deployed position. The landing gear further includes a second linkage coupled to the trailing arm. The second linkage rotates the trailing arm between a first trailing arm position when the strut is in the stowed position and a second trailing arm position when the strut is in the deployed position.