Vertically retracting side articulating landing gear for aircraft

摘要

A side articulating main landing gear assembly for an aircraft which includes a wheel axle fitting oriented in a horizontal plane when the landing gear assembly is in an extended condition deployed from a landing gear bay of the aircraft, a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft, a first linkage for maintaining a tire supported on the wheel axle fitting in a substantially vertical plane as the shock absorber strokes between the extended state and the compressed state, and a second linkage for maintaining the wheel axle fitting in the horizontal plane as the shock absorber strokes between the extended state and the compressed state. The first and second linkages are adapted and configured to minimize lateral tire scuffing during shock absorber stroking.

主权项

1. A side articulating main landing gear assembly for an aircraft, comprising:
a) a wheel axle fitting oriented in a horizontal plane when the landing gear assembly is in an extended condition deployed from a landing gear bay of the aircraft; b) a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft; c) a first linkage for maintaining a tire supported on the wheel axle fitting in a substantially vertical plane as the shock absorber strokes between the extended state and the compressed state; and d) a second linkage for maintaining the wheel axle fitting in said horizontal plane as the shock absorber strokes between the extended state and the compressed state, wherein the first and second linkages are adapted and configured to minimize lateral tire scuffing during shock absorber stroking. e) a drive crank operatively connected to the shock absorber, the first linkage and the second linkage for moving the landing gear assembly between the extended condition deployed from the landing gear bay and an inverted retracted condition stowed in the landing gear bay; and f) a reforming brace operatively connected to the aircraft, the drive crank, the first linkage and the shock absorber for locking the landing gear in the extended condition and in the retracted condition; wherein the reforming brace includes inboard and outboard brace links connected to one another at an overcentered pivot point.