Patent ID: 8789792
Filing Date: 2014-07-29
Classification: B64C

Abstract:
1. An auxiliary undercarriage, associated with an aircraft for landing on the ground, the aircraft having a bottom portion to which is hinged the undercarriage, the auxiliary undercarriage comprising: a wheel axle; two wheels connected laterally by the wheel axle to form a twin wheel assembly and each of the two wheels being independent in rotation; a rocker lever having: a first end zone at a top portion of the auxiliary undercarriage, the auxiliary undercarriage being hinged by the first end zone to the bottom portion for fastening to the auxiliary undercarriage to the aircraft and a second end zone; the second end zone of the rocker lever extending along with a swivel axis, wherein the swivel axis is configured to be inclined at a longitudinal angle offset from a vertical direction; a steerable swivel steerable about the swivel axis and connecting the rocker lever to the subassembly together with the twin wheels, the steerable swivel including a first portion fastened to the second end zone of the rocker lever and a second portion to be swiveled relative to the first portion about the swivel axis, the second portion being connected to the wheel axle of the twin wheel subassembly; a damper disposed between a point of the bottom portion of the aircraft and the steerable swivel; and a hinge disposed along the wheel axle, wherein the second portion of the steerable swivel is pivotally connected to the hinge to pivot in a lateral direction, the hinge being located laterally in the middle of the wheel axle and has a pivot axis perpendicular to the wheel axle and to the swivel axis; wherein the swivel pivots in the lateral direction with respect to the wheel axle to allow the swivel axis to be positioned at the longitudinal angle offset from the vertical direction while maintaining the wheel axle in a generally horizontal position.