U.S. Patent Specifications

Abstract

A landing gear arrangement for an aeroplane having a fuselage and a pair of laterally extending wings, a major central landing gear unit attached to the fuse‐lage, a pair of outboard stabilizing landing gear units each attached to its respective wing and disposed laterally with respect to said central unit, each said landing gear unit including a piston‐cylinder type hydraulic shock absorber, a hydraulic fluid conduit interconnecting the cylinders of each said shock absorber arranged in such manner that each of said laterally disposed units absorbs a predetermined portion of the laterally distributed load of the airplane while at rest upon the ground, cut‐off valve means interposed within said fluid conduit adjacent its connection to said cylinders arranged to prevent loss of fluid from said cylinders in the event of rupture of said fluid conduit at rates of fluid flow beyond the normal equalizing flow between said shock absorber units, and a further central landing gear unit longitudinally disposed with respect to said major central unit for absorbing a portion of the longitudinally distributed load of the aeroplane while at rest upon the ground.

Citation

(1951), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 23 No. 1, pp. 30-30. https://doi.org/10.1108/eb031993