GB726573A - Improvements in or relating to aircraft landing gear - Google Patents

Abstract

726,573. Aircraft landing gear. SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU SUD-EST. March 10, 1953 [March 20, 1952], No. 6621/53. Class 4. [Also in Group XXXII] A main landing gear for an aircraft 1 comprises a pair of symmetrical retractable frame structures 3, 3a, Fig. 2, disposed symmetrically relative to the longitudinal axis of the aircraft and provided with friction beams or skids adapted to act as landing skis, these frame structures being hinged about parallel longitudinal axis for retraction and extension by a control device adapted to lock them in either position, said frame structures being associated with resilient means (see Group XXXII) providing the damping of ground unevennesses and a torsional damping about their hinge axles in the extended position, said frame structures themselves constituting in their retracted position the external fairing closing the aircraft fuselage. As seen in Fig. 5, the skid comprises a lower beam 5 having a skid surface 6 and pivotally mounted at 11 to an upper beam 4 rotatably mounted in the aircraft. Ties 16, 17 and 16a, 17a, are provided and two shock absorbers composed of rubber discs 21 and metal plates 22 are used to damp out ground unevenness (see Group XXXII). The upper beam 4 is fast to the splined shaft 35 engaging discs bonded to annular rubber members 44 which are sheared when rotation of beam 4 occurs in the extended position. Referring to Figs. 9 and 13, extension from the retracted position of Fig. 9 is by jack 66 having two diametrically opposed stops 72 adapted to engage the double levers 74 and 75, of which the former has a notch receiving a pin 72 on a flange 78 of beam 5, keeping the skid retracted. On extension of jack 66, the skid does not move until pin 68 on the skid is engaged by the inner end of slot 67, during which movement stop 72 has deflected cam surface 81 on lever 74, unhooking the skid. Extension then takes place, and on completion, the shock absorber of the longitudinal axis automatically locks itself in position so that the skid may resiliently rock in a plane transverse of the aircraft, pin 68 having play in slot 67. Stop 72 follows the dashed path 102. On retraction, the lost motion of the jack due to slot 67 enables stop 72 to deflect lever 75 which rocks a bell crank 88 unlocking the shock absorber, enabling the skid to rotate freely back to the position in Fig. 9, pin 77 automatically re-engaging in the. notch of lever 74. A micro switch 79 is operated by pin 77 on engagement, and may give a visual or aural signal to the pilot. The space opened by the extended skis may be used for dropping personnel, bombs, or the like.