GB524929A - Improvements relating to aircraft undercarriages with resiliently mounted landing elements - Google Patents

Abstract

524,929. Aircraft landing gear. DOWTY, G. H. Jan. 13, 1939, No. 1269. [Class 4] A retractable aircraft undercarriage comprises a non-yielding supporting structure such as a leg, a pair of alighting elements mounted side by side on substantially coaxial transverse axles connected to the supporting structure by a deformable articulated frame, including a telescopic shock-absorber, arranged in a plane between the alighting elements. Two wheels 5 are mounted on stub axles extending slightly downwardly from opposite sides of a cylinder 8 on an arm SA pivoted to a rigid leg 3. A hollow piston 10 works in the cylinder 8, a connecting-rod 13 being interposed between the upper end of the piston and a pivot 14 on the leg 3. An inner piston 11 divides off an airspace in the piston 10, the rest of the piston 10 and cylinder 8 being filled with oil which is forced through restricted holes 12 in the piston 10 as the air is compressed under the load. The shock absorber and articulated mounting is similar to that described in Specification 522,833. The wheels may be replaced by skis, floats, or endless track elements. The leg 3 is retractable, the twin elements taking up less vertical space, when retracted into a wing, than an equivalent single wheel or other landing element. According to the Provisional Specification the two elements may be mounted on separate arms which act to displace liquid into a common compressed air chamber affording an equalized pressure on the two arms.