GB459562A - Improvements in shock struts for aircraft - Google Patents

Abstract

459,562. Shock absorbers. BENDIX AVIATION CORPORATION, 105, West Adams Street, Chicago, Illinois, U.S.A. Oct. 10, 1935, No. 27988. Convention date, Oct. 11, 1934. Addition to 456,897. [Class 108 (iii)] Relative angular movement between the two tubular telescoping members 10, 12 of the hydraulic shock-absorbing strut claimed in the parent Specification is prevented by a concealed splined connection, the inner member having a limited splined portion 72 on its outer surface for engaging splines 70 on the inner surface of the outer member, followed by a smooth portion 58 engaged by packing 52 and /or guiding means at the open end of the outer member. The lower end of the member 10 comprises an apertured piston 18, flow of liquid through which is controlled by a metering pin 40 on the member 12 and by a tubular housing 33 on the piston having a one-way valve 42 permitting free upward flow of liquid and bleed apertures 44 for restricting the downward flow. The upper end of the member 12 contains compressed air which, after the initial shock is absorbed resiliently supports the load of the aircraft. In order to limit extension of the strut, the splined portion 72 2 ends in a shoulder adapted to engage a packing- retaining ring 48. A landing-wheel stub-axle 14 4 is secured to lugs 60, 62 integral with a cap 34 closing the lower end of the member 12, and a plate 64, to which braking-members or a brake backing-plate may be secured, is splined on the axle. In modified constructions, (a.) one of the telescoping members is formed with concentric tubular casings between which the other member reciprocates, and (b) a splined sleeve is rigidly secured to the inner tubular member for engagement with the outer member.