An aircraft landing gear shock absorber strut 50 comprises: an outer cylinder 52 and a sliding tube 54 within the outer cylinder 52 so as to be movable between compressed and extended positions, further comprising a first piston head 56 upon which pressurised oleo-pneumatic shock absorber fluid acts to force the sliding tube 54 towards the extended position; a second piston head 60 slidably mounted within the sliding tube bore; a piston restraining arrangement 62 configured to limit axial separation between the second piston 60 and the outer cylinder; and a first abutment 68 within the sliding tube bore on the opposite side of the second piston head with respect to the oleo chamber, the first abutment 68 being spaced from the second piston head when the sliding tube 54 is in the extended position, the first abutment 68 being arranged to engage the second piston 60 as the sliding tube moves from the extended position to the compressed position.
Aircraft landing gear shock absorber strut
2025-01-22
Patent
Electronic Resource
English