The landing gear system disclosed herein may comprise a shrink pump (41) and a shrink valve (44) that are capable of shrinking a landing gear (20) by up to 40% of its available stroke, or more depending on the air spring configuration. The shrink pump (41) may be configured to pump fluid (e.g., a hydraulic fluid) between an oil chamber (38, 39), where hydraulic fluid is likely present and a shrink chamber (36) to shrink the landing gear (20). Moreover, the shrink pump (41) and shrink valve (44) may be part of a strut shrink system (40).
Shrink strut landing gear system
Schrumpfstreben-Fahrwerksystem
Système de train d'atterrissage d'entretoise rétractable
2016-05-25
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
LANDING GEAR ARRANGEMENT WITH PASSIVE SHOCK STRUT SHRINK ACTUATOR
European Patent Office | 2018
|LANDING GEAR ARRANGEMENT WITH PASSIVE SHOCK STRUT SHRINK ACTUATOR
European Patent Office | 2018
|