A hydraulic system 300 suitable for an aircraft has a backup hydraulic pressure source 216, to provide hydraulic pressure to a brake 222; and to a landing gear backup system, providing hydraulic pressure for extension and/or retraction of landing gear 100. The backup hydraulic pressure source provides pressure in response to the detection of a failure condition of primary hydraulic pressure sources 202, such as a reduction in the hydraulic pressure beyond a specified threshold. The backup hydraulic pressure source may be an accumulator 216, receiving a supply of pressurised hydraulic fluid from a primary pressure source 202 powered by the aircraft. A controller 304 may detect the failure condition and transmit an activation signal to a valve 302, directing hydraulic fluid from the backup pressure source 2016 to the landing gear backup system. The backup hydraulic pressure source may provide pressure to deactivate a landing gear lock 304, holding the landing gear in a retracted state; and a landing gear door lock 306, holding a landing gear door in a closed state.
Aircraft hydraulics
2018-12-26
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
SLUB | 1957
SLUB | 1957
Engineering Index Backfile | 1943
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