CPC F15B 15/18 (2013.01) [B64C 25/22 (2013.01); B64C 25/24 (2013.01); F15B 13/0444 (2013.01); F15B 2211/20515 (2013.01)] | 20 Claims |
1. An aircraft power system, comprising:
i) a hydraulic reservoir,
ii) a bi-directional hydraulic pump for pumping hydraulic fluid to and from the hydraulic reservoir, and
iii) an electric motor,
wherein the electric motor is connectable to a first driveable component of aircraft such that the electric motor is arranged to drive the first driveable component of the aircraft, and
wherein the bi-directional hydraulic pump is connectable to the first driveable component of the aircraft such that the bi-directional hydraulic pump is arranged to drive the first driveable component, such that, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the bi-directional hydraulic pump,
wherein the electric motor and bi-directional hydraulic pump are connected in parallel such that, in the first driveable mode of operation, both are arranged to supply power to the driveable component independently of the other, and
wherein the electric motor is connectable to the bi-directional hydraulic pump such that, during a replenishing mode of operation, the electric motor is arranged to drive the bi-directional hydraulic pump to pump hydraulic fluid into the hydraulic reservoir.
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