Patent ID: 8636245
Filing Date: 2014-01-28
Classification: B64C,F15B

Abstract:
1. An aircraft comprising: at least one in-flight attitude control system, comprising at least one actuator; a hydraulic circuit connected to said at least one actuator and comprising at least one pump adapted to deliver a first flow when the pressure of the hydraulic circuit is above a presettable threshold value, wherein said pump is adapted to deliver a second flow greater than said first flow, said second flow providing a pressure of the hydraulic circuit greater than a certification pressure of the hydraulic circuit; a sensor adapted to detect a quantity associated with the pressure of said hydraulic circuit; and a programmable central control unit, which controls said pump to deliver said second flow when said quantity detected by said sensor corresponds to a pressure of said hydraulic circuit below said threshold value; wherein said central control unit is adapted to control said pump to deliver said second flow for a predetermined length of time during a boost cycle, in the event of exceptional power demand by said actuator, and said control unit is adapted to automatically switch said pump to said first flow, at the end of said boost cycle; wherein said pump is a variable-displacement axial-piston pump having a delivery, said pump comprising: