A plurality of hydraulically operated actuators (11,12) that drive a control surface (100) and a plurality of control systems (13,14) that respectively control the operation of the actuators (11,12) are included. Each of the control systems (13,14) includes a control valve (23,26), a state switching valve (24,27) and a test orifice circuit. The test orifice circuit includes a test orifice used for testing the performance of an orifice. The state switching valve (24,27) is provided such that its position can be switched between an actuator connection position, a damping position and a test orifice position.
Aircraft actuator control apparatus
Stellgliedsteuerungsvorrichtung für Flugzeug
Appareil de commande d'actionneur d'aéronef
08.05.2019
Patent
Elektronische Ressource
Englisch
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