| 摘要 |
The invention relates to a hydraulically actuatable horizontal stabilizer of an aircraft comprising: two actuators (1, 2) that are supplied by at least one hydraulic-supply system (A, B) and a supporting structural component (M) is coupled to each actuator and a horizontal stabilizer (H) that can be controlled in relation to the supporting structural support (M) and which is designed for actuating therewith, a first control valve device (11) that is hydraulically connected to said first actuator for controlling said actuator (1) and a second control valve device (12) that is hydraulically connected to said second actuator (2) for controlling said actuator, said two valve devices being respectively supplied by a hydraulic-system (A, B), a control and monitoring device (10) that is functionally connected to the control valve devices (11, 12) that detect the corresponding command signals for the control valve devices (11, 12) and sends them to said devices in order to carry out corresponding control movements for actuating the actuators (1, 2), a locking device (20) that is coupled to the first actuator (1) and which comprises a locking mechanism for fixing the exit position of the slide rod (7) of the first actuator (1) in the locked state, said locking device being hydraulically connected to the first hydraulic-system (A) and with the second hydraulic-system (B) by means of a hydraulic or circuit such that in normal operation of at least one of the hydraulic systems, the locking mechanism is in the unlocked state and when both hydraulic systems (A, B) fall below a minimum pressure, the locking mechanism blocks the exit position of the slide rod (7) of the first actuator (1) and/or a locking activation device (21, 22) that is functionally connected to the control and monitoring device (10) and which activates the locking mechanism to the reception of the activation signal. The invention also relates to test methods for controlling the integrity of a control system.
|
