An actuation system (16) for a control surface (6c, 8c, 10c) for an aircraft (2) is disclosed. The actuation system (16) comprises a first, second, third and fourth actuator (18, 20, 22, 24), a first and second bell crank (26, 28), and at least one push pull rod system (30). Each of the first and second bell cranks (26, 28) comprises a first and a second crank arm (90, 98, 92, 100), the first and second crank arms (90, 98, 92, 100) intersect with and are joined to each other at an intersection (93, 101), the first and second crank arms (90, 98, 92, 100) extend from the intersection (93, 101) at an angle to each other, the first bell crank (26) is pivotally connected to the sub-structure by a first pivot (86) extending through the first bell crank's intersection (93), and the second bell crank (28) is pivotally connected to the sub-structure by a second pivot (94) extending through the second bell crank's intersection (101). The first and third actuators (18, 22) have first and second ends, the first ends of the first and third actuators are connected to the sub-structure, the second end of the first actuator is connected to the first crank arm of the first bell crank at a first connection position, the second end of the third actuator is connected to the first crank arm of the first bell crank at a third connection position. The second and fourth actuators (20, 24) have first and second ends, the first ends of the second and fourth actuators are connected to the sub-structure, the second end of the second actuator is connected to the first crank arm of the second bell crank at a second connection position, the second end of the fourth actuator is connected to the first crank arm of the second bell crank at a fourth connection position. In the first bell crank (26) the distance (D1) between the first connection position and the first pivot (86) is greater than the distance (D3) between the third connection position and the first pivot (86), and in the second bell crank (28) the distance (D2) between the second connection position and the second pivot (94) is greater than the distance (D4) between the fourth connection position and the second pivot (94).
ACTUATION SYSTEMS FOR CONTROL SURFACES FOR AIRCRAFT
BETÄTIGUNGSSYSTEME FÜR STEUERFLÄCHEN FÜR FLUGZEUGE
SYSTÈMES D'ACTIONNEMENT POUR SURFACES DE COMMANDE D'AÉRONEF
2022-07-20
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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