An actuation system has a first actuator 31 and a second actuator 133 both configured to outwardly rotate an aircraft cargo door 13, in use covering an opening into a cargo bay (fig.2,11) when closed. The first actuator may rotate the cargo door from a closed position to a first open position (fig.3), and the second actuator may rotate the cargo door from the first open position to a second open position (fig.15). The first actuator may be a rotary actuator, and the second actuator may be a linear actuator which is controlled to rotate the door independently of the first actuator. A first end of the linear actuator may be coupled to the rotary actuator, and a second end coupled to the cargo door, the rotary actuator moving the first end of the linear actuator to rotate the cargo door via a linkage, the linear actuator rotating the cargo door by increasing a distance between the two ends; alternatively, the second actuator is separate (fig.15,60). The actuators may receive power from different independent power sources, the first actuator power source 35 may be electrical, carried by the aircraft, and the second actuator power source (fig.15,90) is not.
Aircraft cargo door actuation system
2025-04-30
Patent
Electronic Resource
English