Abstract: A flight control system controls flight of an unmanned aerial vehicle by control signals of the unmanned aerial vehicle itself and from a ground facility. The unmanned aerial vehicle and the ground facility are each provided with at least one flight control unit (FCU) capable of controlling driving of an airframe actuator based on a sensor output signal from an airframe sensor. The at least one FCU on the unmanned aerial vehicle and the at least one FCU of the ground facility constitute a redundant system for flight control function. In the redundant system one of the at least one FCU on the unmanned aerial vehicle serves as a main unit. In the case where a malfunction has occurred in an FCU that performs flight control on the unmanned aerial vehicle, the ground facility is capable of causing another FCU to take over flight control function from the FCU.

Abstract: A flight control system controls flight of an unmanned aerial vehicle by control signals of the unmanned aerial vehicle itself and from a ground facility. The unmanned aerial vehicle and the ground facility are each provided with at least one flight control unit (FCU) capable of controlling driving of an airframe actuator based on a sensor output signal from an airframe sensor. The at least one FCU on the unmanned aerial vehicle and the at least one FCU of the ground facility constitute a redundant system for flight control function. In the redundant system one of the at least one FCU on the unmanned aerial vehicle serves as a main unit. In the case where a malfunction has occurred in an FCU that performs flight control on the unmanned aerial vehicle, the ground facility is capable of causing another FCU to take over flight control function from the FCU.

Abstract: A disengage device in an aircraft, which prevents a driving force of a drive unit from transmitting to a control surface, having: a first rod having one end portion connected to the drive unit, the other end portion, and a hollow portion formed to have a predetermined length and open at the other end portion; a branch pipe which is connected to a side wall of the first rod and communicates with the hollow portion; a second rod having one end portion connected to the push-pull rod, the other end portion, and a recess portion formed in a part of a side wall of a portion which extends a predetermined length from the other end portion to the one end portion side and is inserted in the hollow portion; and an engaging member arranged to be freely movable in the branch pipe, which is engagable with the recess portion.

Abstract: A disengage device in an aircraft, which prevents a driving force of a drive unit from transmitting to a control surface, having: a first rod having one end portion connected to the drive unit, the other end portion, and a hollow portion formed to have a predetermined length and open at the other end portion; a branch pipe which is connected to a side wall of the first rod and communicates with the hollow portion; a second rod having one end portion connected to the push-pull rod, the other end portion, and a recess portion formed in a part of a side wall of a portion which extends a predetermined length from the other end portion to the one end portion side and is inserted in the hollow portion; and an engaging member arranged to be freely movable in the branch pipe, which is engagable with the recess portion.