An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

A health monitoring method for checking a functionality of a flight control surface driving apparatus using a load sensor for sensing a load imposed on a control surface drive device by: blocking movement of the transmission device with a brake device, commanding the control surface drive device to apply a load on the blocked transmission device, and determining whether a load sensor output signal of the load sensor is within a predetermined range. Also, a flight control surface drive apparatus, a flight control system and an aircraft.

A health monitoring method for checking a functionality of a flight control surface driving apparatus using a load sensor for sensing a load imposed on a control surface drive device by: blocking movement of the transmission device with a brake device, commanding the control surface drive device to apply a load on the blocked transmission device, and determining whether a load sensor output signal of the load sensor is within a predetermined range. Also, a flight control surface drive apparatus, a flight control system and an aircraft.

A linear actuator driven flap mechanism for an aircraft wing is contained within a wing support and fairing of the aircraft wing. The rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at a first and second point. The rib frame of the flap mechanism defines a width with a first and second web. A linear actuator and a motion linkage are positioned with the width between the first and second webs of the rib frame. The linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation. As a result of the compact construction, the flap mechanism can be employed in thinner, smaller aircraft wings being designed today.

A linear actuator driven flap mechanism for an aircraft wing is contained within a wing support and fairing of the aircraft wing. The rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at a first and second point. The rib frame of the flap mechanism defines a width with a first and second web. A linear actuator and a motion linkage are positioned with the width between the first and second webs of the rib frame. The linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation. As a result of the compact construction, the flap mechanism can be employed in thinner, smaller aircraft wings being designed today.

A drive mechanism, a drive system and an aerodynamic structure for an aircraft, each including at least one articulated module comprising four links. Each link includes three coupling points distributed forming a triangular geometry. The links are coupled to each other such that an articulation with only one degree of freedom is provided.

A drive mechanism, a drive system and an aerodynamic structure for an aircraft, each including at least one articulated module comprising four links. Each link includes three coupling points distributed forming a triangular geometry. The links are coupled to each other such that an articulation with only one degree of freedom is provided.

A harmonic drive, having a housing extending from first to second outer ends, the housing has radial outer and inner walls that extend axially between the first and second outer ends of the housing to define an annular channel having first and second ends that taper toward the first and second outer ends of the housing; a flex spline that extends axially between first and second ends and has a radial outer surface, and the first and second ends of the flex spline taper radially outwardly, the flex spline is located within the annular channel so that the first end of the flex spline is located within the first end of the annular channel and the second end of the flex spline is located within the second end of the annular channel; and first and second clamps that are clamped against the first and second ends of the annular channel.

A harmonic drive, having a housing extending from first to second outer ends, the housing has radial outer and inner walls that extend axially between the first and second outer ends of the housing to define an annular channel having first and second ends that taper toward the first and second outer ends of the housing; a flex spline that extends axially between first and second ends and has a radial outer surface, and the first and second ends of the flex spline taper radially outwardly, the flex spline is located within the annular channel so that the first end of the flex spline is located within the first end of the annular channel and the second end of the flex spline is located within the second end of the annular channel; and first and second clamps that are clamped against the first and second ends of the annular channel.