Methods, systems, and assemblies for controlling flight control surfaces of an aircraft wing are described. The method comprises displacing a first trailing edge of a first flight control surface towards a contact surface of a second flight control surface; determining a mechanical stiffness of the first flight control surface as defined by a ratio of F/X as the first flight control surface is displaced, where F is a difference in force F applied to at least two different positions X1 and X2 of the first flight control surface at times T1 and T2, and X is a difference in position X2X1; and achieving full contact between the first trailing edge and the second leading edge when a known full contact mechanical stiffness is reached.

Methods, systems, and assemblies for controlling flight control surfaces of an aircraft wing are described. The method comprises displacing a first trailing edge of a first flight control surface towards a contact surface of a second flight control surface; determining a mechanical stiffness of the first flight control surface as defined by a ratio of F/X as the first flight control surface is displaced, where F is a difference in force F applied to at least two different positions X1 and X2 of the first flight control surface at times T1 and T2, and X is a difference in position X2X1; and achieving full contact between the first trailing edge and the second leading edge when a known full contact mechanical stiffness is reached.

A morphing airfoil system includes an airfoil having a bulkhead structured to form a leading edge of the airfoil. A first spool is rotatably coupled to the bulkhead, and a second spool is rotatably coupled to the bulkhead opposite the first spool. An airfoil skin has a first end secured to the first spool, a second end secured to the second spool, and a portion extending between the first and second spools to form an exterior surface of the airfoil. The airfoil skin is structured to be windable around the first and second spools such that a configuration of the airfoil is controllable by rotating at least one of the first spool and the second spool so as to wind a portion of the airfoil skin around, or unwind a portion of the airfoil skin from, the at least one of the first spool and the second spool.

A morphing airfoil system includes an airfoil having a bulkhead structured to form a leading edge of the airfoil. A first spool is rotatably coupled to the bulkhead, and a second spool is rotatably coupled to the bulkhead opposite the first spool. An airfoil skin has a first end secured to the first spool, a second end secured to the second spool, and a portion extending between the first and second spools to form an exterior surface of the airfoil. The airfoil skin is structured to be windable around the first and second spools such that a configuration of the airfoil is controllable by rotating at least one of the first spool and the second spool so as to wind a portion of the airfoil skin around, or unwind a portion of the airfoil skin from, the at least one of the first spool and the second spool.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

An aircraft wing having a fixed root part hingedly connected to a moveable tip part is disclosed. The tip part is configured to pivot relative to the root part about a substantially horizontal axis, between a load-alleviating configuration in which the tip part is oriented relative to the root part such that at least one of the upper and lower surface of the tip part is positioned away from the respective surface of the root part and a flight configuration in which the upper and lower surfaces of the tip part are continuations of the upper and lower surfaces of the root part. The shape of the tip part is controllably switchable between a cruise shape in which the tip part has positive camber and a recovery shape in which the tip part has negative camber.

A device to fasten a system to a structure of a vehicle includes a drive unit that provides rotary movement of a drive element relative to the structure. The device has first and second supporting elements. The first supporting element is rotatably coupled to the drive element via a first rotation axis, and is rotatably mounted to the structure via a second rotation axis. The second supporting element is rotatably coupled to the first supporting element, and a first connecting element, which is rotatably mounted to the structure via a third rotation axis. The first connecting element is rotatably coupled to the second supporting element via a fourth rotation axis. The second supporting element is rotatably coupled to the first supporting element via a fifth rotation axis. During movement, the first supporting element has a different rotational speed than the second supporting element.