An aerial vehicle including a frame, a housing at least partially enclosing the frame, and a flap assembly mounted to at least one of the frame and the housing. The flap assembly can include a flap and an actuator. The aerial vehicle further can include a communication device coupled to the flap. The actuator can be operable to move the flap relative to the housing to at least partially maintain an orientation of the communication device relative to a remote system.

The invention pertains to a connecting device for connecting a first structural component and a second structural component that can be moved relative to the first structural component in an articulated fashion such that three rotatory degrees of freedom are provided.

A system for calculating forces exerted into an aircraft component includes a test hinge assembly and a monitoring system. In at least one embodiment, the test hinge assembly is a triangular shaped assembly, and includes at least one beam, at least one connecting joint having a channel configured to receive and retain a fastening member, and at least one strain gage secured to an outer surface of the beam(s). The strain gage(s) is configured to detect one or more strains exerted into the beam(s). The monitoring system is in communication with the strain gage(s). The monitoring system is configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) exerted into the beam(s).

A system for calculating forces exerted into an aircraft component includes a test hinge assembly and a monitoring system. In at least one embodiment, the test hinge assembly is a triangular shaped assembly, and includes at least one beam, at least one connecting joint having a channel configured to receive and retain a fastening member, and at least one strain gage secured to an outer surface of the beam(s). The strain gage(s) is configured to detect one or more strains exerted into the beam(s). The monitoring system is in communication with the strain gage(s). The monitoring system is configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) exerted into the beam(s).

A high-lift device comprising an airfoil shaped body having a leading edge and a trailing edge and extending in a spanwise direction configured mainly to generate aerodynamic force; a profile structure arranged to be mounted inside of the airfoil shaped body and extending in spanwise direction of the airfoil shaped body that is configured to provide most of the mechanical strength and stiffness; wherein the airfoil shaped body is provided with an opening extending in spanwise direction at one side through which the profile structure can be fastened and remains accessible inside of the airfoil shaped body.

A high-lift device comprising an airfoil shaped body having a leading edge and a trailing edge and extending in a spanwise direction configured mainly to generate aerodynamic force; a profile structure arranged to be mounted inside of the airfoil shaped body and extending in spanwise direction of the airfoil shaped body that is configured to provide most of the mechanical strength and stiffness; wherein the airfoil shaped body is provided with an opening extending in spanwise direction at one side through which the profile structure can be fastened and remains accessible inside of the airfoil shaped body.

An aircraft including a flap support assembly for a flap support. An aircraft includes a fuselage comprising a pressure deck, where at least a portion the pressure deck is substantially horizontal. The aircraft further includes a wing extending from the fuselage, where the wing includes a leading edge and a trailing edge. The wing additionally includes a flap assembly on the trailing edge of the wing, where the flap assembly is configured to move between an extended position and a retracted position. The aircraft further includes a flap support coupled to the flap assembly comprising a plurality of load-bearing connection points, where at least one of the load-bearing connection points is coupled to the pressure deck.

An aircraft including a flap support assembly for a flap support. An aircraft includes a fuselage comprising a pressure deck, where at least a portion the pressure deck is substantially horizontal. The aircraft further includes a wing extending from the fuselage, where the wing includes a leading edge and a trailing edge. The wing additionally includes a flap assembly on the trailing edge of the wing, where the flap assembly is configured to move between an extended position and a retracted position. The aircraft further includes a flap support coupled to the flap assembly comprising a plurality of load-bearing connection points, where at least one of the load-bearing connection points is coupled to the pressure deck.

Methods and apparatus to control a gap between movable aircraft wing components are disclosed. An example apparatus includes spoiler including a first panel and a second panel, a flexible tip extending from an intersection of the first and second panels; and a rub block coupled to a surface of the second panel, the rub block positioned to engage a flap to maintain a distance between the spoiler and the flap and to enable the flexible tip to perform deform to change aerodynamic properties of the spoiler.

Methods and apparatus to control a gap between movable aircraft wing components are disclosed. An example apparatus includes spoiler including a first panel and a second panel, a flexible tip extending from an intersection of the first and second panels; and a rub block coupled to a surface of the second panel, the rub block positioned to engage a flap to maintain a distance between the spoiler and the flap and to enable the flexible tip to perform deform to change aerodynamic properties of the spoiler.