In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

Systems and methods are provided for a track roller failure detection system. The system may include a main aerodynamic device and a secondary aerodynamic device including a track supported by one or more rollers and a marker. Failure of the one or more rollers may result in the track contacting the marker. Operation of the secondary aerodynamic device when one or more of the rollers have failed may result in the marker leaving a mark and/or a trail on a portion of the main aerodynamic device and/or a portion of the secondary aerodynamic device. Failure of the one or more rollers may then be determined from the mark and/or trail.

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 joining structure according to one embodiment of the present invention includes a first member and a second member, the first member having a hole extending along an axis direction, the second member including a shaft member, the shaft member being formed of a fiber-containing composite material and having a shape to fit in the hole, the second member being joined to the first member via the shaft member so that movement thereof in the axis direction is restricted.

A joining structure according to one embodiment of the present invention includes a first member and a second member, the first member having a hole extending along an axis direction, the second member including a shaft member, the shaft member being formed of a fiber-containing composite material and having a shape to fit in the hole, the second member being joined to the first member via the shaft member so that movement thereof in the axis direction is restricted.

In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.

In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.

Variable angular compression seal assemblies are disclosed that may usefully be employed to seal movable aircraft components, e.g., so as to seal a flap torque tube operating in a flap track cutout opening in a wing to fuselage fairing. The seal assembly may be provided so as to seal a component moveable between first and second positions within a cutout opening. The seal assembly includes a split seal having opposed seal members in non-compressive contact with one another along a split line between opposed ends of the seal members so as to allow the component to be moved along the split line between the first and second positions thereof. The seal members include opposed wall portions at one end thereof defining a recess for receiving the moveable component when in the first position thereof. The split line between the opposed seal members can be variably curved.

Variable angular compression seal assemblies are disclosed that may usefully be employed to seal movable aircraft components, e.g., so as to seal a flap torque tube operating in a flap track cutout opening in a wing to fuselage fairing. The seal assembly may be provided so as to seal a component moveable between first and second positions within a cutout opening. The seal assembly includes a split seal having opposed seal members in non-compressive contact with one another along a split line between opposed ends of the seal members so as to allow the component to be moved along the split line between the first and second positions thereof. The seal members include opposed wall portions at one end thereof defining a recess for receiving the moveable component when in the first position thereof. The split line between the opposed seal members can be variably curved.