In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. 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.

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.

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.

Methods and devices to measure an angular deflection of an aircraft member. The devices are configured to be attached to the aircraft member. The devices are configured to obtain an orientation of the device about three separate axes. The methods use initial orientation values and dynamic orientation values to calculate an axis of rotation. Using the axis of rotation, the deflection angle can be calculated for the aircraft member.

Methods and devices to measure an angular deflection of an aircraft member. The devices are configured to be attached to the aircraft member. The devices are configured to obtain an orientation of the device about three separate axes. The methods use initial orientation values and dynamic orientation values to calculate an axis of rotation. Using the axis of rotation, the deflection angle can be calculated for the aircraft member.

A winglet includes a winglet body and a control body. The winglet body includes a first winglet surface arranged opposite a second winglet surface. The second winglet surface is joined to the first winglet surface to form front and trailing edges of the winglet body. The second winglet surface defines a control body seat. The control body is coupled to the winglet body to move between a stowed position seated in the control body seat and a deployed position rotated out of the control body seat. The control body includes a first control surface arranged to face toward the winglet body, a second control surface arranged opposite the first control surface to face away from the winglet body and joined to the first control surface to form a trailing edge of the control body and a control front connecting the first control surface and the second control surface.

An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

An aircraft wing includes a groove extending along a length between a forward extremity and an aft extremity. A forward segment of the groove extends upwardly to the forward extremity. The forward extremity is a highest point of the groove. A flap carriage is mounted to the groove and displaceable therealong. A flap is pivotably attached to the flap carriage to define a flap pivot axis about which the flap is rotatable. The flap is displaceable with the flap carriage. An actuator has an arm being extendable between an extended position and a retracted position to displace the flap carriage along the groove. The flap carriage in the retracted position being disposed in the forward segment of the groove and the flap being rotated about the flap pivot axis to position the flap trailing edge in negative flap deployment.

An aircraft wing includes a groove extending along a length between a forward extremity and an aft extremity. A forward segment of the groove extends upwardly to the forward extremity. The forward extremity is a highest point of the groove. A flap carriage is mounted to the groove and displaceable therealong. A flap is pivotably attached to the flap carriage to define a flap pivot axis about which the flap is rotatable. The flap is displaceable with the flap carriage. An actuator has an arm being extendable between an extended position and a retracted position to displace the flap carriage along the groove. The flap carriage in the retracted position being disposed in the forward segment of the groove and the flap being rotated about the flap pivot axis to position the flap trailing edge in negative flap deployment.