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 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.

Assemblies for air vehicle control surfaces and related methods are disclosed. An example apparatus includes a control surface; a bullnose carried by the control surface, the bullnose moveable relative to the control surface; a first actuator operatively coupled to the control surface to cause the control surface to rotate; and a second actuator operatively coupled to the control surface, the second actuator to cause the bullnose to move from a first position to a second position to cause an opening to be formed relative to the control surface, the movement of the bullnose independent of rotation of the control surface.

Assemblies for air vehicle control surfaces and related methods are disclosed. An example apparatus includes a control surface; a bullnose carried by the control surface, the bullnose moveable relative to the control surface; a first actuator operatively coupled to the control surface to cause the control surface to rotate; and a second actuator operatively coupled to the control surface, the second actuator to cause the bullnose to move from a first position to a second position to cause an opening to be formed relative to the control surface, the movement of the bullnose independent of rotation of the control surface.

Described herein is an aircraft. The aircraft comprises a body. The aircraft also comprises a wing coupled to and extending from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The aircraft further comprises a strut. The strut comprises a strut inboard end portion coupled to and extending from the body and a strut outboard end portion coupled to and extending from the intermediate portion of the wing. The aircraft additionally comprises at least one aerodynamic control surface movably coupled to the strut.

Described herein is an aircraft. The aircraft comprises a body. The aircraft also comprises a wing coupled to and extending from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The aircraft further comprises a strut. The strut comprises a strut inboard end portion coupled to and extending from the body and a strut outboard end portion coupled to and extending from the intermediate portion of the wing. The aircraft additionally comprises at least one aerodynamic control surface movably coupled to the strut.

A dispenser for storing and launching countermeasures from an aircraft, comprising an elongate body provided with at least one launch opening adapted for storing the countermeasures in cartridges, where the dispenser comprises a manoeuvrable spoiler arranged in front of the launch opening, where the spoiler is adapted to be fully retracted before a countermeasure has been launched, and that the spoiler is adapted to extend outwards in a predefined manner when a countermeasure has been launched. The advantage of the invention is that a spoiler will reduce induced noise from the open cartridges by extending a spoiler outwards depending on the number of launched countermeasures. This allows for a simple, reliable and cost-effective solution.

A dispenser for storing and launching countermeasures from an aircraft, comprising an elongate body provided with at least one launch opening adapted for storing the countermeasures in cartridges, where the dispenser comprises a manoeuvrable spoiler arranged in front of the launch opening, where the spoiler is adapted to be fully retracted before a countermeasure has been launched, and that the spoiler is adapted to extend outwards in a predefined manner when a countermeasure has been launched. The advantage of the invention is that a spoiler will reduce induced noise from the open cartridges by extending a spoiler outwards depending on the number of launched countermeasures. This allows for a simple, reliable and cost-effective solution.

An air flow channeling yaw control device includes a vane cover, a vane array, and an actuator. The vane array includes a plurality of vanes, each of the plurality of vanes comprising a first edge and a second edge, the first edge being hingedly coupled to the vane cover and the second edge being hingedly coupled to a wing of an aircraft. The wing includes a leading edge and a trailing edge. The actuator is configured to move the plurality of vanes from a retracted position into a deployed position. The plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over the leading edge of the wing through channels created by the plurality of vanes. The plurality of vanes, when moved into the retracted position, are configured to retract within the wing.

An air flow channeling yaw control device includes a vane cover, a vane array, and an actuator. The vane array includes a plurality of vanes, each of the plurality of vanes comprising a first edge and a second edge, the first edge being hingedly coupled to the vane cover and the second edge being hingedly coupled to a wing of an aircraft. The wing includes a leading edge and a trailing edge. The actuator is configured to move the plurality of vanes from a retracted position into a deployed position. The plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over the leading edge of the wing through channels created by the plurality of vanes. The plurality of vanes, when moved into the retracted position, are configured to retract within the wing.