초록 ▼

An aircraft comprises first and second wings positioned on opposite sides of a longitudinal axis, a first forward opening control surface attached to an upper surface of the first wing, and a second forward opening control surface attached to an upper surface of the second wing, wherein each of the

An aircraft comprises first and second wings positioned on opposite sides of a longitudinal axis, a first forward opening control surface attached to an upper surface of the first wing, and a second forward opening control surface attached to an upper surface of the second wing, wherein each of the first and second hinges is canted with respect to a direction perpendicular to a longitudinal axis of the aircraft. A method of providing yaw control of an aircraft is also provided. The method comprises the steps of providing a first forward opening, canted spoiler in a top surface of a first wing of the aircraft, providing a second forward opening, canted spoiler in a top surface of a second wing of the aircraft, and operating the first and second spoilers differentially to create a yaw moment. The creation of yaw moments without any down force has application in sweptback wings where the tips are behind the center of gravity of the aircraft. The advantage is in reducing radar cross section over traditional (forward hinged, rearward opening) spoilers where there must be a spoiler on the bottom side to counter the down force created by the top spoiler.

대표청구항 ▼

1. An aircraft comprising:first and second of wings positioned on opposite sides of a longitudinal axis; a first forward opening control surface being attached by a first hinge to an upper surface of the first wing; and a second forward opening control surface being attached by a second hinge to an

1. An aircraft comprising:first and second of wings positioned on opposite sides of a longitudinal axis; a first forward opening control surface being attached by a first hinge to an upper surface of the first wing; and a second forward opening control surface being attached by a second hinge to an upper surface of the second wing; wherein each of the first and second hinges is canted with respect to a direction perpendicular to the longitudinal axis, and wherein the first and second wings do not include openings for air flow under the first and second hinges. 2. The aircraft of claim 1, wherein:each of the first and second hinges is canted at an angle of between 20 and 50 degrees with respect to a line perpendicular to the longitudinal axis. 3. The aircraft of claim 1, wherein:the first and second forward opening control surfaces can be raised to various amounts of opening to generate various amounts of drag, with the drag being displaced laterally from the centerline to produce various amounts of yaw moment. 4. The aircraft of claim 1, wherein:the first forward opening control surface has a substantially rectangular shape, with the aft edge of the first forward opening control surface being connected to the first wing by the first hinge; and the second forward opening control surface has a substantially rectangular shape, with the aft edge of the second forward opening control surface being connected to the second wing by the second hinge. 5. The aircraft of claim 1, wherein the first forward opening control surface, and the second forward opening control surface each comprise an inlay spoiler for controlling yaw without the introduction of any up or down force.6. An aircraft, comprising:an integrated fuselage/wing structure generally defining the aircraft; a first forward opening control surface integrally formed with an upper surface of the integrated fuselage/wing, and connected to the upper surface of the integrated fuselage/wing by a first hinge; and a second forward opening control surface integrally formed with the upper surface of the integrated fuselage/wing, and connected to the upper surface of the integrated fuselage/wing by a second hinge; wherein the first and second control surfaces are canted with respect to air flow during flight of the aircraft, and wherein the integrated fuselage/wing does not include openings for air flow under the first and second hinges. 7. An aircraft according to claim 6, wherein the integrated fuselage/wing structure comprises:first and second wings positioned on opposite sides of a longitudinal axis with each of the wings including a substantially straight swept-back leading edge, a lower surface extending aft from the leading edge, and an upper surface extending aft from the leading edge; and wherein each of the first and second hinges is canted with respect to a direction perpendicular to the longitudinal axis. 8. The aircraft of claim 7, wherein:each of the first and second hinges is canted at an angle of between 20 and 50 degrees with respect to a line perpendicular to the longitudinal axis. 9. The aircraft of claim 7, wherein:the first and second forward opening control surfaces can be raised to various amounts of opening to generate various amounts of drag, with the drag being displaced laterally from the centerline to produce various amounts of yaw moment. 10. The aircraft of claim 6, wherein:the first forward opening control surface has a substantially rectangular shape, with the aft edge of the first forward opening control surface being connected to the first wing by a first hinge; and the second forward opening control surface has a substantially rectangular shape, with the aft edge of the second forward opening control surface being connected to the second wing by a second hinge. 11. The aircraft of claim 6, wherein the first forward opening control surface, and the second forward opening control surface each comprise an inlay spoiler for controlling yaw without the introduction of any up or down force.12. A method of providing yaw control of an aircraft, the method comprising the steps of:providing a first forward opening, canted spoiler in a top surface of a first wing of the aircraft, wherein the first spoiler includes an aft edge connected to the first wing by a first hinge, and the first wing does not include an opening for air flow under the first hinge; providing a second forward opening, canted spoiler in a top surface of a second wing of the aircraft, wherein the second spoiler includes an aft edge connected to the second wing by a second hinge, and the second wing does not include an opening for air flow under the second hinge; and operating the first and second spoilers differentially to create a yaw moment. 13. The method of claim 12, wherein:each of the first and second hinges is canted at an angle of between 20 and 50 degrees with respect to a line perpendicular to the g longitudinal axis. 14. The method of claim 12, wherein:the first and second forward opening control surfaces can be raised to various amounts of opening to generate various amounts of drag, with the drag being displaced laterally from the centerline to produce various amounts of yaw moment. 15. The method of claim 12, wherein:the first forward opening control surface has a substantially rectangular shape; and the second forward opening control surface has a substantially rectangular shape. 16. The method of claim 12, wherein the first forward opening control surface, and the second forward opening control surface each comprise an inlay spoiler for controlling yaw without the introduction of any up or down force.