Flight control device to provide directional control

Claim 2

In an airplane having a fuselage which has a forebody terminating in a fuselage nose, the forebody creating forebody vortices during high angle of attack flight, the airplane having a pair of wings extending from opposite sides of the fuselage to provide lift, an improved apparatus for controlling yaw of the airplane during high angles of attack, comprising in combination: a chine support member carried forward of the nose of the airplane, the chine support member having a chine axis which extends along the length of the airplane, the chine support member being rotatable relative to the nose about the chine axis; a chine mounted to the chine support member, the chine comprising a pair of substantially thin flight control surfaces mounted on opposite sides of the chine support member forward of the nose and configured for creating chine vortices independent of the forebody vortices; a drive motor in engagement with the chine support member for rotating the chine support member and the chine about the chine axis; and control means for controlling the drive motor to position the chine at selected vortices to interact with and move the forebody vortices to generate directional control moments to control yaw.

Claim 3

The airplane according to claim 1 wherein the flight control surfaces of the chine have a total aerodynamic surface area that is substantially less than the total aerodynamic surface area of the wings.

Claim 4

The airplane according to claim 1 wherein the flight control surfaces of the chine have a total aerodynamic surface area that is in the range of 0.05 to 0.5 percent of the aerodynamic surface area of the wings.

Claim 5

The airplane according to claim 1 wherein the chine has a neutral portion relative to the wings wherein each of the flight control surfaces is at the same orientation relative to the wings, and wherein the control means controls the drive motor to rotate the chine support no more than 90 degrees in any direction from the neutral position.

Claim 6

The airplane according to claim 1 wherein the chine has a neutral position relative to the wings wherein each of the flight control surfaces is at the same angular position relative to the wings, and wherein the control means prevents the drive motor from rotating the chine support and the flight control surfaces more than 60 degrees in any direction from the neutral position.

Claim 7

The airplane according to claim 1 wherein: the airplane has a leading edge contour on its nose as seen in a cross-sectional view taken along a plane that passes through a longitudinal axis of the airplane and is substantially parallel to a plane of the wings; and the flight control surfaces of the chine have leading edges and trailing edges and a substantially constant cross-sectional thickness from the leading edge to the trailing edge, the trailing edges having a recessed central portion with a contour that matches the leading edge contour of the nose of the airplane, the central portion of the trailing edges being spaced closely to the leading edge contour of the nose of the airplane.

Claim 8

The airplane according to claim 1 wherein: the airplane has a leading edge contour on its nose as seen in a cross-sectional view taken along a plane that passes through a longitudinal axis of the airplane and is substantially parallel to a plane of the wings; and wherein the flight control surfaces of the chine have leading edges and trailing edges, the leading edges sweeping back and diverging, the trailing edges having a recessed central portion with a contour that matches the leading edge contour of the nose of the airplane, the central portion of the trailing edges being spaced closely to the leading edge contour of the nose of the airplane.

Claim 9

In an airplane having a fuselage which has a longitudinal axis, a fuselage nose having a leading edge contour, the airplane having means including a pair of wings extending from opposite sides of the fuselage for producing lift, an improved apparatus for controlling yaw of the airplane during high angles of attack, comprising in combination; a chine support member carried forward of the nose, the chine support member having a chine axis which is substantially parallel to the longitudinal axis of the airplane, the chine support member being rotatable relative to the nose about the chine axis; a chine mounted to the chine support member forward of the nose, and configured for creating chine vortices independent of the forebody vortices, the chine comprising a pair of flight control surfaces rigidly mounted on opposite sides of the chine support member for rotation with the chine support member, the flight control surfaces having a neutral position in which each flight control surface lies at the same angle relative to a plane of the wings; the chine having leading edges which sweep back and diverge, terminating at trailing edges, the flight control surfaces being thin, substantially flat sheets substantially constant in cross-sectional thickness from the leading edges to the trailing edges; the flight control surfaces of the chine having a total aerodynamic surface area that is substantially less than the total aerodynamic surface area of the wings; drive motor means in engagement with the chine support member for rotating the chine support member and the chine about the chine axis; and control means for controlling the drive motor means to change the angle of the flight control surfaces relative to the wings from the neutral position to positions less than 90 degrees from the neutral position in any direction to cause the chine vortices to interact with and move the forebody vortices to generate directional control moments to control yaw.

Claim 10

In an airplane having a fuselage which has a longitudinal axis, a fuselage nose having a leading edge contour, the airplane having means including a pair of wings extending from opposite sides of the fuselage for producing lift, an improved apparatus for controlling yaw of the airplane during high angles of attack, comprising in combination; a chine support member carried forward of the nose, the chine support member having a chine axis which is substantially parallel to the longitudinal axis of the airplane, the chine support member being rotatable relative to the nose about the chine axis; a chine mounted to the chine support member forward of the nose, and configured for creating chine vortices independent of the forebody vortices, the chine comprising a pair of flight control surfaces rigidly mounted on opposite sides of the chine support member for rotation with the chine support member, the flight control surfaces having a neutral position in which each flight control surface lies at the same angle relative to a plane of the wings; the chine having leading edges which sweep back and diverge, terminating at trailing edges, the flight control surfaces being thin, substantially flat sheets substantially constant in cross-sectional thickness from the leading edges to the trailing edges; the flight control surfaces of the chine having a total aerodynamic surface area that is substantially less than the total aerodynamic surface area of the wings; drive motor means in engagement with the chine support member for rotating the chine support member and the chine about the chine axis; and control means for controlling the drive motor means to change the angle of the flight control surfaces relative to the wings from the neutral position to positions less than 90 degrees from the neutral position in any direction to cause the chine vortices to interact with and move the forebody vortices to generate directional control moments to control yaw.

Claim 11

The airplane according to claim 8 wherein the total aerodynamic surface area of the flight control surfaces of the chine is in the range of 0.05 to 0.5 percent of the total aerodynamic surface area of the wings.

Claim 12

The airplane according to claim 8 wherein the control means prevents the drive motor means from rotating the chine support and the flight control surfaces more than 60 degrees from the neutral position in any direction.

Claim 13

The airplane according to claim 8 wherein the airplane has a leading edge contour on its nose as seen in a cross-sectional view taken along a plane that passes through the longitudinal axis of the airplane and is substantially parallel to a plane of the wings; and wherein the trailing edges of the flight control surfaces of the chine have portions which extend alongside a portion of the leading edge contour of the nose.