Aircraft wing stall control device and method

Claim 2

In a wing of an aircraft, where the wing comprises: (a) a main wing structure having an upper aerodynamic surface, a lower aerodynamic surface, and a forward surface portion that extends upwardly toward said upper aerodynamic surface; (b) a leading edge member which is moveable between a stowed position for cruise mode where the device aerodynamically conceals the surface of the main wing structure, and a deployed position for high-lift mode where the device forms with the forward surface portion of the main wing structure a slot for passage of air upwardly therethrough and over the wing upper surface; (c) said wing being characterized in that within a predetermined range of high angles of attack and with the leading edge member deployed, there is an aerodynamic condition of initial stall at a first spanwise location of the wing, without a corresponding pattern of stall developing at a second spanwise location of the wing, with said aerodynamic condition producing an undesired pitching moment; the improvement comprising a flow disturbing means positioned at said slot at said second spanwise location in a manner that with the leading edge member in said stowed position, the flow disturbing means is aerodynamically concealed by the leading edge member, and with the leading edge member in its deployed position, said flow disturbing means is exposed aerodynamically to antiflow in said slot to disturb the airflow that proceeds upwardly through said slot and over said wing, so as to create a disturbance which creates a desired stall condition at said second location.

Claim 3

The improvement as recited in claim 1, wherein said wing is a swept wing, and said first spanwise location is at an outboard location of the wing, and said flow disturbing means is mounted at an inboard location of said wing.

Claim 4

The improvement as recited in claim 2, wherein said flow disturbing means is mounted to the front surface portion of the main wing structure.

Claim 5

The improvement as recited in claim 2, wherein said flow disturbing means comprises a device that has a first retracted position where the device is positioned to have a lesser disturbing effect on airflow through the slot, and an outwardly deployed position where said device has a greater disturbing effect on airflow through the slot, said improvement further comprising means responsive to airflow through the slot to deploy said device in its flow disturbing position when there is greater airflow through the slot.

Claim 6

The improvement as recited in claim 4, wherein said device deploying means comprises spring means arranged to urge said device towards its retracted position, with said device having a surface exposed to air flow through said slot, with a reduction of static pressure in air flowing through the slot acting against said spring means to move the device from its passive position to its flow disturbing position.

Claim 7

The improvement as recited in claim 2, wherein said flow disturbing means comprises a fixed member that is fixedly mounted to the front surface portion of the main wing structure.

Claim 8

The improvement as recited in claim 2, wherein said flap forms a slot that converges in cross-sectional area in an upward direction of air flow so as to have a narrower high velocity area closer to an upper exit area of the slot, said flow disturbing means comprising a member positioned at said high velocity flow area so as to optimize disturbing effect of the device on the air flow through the slot.

Claim 9

The improvement as recited in claim 1, wherein said flow disturbing means is mounted to the front surface portion of the main wing structure.

Claim 10

The improvement as recited in claim 1, wherein said flow disturbing means comprises a device that has a first retracted position where the device is positioned to have a lesser disturbing effect on airflow through the slot, and an outwardly deployed position where said device has a greater disturbing effect on airflow through the slot, said improvement further comprising means responsive to airflow through the slot to deploy said device in its flow disturbing position when there is greater airflow through the slot.

Claim 11

The improvement as recited in claim 9, wherein said device deploying means comprises spring means arranged to urge said device towards its retracted position, with said device having a surface exposed to air flow through said slot, with a reduction of static pressure in air flowing through the slot acting against said spring means to move the device from its passive position to its flow disturbing position.

Claim 12

The improvement as recited in claim 1, wherein said flow disturbing means comprises a fixed member that is fixedly mounted to the front surface portion of the main wing structure.

Claim 13

The improvement as recited in claim 1, wherein said flap forms a slot that converges in cross-sectional area in an upward direction of air flow so as to have a narrower high velocity area closer to an upper exit area of the slot, said flow disturbing means comprising a member positioned at said high velocity flow area so as to optimize disturbing effect of the device on the air flow through the slot.

Claim 14

In a wing of an aircraft, where the wing comprises: (a) a main wing structure having an upper aerodynamic surface, a lower aerodynamic surface, and a forward surface portion that extends upwardly toward said upper aerodynamic surface; (b) a leading edge member which is moveable between a stowed position for cruise mode where the device aerodynamically conceals the surface of the main wing structure, and a deployed position for high-lift mode where the device forms with the forward surface portion of the main wing structure a slot for passage of air upwardly therethrough and over the wing upper surface; (c) said wing being characterized in that within a predetermined range of high angles of attack and with the leading edge member deployed, there is an aerodynamic condition of initial stall at or first spanwise location of the wing, without a corresponding pattern of stall developing at a second spanwise location of the wing, with said aerodynamic condition producing an undesired pitching moment; a method of alleviating said undesired pitching moment, said method comprising: a. providing a flow disturbing merans positioned at said slot and said second spanwise location; b. positioning the leading edge member in said stowed position so that the flow disturbing means is aerodynamically concealed by the leading edge member; c. positioning the leading edge member in its deployed position so that said flow distrubing means is exposed aerodynamically to airflow in said slot to disturb the airflow that proceeds upwardly through said slot and over said wing, so as to create a disturbance which creates a desired stall condition at said second location.

Claim 15

In a wing of an aircraft, where the wing comprises: (a) a main wing structure having an upper aerodynamic surface, a lower aerodynamic surface, and a forward surface portion that extends upwardly toward said upper aerodynamic surface; (b) a leading edge member which is moveable between a stowed position for cruise mode where the device aerodynamically conceals the surface of the main wing structure, and a deployed position for high-lift mode where the device forms with the forward surface portion of the main wing structure a slot for passage of air upwardly therethrough and over the wing upper surface; (c) said wing being characterized in that within a predetermined range of high angles of attack and with the leading edge member deployed, there is an aerodynamic condition of initial stall at or first spanwise location of the wing, without a corresponding pattern of stall developing at a second spanwise location of the wing, with said aerodynamic condition producing an undesired pitching moment; a method of alleviating said undesired pitching moment, said method comprising: a. providing a flow disturbing merans positioned at said slot and said second spanwise location; b. positioning the leading edge member in said stowed position so that the flow disturbing means is aerodynamically concealed by the leading edge member; c. positioning the leading edge member in its deployed position so that said flow distrubing means is exposed aerodynamically to airflow in said slot to disturb the airflow that proceeds upwardly through said slot and over said wing, so as to create a disturbance which creates a desired stall condition at said second location.

Claim 16

The method as recited in claim 13, wherein said wing is a swept wing, and said first spanwise location is at an outboard location of the wing, and said flow disturbing means is mounted at an inboard location of said wing.

Claim 17

The method as recited in claim 14, wherein said flow disturbing means is mounted to the front surface portion of the main wing structure.

Claim 18

The method as recited in claim 14, wherein said flow disturbing means comprises a fixed member that is fixedly mounted to the front surface portion of the main wing structure.

Claim 19

The method as recited in claim 14, wherein said flap forms a slot that converges in cross-sectional area in an upward direction of air flow so as to have a narrower high velocity area closer to an upper exit area of the slot, said flow disturbing means comprising a member positioned at said high velocity flow area so as to optimize disturbing effect of the device on the air flow through the slot.

Claim 20

The method as recited in claim 13, wherein said flow disturbing means is mounted to the front surface portion of the main wing structure.

Claim 21

The method as recited in claim 13, wherein said flow disturbing means comprises a fixed member that is fixedly mounted to the front surface portion of the main wing structure.

Claim 22

The method as recited in claim 13, wherein said flap forms a slot that converges in cross-sectional area in an upward direction of air flow so as to have a narrower high velocity area closer to an upper exit area of the slot, said flow disturbing means comprising a member positioned at said high velocity flow area so as to optimize disturbing effect of the device on the air flow through the slot.