Jet flow deflector for aircraft

Claim 2

In an aircraft having jet propulsion means, a nacelle mounted in a wing of the aircraft and containing said propulsion means, said nacelle providing a nozzle at its end portion for discharging a jet flow in the aft direction of the aircraft, and deflector means on the nacelle movable between first and second positions, the deflector means engaging the nacelle at the aft end thereof in its first position to form a continuous interior surface with the nacelle constituting a part of said nozzle, and the deflector means being movable downwards and aft relative to the nacelle to its second position in which the deflector means deflects the jet flow downward and is spaced from the nacelle to provide additional jet flow in the aft direction over the deflector means between the nacelle and the upper surface of the deflector means to increase the effective nozzle area.

Claim 3

The combination of claim 1 in which the upper surface of the deflector means is shaped to function as a Coanda surface.

Claim 4

The combination of claim 1 in which the deflector means in its second position extends beyond the end of the nacelle to provide a further area for jet flow at one side of the deflector means.

Claim 5

The combination of claim 1 in which the deflector means is a curved member adapted to engage a recess in the upper part of the nacelle in said first position to form with the nacelle an effective nozzle for jet flow, and said member being spaced from the nacelle in said second position to form an open flow area for jet flow between the nacelle and the upper surface of the member, said surface being shaped as a Coanda surface to cause said last-mentioned jet flow to flow downward to merge with the main flow from the nacelle.

Claim 6

The combination of claim 1 in which the deflector means comprises a plurality of curved segments disposed side-by-side and adapted to engage the nacelle and each other in said first position to form with the nacelle an effective nozzle for jet flow, and said segments being displaced downwards and aft relative to the nacelle and to each other in said second position to deflect downward the main jet flow through said nozzle and to provide open flow areas for jet flow over the upper surfaces of the segments.

Claim 7

The combination of claim 5 in which said segments engage a recess in the upper part of the nacelle and each other in said first position in a manner to form with the nacelle an effective nozzle for jet flow, and in which said upper surfaces of the segments are shaped as Coanda surfaces to cause the flow over said surfaces in said second position to flow downward to merge with the main jet flow.

Claim 8

In an aircraft having jet propulsion means, a nacelle mounted in a wing of the aircraft and containing said propulsion means, said nacelle having its end portion formed to provide a nozzle for discharging a jet flow in the aft direction of the aircraft, said end portion of the nacelle having a recess in the upper part thereof adjoining a circumferential opening in the aft edge of the nacelle, a curved deflector on the nacelle, said deflector having a first position in which it engages in said recess and closes said opening, the configuration of the deflector being such that in said first position it forms with the nacelle a continuous interior surface providing a single effective flow passage for the entire jet flow and the upper surface of the deflector forming with the nacelle a smooth continuous exterior surface, and the deflector having a second position in which it is displaced downwards of the nacelle and aft from the first position to deflect the jet flow downward and to provide an open flow area between the upper surface of the deflector and the nacelle to provide additional jet flow in the aft direction over the upper surface of the deflector to increase the effective nozzle area.

Claim 9

In an aircraft having jet propulsion means, a nacelle mounted in a wing of the aircraft and containing said propulsion means, said nacelle having its end portion formed to provide a nozzle for discharging a jet flow in the aft direction of the aircraft, said end portion of the nacelle having a recess in the upper part thereof adjoining a circumferential opening in the aft edge of the nacelle, a curved deflector on the nacelle, said deflector having a first position in which it engages in said recess and closes said opening, the configuration of the deflector being such that in said first position it forms with the nacelle a continuous interior surface providing a single effective flow passage for the entire jet flow and the upper surface of the deflector forming with the nacelle a smooth continuous exterior surface, and the deflector having a second position in which it is displaced downwards of the nacelle and aft from the first position to deflect the jet flow downward and to provide an open flow area between the upper surface of the deflector and the nacelle to provide additional jet flow in the aft direction over the upper surface of the deflector to increase the effective nozzle area.

Claim 10

The combination of claim 7 in which said upper surface of the deflector is shaped to function as a Coanda surface to cause jet flow through said open flow area to follow said surface and merge with flow through the nozzle.

Claim 11

The combination of claim 7 in which said deflector in the second position provides a further flow area at one side thereof and beyond the end of the nacelle.

Claim 12

The combination of claim 9 in which the nacelle has an extension at the other side thereof in position to be engaged by the deflector member in its second position.

Claim 13

The combination of claim 7 in which the deflector comprises a plurality of curved segments engaging each other and the nacelle in said first position to close said opening, said segments being spaced from the nacelle and each other in said second position to provide areas for jet flow over the upper surfaces of the segments.

Claim 14

The combination of claim 11 in which the upper surfaces of the segments are shaped to function as Coanda surfaces to cause the flows over said surfaces to flow downward and merge with the main jet flow through the nozzle.