Integrated multi-role variable sweep wing aircraft

Claim 2

An aircraft having a fuselage with a nose, jet engine means and wings mounted on and projecting from said fuselage for supplying lift to said aircraft, said wings being pivotally mounted on said fuselage for swinging movement between a forwardly disposed position, wherein the included angle between said wings and said fuselage is relatively large, and rearwardly disposed aft sweep positions wherein the includes angle between said wings and said fuselage is smaller, the resultant of the lifting forces exerted by said wings being to the rear of the center of gravity for said aircraft irrespective of the position of said wings and being located further rearwardly in the aft sweep position than in the forward position, whereby the lift forces on said wings create a nose-down moment about said center of gravity, said aircraft comprising canards pivotally mounted on said fuselage and rotatable about a control axis extending substantially perpendicularly to said fuselage, said canards projecting laterally with respect to said fuselage sorwardly of said wings and center of gravity and being spaced longitudinally from said wings, said canards being positioned and configured to produce a moment about said center of gravity which is in opposition to the nose-down moment created by said wings; thrust-vectoring means extending from said jet engine means for varying the thrust direction of said jet engine means and providing momeent control, said thrust-vectoring means having an exhaust area and flaps affixed to and extending rearwardly therefrom, said flaps being variable in position in a plane substantially perpendicular to that of said wings; wing sweep sensing means for detecting the position of said wings relative to said fuselage and providing corresponding information; thrust-vector sensing means for detecting the position of the flaps of said thrust-vectoring means and prodiving corresponding information; canard position sensing means for detecting the position of said canards relative to the plane of said wings and providing corresponding information; and control means mounted in said fuselage and extending to said wings, said canards and said thrust-vectoring means and to said wing sweep sensing means, said thrust-vector sensing means and said canard position sensing means for controlling said wings in angular positions relative to said fuselage, controlling said canards in rotary position relative to said fuselage and controlling said thrust-vectoring means to control said thrust direction in accordance with information received from said sensing means, said control means rotating the leading edges of said canards up to provide a nose-up pitching moment to balance out negative pitching moments due to thrust-vectored lift enhancement on landing approach and controlling said positions in coordination to provide maximized subsonic takeoff and landing, transonic maneuver and supersonic cruise performance of said aircraft while keeping said aircraft safe from pitch departure, deep stall and spin.

Claim 3

An aircraft as claimed in claim 1, wherein said thrust-vectoring means comprises exhaust nozzle means extending aft of said jet engine means and said flaps consits of nozzle flaps affixed to and extending rearwardly from said nozzle means and variable in position in a plane substantially perpendicular to that of said wings, said nozzle flaps being rotatable nozzle axes extending substantially parallel to said control axis.

Claim 4

An aircraft as claimed in claim 2 wherein said control means rotates said nozzle flaps to an angle sufficient to provide a moment about said center of gravity to pitch the nose of said aircraft down when said wings are swept forward to obtain additional lift and slower landing speed and thereby create forces tending to pitch said nose up.

Claim 5

An aircraft having a fuselage with a nose, jet engine means and wings mounted on and projecting from said fuselage for supplying lift said aircraft, and wings being pivotally mounted on said fuselage for swinging movement between a forwardly disposed position, wherein the included angle between said wings and fuselage is relatively large, and rearwardly disposed aft sweep positions wherein the included angle between said wings and said fuselage is smaller, the resultant of the lifting forces exerted by said wings being to the rear of the center of gravity for said aircraft irrespective of the position of said wings and being located further rearwardly in the aft sweep position than in the forward position, whereby the lift forces on said wings create a nose-down moment about said center of gravity, said aircraft comprising horizontal stabilizers mounted on said fuselage behine said wings and being spaced longitudinally from said wings, said horizontal stabilizers being positioned and configured to produce a movement about said center of gravity which oppose the nose-down moment exerted by said wings, said horizontal stabilizers having flaps rotatable about a stabilizer axis extending substantially perpendicularly to said fuselage; thrust-vectoring means extending from said jet engine means for varying the thrust direction of said jet engine means, said thrust-vectoring means comprising exhaust nozzle means extending aft of said jet engine means, said nozzle means having nozzle flaps affixed to and extending rearwardly therefrom and variable in position in a plane substantially perpendicular to that of said wings; wing sweep sensing means for detecting the position of said wings relative to said fuselage and providing corresponding information; thrust-vector sensing means for detecting the positions of said nozzle flaps and providing corresponding information; horizontal stabilizer position sensing means for detecting the position of said flaps of said horizontal stabilizer relative to the plane of said wings and providing corresponding information; and control means mounted in said fuselage and extending to said wings, said horizontal stabilizers and said thrust-vectoring means and to said wing sweep sensing means, said thrust-vector sensing means and said horizontal stabilizer position sensing means for controlling said wings in angular position relative to said fuselage, controlling said flaps of said horizontal stabilizers in rotary position relative to said fuselage and controlling said thrust-vectoring means to control said thrust direction in accordance with information received from said sensing means, said control means rotating said nozzle flaps to an angle sufficient to provide a moment about said center of gravity to pitch the nose of said aircraft down when said wings are swept forward to obtain additional lift and slower landing speed and thereby create forces tending to pitch said nose-up and controlling said positions in coordination to overcome pitch departure, deep stall and spin, due to lack of nose-down pitch power thereby providing maximum supersonic cruise and transonic maneuver performance of said aircraft.

Claim 6

An aircraft having a fuselage with a nose, jet engine means and wings mounted on and projecting from said fuselage for supplying lift said aircraft, and wings being pivotally mounted on said fuselage for swinging movement between a forwardly disposed position, wherein the included angle between said wings and fuselage is relatively large, and rearwardly disposed aft sweep positions wherein the included angle between said wings and said fuselage is smaller, the resultant of the lifting forces exerted by said wings being to the rear of the center of gravity for said aircraft irrespective of the position of said wings and being located further rearwardly in the aft sweep position than in the forward position, whereby the lift forces on said wings create a nose-down moment about said center of gravity, said aircraft comprising horizontal stabilizers mounted on said fuselage behine said wings and being spaced longitudinally from said wings, said horizontal stabilizers being positioned and configured to produce a movement about said center of gravity which oppose the nose-down moment exerted by said wings, said horizontal stabilizers having flaps rotatable about a stabilizer axis extending substantially perpendicularly to said fuselage; thrust-vectoring means extending from said jet engine means for varying the thrust direction of said jet engine means, said thrust-vectoring means comprising exhaust nozzle means extending aft of said jet engine means, said nozzle means having nozzle flaps affixed to and extending rearwardly therefrom and variable in position in a plane substantially perpendicular to that of said wings; wing sweep sensing means for detecting the position of said wings relative to said fuselage and providing corresponding information; thrust-vector sensing means for detecting the positions of said nozzle flaps and providing corresponding information; horizontal stabilizer position sensing means for detecting the position of said flaps of said horizontal stabilizer relative to the plane of said wings and providing corresponding information; and control means mounted in said fuselage and extending to said wings, said horizontal stabilizers and said thrust-vectoring means and to said wing sweep sensing means, said thrust-vector sensing means and said horizontal stabilizer position sensing means for controlling said wings in angular position relative to said fuselage, controlling said flaps of said horizontal stabilizers in rotary position relative to said fuselage and controlling said thrust-vectoring means to control said thrust direction in accordance with information received from said sensing means, said control means rotating said nozzle flaps to an angle sufficient to provide a moment about said center of gravity to pitch the nose of said aircraft down when said wings are swept forward to obtain additional lift and slower landing speed and thereby create forces tending to pitch said nose-up and controlling said positions in coordination to overcome pitch departure, deep stall and spin, due to lack of nose-down pitch power thereby providing maximum supersonic cruise and transonic maneuver performance of said aircraft.

Claim 7

An aircraft as claimed in claim 4, wherein said nozzle flaps are rotatable about nozzle axes extending substantially parallel to said stabilizer axis.

Claim 8

An aircraft as claimed in claim 4, wherein said control means rotates said horizontal stabilizer flaps trailing edge up to provide a nose-up pitching moment to balance out negative pitching moments due to thrust-vectored lift enhancement on landing approach.