IN-FLIGHT AIRCRAFT RECOVERY SYSTEM

• US 3,796,398 A
• Filed: 05/14/1973
• Issued: 03/12/1974
• Est. Priority Date: 05/14/1973
• Status: Expired due to Term

• Current Assignee: Warren H. Eilertson
• Original Assignee: Warren H. Eilertson
• Inventors: Eilertson, Warren H.
• Primary Examiner(s): Blix, Trygve M.
• Assistant Examiner(s): Auton, Gary L.
• Application Number:
  US05/359,744
• Time in Patent Office: 302 Days
• Field of Search: 244/139,146,138R,17.1S,33
• US Class Current: 244/139
• CPC Class Codes: B64D 17/80 in association with aircraft, e.g. for braking thereof

Abstract

An in-flight aircraft recovery system utilizing an inflatable wing of generally rectangular planform configuration stowed in a normally collapsed condition in a compartment located on the upper portion of the fuselage in the vicinity of the plane'"'"''"'"'s center of gravity. Upon deployment, the compartment'"'"''"'"'s cover is ejected and a first parawing type pilot chute lifts a container including the inflatable wing from the compartment and above the tail section of the aircraft. The first pilot chute is jettisoned along with the container after the suspension lines are fully extracted and a second pilot chute of a similar parawing configuration attached to the wing is deployed which positions the inflatable wing above the aircraft with the wing then being inflated by means of a turbine driven compressor mounted on the airfoil surface. The inflatable wing when inflated comprises a rectangular wing including control surfaces in the form of controlled flaps at the wing trailing edge. The wing is connected to the airplane by means of a plurality of suspension lines which are attached to respective rotatable reels. The reels are further controlled for providing selective unreeling and braking of the lines during wing deployment and for subsequently altering not only the angle of attack of the inflated wing, but also the flaps so that the inflated wing flys the aircraft to a predetermined destination either by means of remote pilot control or beacon ground control.

Claims

1. An in-flight recovery system, for disabled aircraft and/or personnel, comprising in combination:

speed reduction means selectively operable to stabilize and slow the air speed in the event of an emergency condition;

an inflatable structure having an airfoil cross-section including flight control surfaces and a container therefor stored in a normally deflated condition in said aircraft;

a first pilot parachute attached to said container;

means responsive to flight speed, becoming operable after a predetermined speed reduction of said aircraft to eject said container and said first pilot parachute from said aircraft, said pilot parachute then acting to lift said container above the aircraft away from any obstruction thereon and pulling container off said deflated airfoil;

inflation means integral with said airfoil structure and including means for being rendered operative after said container is removed;

a second pilot parachute attached to said airfoil structure and becoming deployed after said container is removed for orienting said airfoil structure to provide lift substantially immediately during inflation and further aiding proper inflation of the structure so that the centermost section inflates prior to the outermost sections whereby an immediate altitude increase results for providing additional clearance for emergencies occurring near the ground;

a plurality of suspension lines attached to the underside of said airfoil structure and said control surfaces;

a plurality of rotatable reels mounted on said aircraft, being attached to said suspension lines and having controlled braking means, said braking means being adapted to control the unreeling of the suspension lines during deployment to prevent unusually high snatch forces from being exerted on said suspension lines;

respective driver means coupled to said plurality of rotatable reels, being operable thereby to control the angle of attack of said airfoil and selective operation of said control surfaces; and

flight control means coupled to said individual reel driver means to selectively control the angle of attack of said airfoil structure and operate said control surfaces for steering said airfoil structure to a predetermined destination and performing a flareout and landing maneuver thereby.

2. The system as defined by claim 1 wherein said inflatable airfoil structure comprises a wing having a rectangular planform and said control surfaces comprises deflectable flap means arranged along the trailing edge of said wing.

3. The system as defined by claim 2 wherein said plurality of suspension lines include three sets of lines respectively attached to the forward, middle and rear portions of said wing.

4. The system as defined by claim 3 and wherein said flap means comprises three flap members arranged substantially across the entire trailing edge of said wing and wherein said plurality of suspension lines includes at leAst one individual suspension line attached to each flap member.

5. The system as defined by claim 4 wherein said first and second pilot parachute comprise lifting type parachutes.

6. The system as defined by claim 5 wherein said lifting type parachutes are comprised of parawing parachutes.

7. The system as defined in claim 6 wherein said aircraft speed reduction means comprises a drag parachute located in the rear section of said aircraft and being deployable upon command.

8. The system as defined in claim 7 wherein said inflation means comprises a gas turbine and a rotary air compressor coupled to and driven by said turbine and having a compressed air output conduit coupled to the interior of said wing, said turbine being energized upon command to inflate said wing.

9. The system as defined by claim 8 and additionally including electrical generator means coupled to said turbine for powering said flight control means.

10. The system as defined by claim 8, and wherein said wing additionally includes pressure relief valve means for maintaining the internal pressure of said wing at a predetermined value upon inflation, and wherein said turbine is operable for a predetermined time after inflation to insure continued pressurization of said wing for a time sufficient to land said disabled aircraft at its predetermined location.

11. The system as defined by claim 4 wherein said plurality of rotatable reels are mounted within a housing located on the upper portion of said aircraft in the vicinity of its center of gravity.

12. The system as defined by claim 11 wherein a plurality of said rotatable reels are mounted on respective concentric shafts having a common central axis and wherein said braking means includes pressure plates at either end of said plurality of rotatable reels and wherein said pressure plates and said rotatable reels include braking surfaces which frictionally engage one another upon a compression force being applied to at least one of said plates.

13. The system as defined by claim 11 wherein selected reels of said plurality are located on a common axis of rotation and at least one reel of said plurality is located on another axis rotation substantially parallel to said common axis.

14. The system as defined by claim 1 and additionally including catenary means formed on the underside of the airfoil structure and wherein selected suspension lines of said plurality of suspension lines are connected to said catenary means.