Multi-purpose aircraft

• US 5,645,250 A
• Filed: 08/26/1993
• Issued: 07/08/1997
• Est. Priority Date: 08/26/1993
• Status: Expired due to Fees

• Current Assignee: David E. Gevers
• Original Assignee: David E. Gevers
• Inventors: Gevers, David E.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): MARQUIS, LISSI MOJICA
• Application Number:
  US08/112,877
• Time in Patent Office: 1,412 Days
• Field of Search: 244/45 R, 244/46, 244/218, 244/50, 244/51, 244/55, 244/56, 244/58, 244/60, 244/69, 244/101, 244/102 R, 244/105, 244/106, 244/107
• US Class Current: 244/101
• CPC Class Codes: B64C 1/00 Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
• CPC Class Codes: B64C 2001/0045 Fuselages characterised by special shapes
• CPC Class Codes: B64C 25/52 Skis or runners
• CPC Class Codes: B64C 25/54 Floats
• CPC Class Codes: B64C 25/66 Convertible alighting gear; Combinations of different kinds of ground or like engaging elements
• CPC Class Codes: B64C 3/38 Adjustment of complete wings or parts thereof
• CPC Class Codes: B64C 3/54 Varying in area
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64C 35/00 Flying-boats; Seaplanes
• CPC Class Codes: B64C 35/002 using adjustable auxiliary floats
• CPC Class Codes: B64C 35/008 Amphibious sea planes
• CPC Class Codes: B64D 27/00 Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
• CPC Class Codes: B64D 27/08 within, or attached to, fuselages
• CPC Class Codes: B64D 29/04 associated with fuselages
• CPC Class Codes: B64D 35/04 characterised by the transmission driving a plurality of propellers or rotors
• CPC Class Codes: Y02T 50/10 Drag reduction
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Claims

1. A multi-purpose aircraft comprising

(a) a fuselage having a generally cylindrical structure defining a forward end to an aft end, the fuselage being closed at the forward end by a nose section and closed at the aft end by a tail section, said fuselage further having a hull-shaped underside having forward and aft landing gear openings, said fuselage further having a port lateral recess and a starboard lateral recess;

(b) a compound aircraft wing attached to said fuselage comprising

(1) a fixed wing section comprising a bilaterally symmetrical aircraft wing providing lift in response to the flow of air thereacross defining leading and trailing edges and defining port and starboard halves, said fixed wing section being at least partially hollow and being open at the port and starboard ends, said fixed wing section further having a recess along the top surface of both the port and starboard halves;

(2) a port wing extension panel comprising a forward port lift spar, a center port drag spar, and an aft port lift spar, which port spars are disposed in parallel relation and each spar being substantially the same length as said fixed wing section, substantially one-half the length of said spars being enclosed by and giving structural support to an outer skin so as to form a port aircraft wing extension section ending in a wing tip, said port wing extension section providing lift in response to the flow of air thereacross, said port wing extension panel being extendably mounted inside said fixed wing section such that said port wing extension panel is extendable from the port opening of the fixed wing section such that substantially all of the port aircraft wing extension section protrudes from the port end of the fixed wing section and the portion of the port spars not enclosed by an outer skin being still inside said fixed wing section, said port wing extension panel further being mounted inside said fixed wing section such that said port wing extension panel is retractable within said fixed wing section such that substantially all of the port wing extension panel is enclosed by said fixed wing section;

(3) a starboard wing extension panel comprising a forward starboard lift spar, a center starboard drag spar, and an aft starboard lift spar, which starboard spars are disposed in parallel relation and each spar being substantially the same length as said fixed wing section, substantially one-half the length of said spars being enclosed by and giving structural support to an outer skin so as to form a starboard aircraft wing extension section ending in a wing tip, said starboard wing extension section providing lift in response to the flow of air thereacross, said starboard wing extension panel being extendably mounted inside said fixed wing section such that said starboard wing extension panel is extendable from the starboard opening of the fixed wing section such that substantially all of the starboard aircraft wing extension section protrudes from the starboard end of the fixed wing section and the portion of the starboard spars not enclosed by an outer skin being still inside said fixed wing section, said starboard wing extension panel further being mounted inside said fixed wing section such that said starboard wing extension panel is retractable within said fixed wing section such that substantially all of the starboard wing extension panel is enclosed by said fixed wing section, said port wing extension panel and said starboard wing extension panel being mounted in such relation that said port spars and said starboard spars are in interlocking juxtaposition inside the fixed wing section so as to permit the complete retraction of both the port and starboard wing extension panels within said fixed wing section at the same time; and

(4) means for effecting the extension and retraction of said port and starboard wing extension panels;

(c) one or more engines, mounted on the inside of the fuselage, each of said one or more engines, when operating, causing rotation of an engine shaft;

(d) a port mounting armature comprising a unitary body pivotally mounted on the trailing edge of the port half of the fixed wing section, the pivotal mount defining an upper portion and a lower portion of said port mounting armature, the armature being positioned on the fixed wing section and shaped so that when pivoted to port, the lower portion of said port mounting armature nests in said port fuselage recess and the upper portion of said port mounting armature nests in the recess in the port half of the fixed wing section, the upper portion of said port mounting armature including at least one port propeller nacelle in which a port shaft and propeller assembly is rotatably mounted, which port shaft and propeller assembly extends aft of said at least one port propeller nacelle such that the propeller portion of the port shaft and propeller assembly is positioned aft of the trailing edge of the fixed wing section, said propeller portion being a pusher propeller, the lower portion of said port mounting armature further comprising integrated pontoon and wheel landing gear, said port mounting armature being further shaped such that when pivoted to starboard, the wheel and the pontoon are oriented, at separate points of rotation of the port mounting armature, to a position appropriate for contact with the landing surface upon landing, and the upper portion of the port mounting armature is raised above said fixed wing section;

(e) a starboard mounting armature comprising a unitary body pivotally mounted un the trailing edge of the starboard half of the fixed wing section, the pivotal mount defining an upper portion and a lower portion of said starboard mounting armature, the armature being positioned on the fixed wing section and shaped so that when pivoted to starboard, the lower portion of said starboard mounting armature nests in said starboard fuselage recess and the upper portion of said starboard mounting armature nests in the recess in the starboard half of the fixed wing section, the upper portion of said starboard mounting armature including at least one starboard propeller nacelle in which a starboard shaft and propeller assembly is rotatably mounted, which starboard shaft and propeller assembly extends aft of said at least one starboard propeller nacelle such that the propeller portion of the starboard shaft and propeller assembly is positioned aft of the trailing edge of the fixed wing section, said propeller portion being a pusher propeller, the lower portion of said starboard mounting armature further comprising integrated pontoon and wheel landing gear, said starboard mounting armature being further shaped such that when pivoted to port, the wheel and the pontoon are oriented, at separate points of rotation of the starboard mounting armature, to a position appropriate for contact with the landing surface upon landing and the upper portion of the starboard mounting armature is raised above said fixed wing section;

(f) belt drive means connecting each engine shaft to at least one propeller shaft in such a manner that rotation of the engine shaft causes rotation of each propeller shaft and propeller to which said belt drive means is attached;

(g) compound landing gear comprising

(1) a forward landing gear component positioned forward of the center of gravity of the aircraft, substantially completely retractable into the fuselage through said forward opening in the fuselage, including integrated steerable ski and steerable wheel subcomponents; and

(2) a main central landing gear component, substantially completely retractable into the fuselage through said aft opening in the fuselage, including integrated skis and steerable wheel subcomponents, which, when retracted, assist in formation of a step in the fuselage.

2. The aircraft according to claim 1, wherein each subcomponent of said integrated pontoon and wheel landing gear, and said main central landing gear component, when fully deployed, is oriented at a point 10°

-11°

aft of the center of gravity of the level aircraft.

3. The aircraft according to claim 1, wherein said port and starboard wing extension panels, when fully extended from the fixed wing section, increase the total wingspan of the aircraft up to 90-95%.

4. The aircraft according to claim 1, wherein said fixed wing section is attached to the top of said fuselage, and wherein there are twin engines tandemly mounted and opposed on the inside of said fuselage, and wherein each engine drives one shaft and propeller assembly.

5. The aircraft according to claim 4, wherein said twin engines are connected to a common gearbox which permits either engine to drive both shaft and propeller assemblies in the event of the shutdown of the other engine.

6. The aircraft according to claim 1, wherein said engines are air-cooled aircraft engines or water-cooled automobile engines.

7. The aircraft according to claim 1, wherein the fixed wing section is NACA 63₃ -018 at root and tip, has a wing chord of 10 feet, 8 inches at the root and 6 feet, 8 inches at the tip, dihedral of 3 degrees, sweep of -3.28 degrees at the 1/4 chord, and a span of 26 feet;

said port and starboard wing extension panels have no sweep;

the wing span of the compound wing with port and starboard wing extension panels fully extended is 50 feet;

said tail section forming a cantilever T-type tail with a span of 14 feet, 7 inches and having a horizontal stabilizer and elevator;

wherein the overall aircraft length is 40 feet and overall height is 12 feet, 4 inches.

8. An aircraft comprising

(a) a fuselage having a generally cylindrical structure extending from a forward end to an aft end, being dosed at the forward end by a nose section and closed at the aft end by a tail section,

(b) a fixed wing section attached to said fuselage so as to provide port and starboard wings extending laterally on either side of the fuselage,

(c) port and starboard mounting armatures pivotally mounted, respectively, on the trailing edges of the port and starboard wings, the pivotal mounts permitting each of the armatures to be rotated above the plane of the wing section and perpendicular to the longitudinal axis of the fuselage, each armature including a propeller nacelle at its distal end, each nacelle enclosing a propeller shaft rotatably mounted therein, which propeller shaft protrudes from the aft end of the nacelle and past the trailing edge of the wing on which the armature is located, each propeller shaft having a pusher propeller fixedly attached on the shaft at a point aft of the trailing edge of the wing, each armature being positioned on its respective wing so that when pivoted the nacelle and propeller at the distal end of the armature are moved to a different position relative to the wing section,

(d) one or more engines, mounted on the inside of the fuselage, each of said one or more engines, when operating, causing rotation of an engine shaft, and

(e) belt drive means connecting each engine shaft to at least one propeller shaft in such a manner that rotation of the engine shaft causes rotation of each propeller shaft and the propeller attached thereto.

9. The aircraft according to claim 8, wherein said fixed wing section is attached to the top of said fuselage, and wherein there are twin engines tandemly mounted and opposed on the inside of said fuselage, and wherein each engine drives one propeller shaft such that the propellers are counterrotating in operation.

10. The aircraft according to claim 9, wherein said twin engines are connected to a common gearbox which permits either engine to drive both shaft and propeller assemblies in the event of the shutdown of the other engine.

11. The aircraft according to claim 8, wherein said engines are air-cooled aircraft engines or water-cooled automobile engines.

12. An aircraft comprising

(a) a fuselage having a generally cylindrical structure extending from a forward end to an aft end, being closed at the forward end by a nose section and closed at the aft end by a tail section,

(b) a fixed wing section attached to said fuselage so as to provide port and starboard wings extending laterally on either side of the fuselage,

(c) a port mounting armature pivotally attached to the trailing edge of the port wing, the pivotal mount defining an upper portion and a lower portion of said port mounting armature, said upper portion including at least one propeller nacelle providing a mount for accepting a propeller shaft, and said lower portion incorporating a pontoon member and a wheel, and

(d) a starboard mounting armature pivotally attached to the trailing edge of the starboard wing, the pivotal mount defining an upper portion and a lower portion of said starboard mounting armature, said upper portion including at least one propeller nacelle providing a mount for accepting a propeller shaft, and said lower portion incorporating a pontoon member and a wheel,

wherein pivotal rotation of either said port or starboard mounting armatures simultaneously repositions both the propeller nacelle situated on the upper portion and the pontoon member and wheel situated on the lower portion of said armature.

13. The aircraft according to claim 12, wherein each propeller nacelle encloses a propeller shaft rotatably mounted therein, which propeller shaft protrudes from the aft end of the nacelle and past the aft edge of the wing on which the nacelle is located, each propeller shaft having a pusher propeller fixedly attached on the shaft at a point aft of the aft edge of the wing, said aircraft further comprising (e) two engines, tandemly mounted and opposed on the inside of the fuselage, each of said engines, when operating, causing rotation of an engine shaft, and (f) belt drive means connecting each engine shaft to one or the other of the propeller shafts in such a manner that operation of the engines causes rotation of the two propellers.

14. The aircraft according to claim 13, wherein said engines are connected to a common gearbox which permits either engine to drive both propellers in the event of the shutdown of the other engine.

15. An aircraft comprising a fuselage and further comprising

a forward landing gear component positioned forward of the center of gravity of the aircraft, substantially-completely retractable into the fuselage, including integrated steerable ski and steerable wheel subcomponents;

(b) a main central landing gear component, substantially completely retractable into the fuselage, including integrated skis and steerable wheel subcomponents, each of which may be deployed to a point 8°

-13°

aft of the center of gravity of the level aircraft and which, when retracted, assist in formation of a step in the fuselage at a point 8°

-13°

aft of the center of gravity of the level aircraft; and

(c) a lateral stabilizing gear component comprising two bilaterally situated stabilizing members, each of which may be deployed on either side of the aircraft to a point 8°

-13°

aft of the center of gravity of the level aircraft and substantially aligned with the main central landing gear, and each member including integrated pontoon and wheel subcomponents.

16. The aircraft according to claim 15, wherein each subcomponent of, said main central landing gear component, and said lateral stabilizing gear component, when fully deployed, is oriented at a point 10°

-11°

aft of the center of gravity of the level aircraft.