Tilt-rotor wing fold mechanism and method

• US 4,691,878 A
• Filed: 11/06/1985
• Issued: 09/08/1987
• Est. Priority Date: 11/06/1985
• Status: Expired due to Fees

• Current Assignee: the united states of america as represented by the secretary of the navy
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Vaughan, John C., Perkins, Russel G. Jr.
• Primary Examiner(s): Barefoot, Galen
• Application Number:
  US06/795,303
• Time in Patent Office: 671 Days
• Field of Search: 244/6, 244/7 R, 244/7 A, 244/7 C, 244/49, 244/46, 244/201, 244/2, 416/142, 416/143
• US Class Current: 244/7.00R
• CPC Class Codes: B64C 27/28 with forward-propulsion propellers pivotable to act as lifting rotors
• CPC Class Codes: B64C 27/50 Blades foldable to facilitate stowage of aircraft
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft

Abstract

A mechanism and method for folding the wing of a tilt-rotor aircraft, hav a rotatable load bearing member cooperatively disposed between a high point of the fuselage and the tilt-rotor wing, and a plurality of locking, load bearing pin joints disposed between the fuselage and the tilt-rotor wing, concentric to the rotatable load bearing member, and wherein the tilt-rotor wing may be stored by rotating the tilt-rotor wing, as a single segment, about the rotatable load bearing member, to a position substantially parallel to the fuselage, and wherein the wing may be locked in the flight configuration and the storage configuration with the same pin joints.

Claims

1. A wing fold mechanism for a tilt-rotor aircraft, said aircraft including a fuselage, a single-segment tilt-rotor wing having a tilting rotor-prop assembly on each wing tip and engine cross-shafting therebetween, and a tail empennage, comprising:

a rotatable load bearing member, disposed between the tilt-rotor wing and a high point of the fuselage, wherein the tilt-rotor wing is rotatably affixed to the high point of the fuselage;

at least one load bearing pin joint, each having an upper pin joint member rigidly affixed to the tilt-rotor wing, a lower pin joint member rigidly affixed to the fuselage, and a locking means, detachably connecting said upper and lower pin joint members, wherein each load bearing pin joint transfers the ground and flight loads between the tilt-rotor wing and the fuselage; and

,

wherein the tilt-rotor wing is reversably rotatable from a flight configuration, perpendicular to the fuselage, to a storage configuration, substantially parallel to the fuselage, and may be locked in each of said configurations.

2. The apparatus recited in claim 1, wherein said rotatable load bearing member comprises:

an upper ring member, rigidly affixed to the wing spars, and depending from the tilt-rotor wing;

a lower ring member, rigidly affixed to the fuselage ribs, and appending from said high point of the fuselage; and

,

a plurality of bearing members disposed between said upper ring member and said lower ring member, wherein said ring members are rotatably connected.

3. The apparatus recited in claim 1, wherein said rotatable load bearing member comprises:

an inner cylindrical shaft, rigidly affixed to the tilt-rotor wing, and depending therefrom;

an outer cylindrical shaft, concentrically disposed about and supporting said inner shaft, rigidly affixed to the fuselage ribbing, and appending from said high point of the fuselage; and

,

a plurality of bearing members disposed between said inner and outer shaft members, wherein said shaft members are rotatably mounted.

4. The apparatus recited in claim 1, wherein the number of load bearing pin joints is four.

5. The apparatus recited in claim 4, wherein the load bearing pin joints are disposed radially and concentric to said rotatable load bearing member, each upper pin joint member, a female joint member, being rigidly affixed to a wing spar and provided with a locking pin hole, each lower pin joint member, a male joint member, being rigidly affixed to a fuselage rib and provided with a corresponding locking pin hole, and each locking means being a locking pin, wherein each male joint member may rotate through, and be locked with, each female joint member, and wherein the same pin joint members can lock the wing in a flight configuration and a storage configuration.

6. The apparatus recited in claim 4, wherein the load bearing pin joints are disposed radially and concentric to said rotatable load bearing member, each upper pin joint member, a male joint member, being ridigly affixed to a wing spar and provided with a locking pin hole, each lower pin joint member, also a male joint member, being rigidly affixed to a fuselage rib and provided with a locking pin hole, and each locking means comprising a sleeve, slidably encompassing said upper and lower pin joint members and provided with corresponding upper and lower pin holes, and upper and lower locking pins, wherein when unlocked, each upper pin joint member may rotate past, and allign with, each lower pin joint member, and wherein the same pin joint members can lock the wing in a flight configuration and a storage configuration.

7. The apparatus recited in claim 1, the tail empennage further comprising:

a folding control surface, wherein during storage the control surface is folded to provide additional clearance for the tilt-rotor-prop assembly.

8. A method for folding the wing of a tilt-rotor-aircraft, said aircraft including a fuselage, a single segment tilt-rotor wing having a tilting rotor-prop assembly on each wing tip and engine cross-shafting therebetween, a tail empennage having a foldable control surface, a rotatable load bearing member disposed between the wing and the fuselage, and at least one lockable load bearing pin joint radially disposed concentric to the rotatable load bearing member, said method comprising the steps of:

folding the rotors of each tilt-rotor-prop assembly inboard;

unlocking each load bearing pin joint;

rotating the single segment tilt-rotor wing relative to the fuselage on the rotatable load bearing member to a configuration substantially parallel to said fuselage; and

locking each load bearing pin joint.

9. The wing fold method recited in claim 8, further comprising the step of:

folding said foldable tail empennage control surface to provide additional clearance for the tilting rotor-prop assembly during storage.

10. A wing fold mechanism for a tilt-rotor aircraft, said aircraft including a fuselage, a one piece single-segment tilt-rotor wing having a tilting rotor-prop assembly on each wing tip and engine cross-shafting therebetween, and a tail empennage, comprising:

a rotatable load bearing member, disposed between the tilt-rotor wing and a high point of the fuselage, wherein the tilt-rotor wing is rotatably affixed to the high point of the fuselage;

at least one load bearing pin joint, each having an upper pin joint member rigidly affixed to the tilt-rotor wing, a lower pin joint member rigidly affixed to the fuselage, and a locking means, detachably connecting said upper and lower pin joint members, wherein each load bearing pin joint transfers the ground and flight loads between the tilt-rotor wing and the fuselage; and

,

wherein the tilt-rotor wing is reversibly rotatable from a flight configuration, perpendicular to the fuselage to a storage configuration, substantially parallel to the fuselage, and may be locked in each of said configurations.

11. The apparatus recited in claim 10, wherein said rotatable load bearing member comprises:

an upper ring member, rigidly affixed to the wing spars, and depending from the tilt-rotor wing;

a lower ring member, rigidly affixed to the fuselage ribs, and appending from said high point of the fuselage; and

,

a plurality of bearing members disposed between said upper ring member and said lower ring member, wherein said ring members are rotatably connected.

12. The apparatus recited in claim 10, wherein said rotatable load bearing member comprises:

an inner cylindrical shaft, rigidly affixed to be tilt-rotor wing, and depending therefrom;

an outer cylindrical shaft, concentrically disposed about and supporting said upper shaft, rigidly affixed to the fuselage ribbing, and appending from said high point of the fuselage; and

,

a plurality of bearing members disposed between said inner and outer shaft members, wherein said shaft members are rotatably mounted.

13. The apparatus recited in claim 10, wherein the number of load bearing pin joints is four.

14. The apparatus recited in claim 13, wherein the load bearing pin joints are disposed radially and concentric to said rotatable load bearing member, each upper pin joint member, a female joint member, being rigidly affixed to a wing spar and provided with a locking pin hole, each lower pin joint member, a male joint member, being rigidly affixed to a fuselage rib and provided with a corresponding locking pin hole, and each locking means being a locking pin, wherein each male joint member may rotate through, and be locked with, each female joint member, and wherein the same pin joint members can lock th wing in a flight configuration and a storage configuration.

15. The apparatus recited in claim 13, wherein the load bearing pin joints are disposed radially and concentric to said rotatable load bearing member, each upper pin joint member, a male joint member, being rigidly affixed to a wing spar and provided with a locking pin hole, each lower pin joint member, also a male joint member, being rigidly affixed to a fuselage rib and provided with a locking pin hole, and each locking means comprising a sleeve, slidably encompassing said upper and lower pin joint members and provided with corresponding upper and lower pin holes, and upper and lower looking pins, wherein when unlocked, each upper pin joint member may rotate past, and align, with, each lower pin joint member, and wherein the same pin joint members can lock the wing in a flight configuration and a storage configuration.

16. The apparatus recited in claim 10, the tail empennage further comprising:

a folding control surface, wherein during storage the control surface is folded to provide additional clearance for the tilt-rotor-prop assembly.