Aircraft door hinge mechanism

• US 5,289,615 A
• Filed: 11/08/1991
• Issued: 03/01/1994
• Est. Priority Date: 11/08/1991
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kishi, Hajime, Urasawa, Takayoshi, Odell, Richard B., Hamatani, Tomio, Banks, Eddie D.
• Primary Examiner(s): Jones, David
• Assistant Examiner(s): Cuda, Carmine
• Application Number:
  US07/791,663
• Time in Patent Office: 844 Days
• Field of Search: 16/366, 244/129.5, 244/129.4, 49/246
• US Class Current: 16/366
• CPC Class Codes: B64C 1/1407 Doors; surrounding frames
• CPC Class Codes: B64C 1/143 of the plug type
• CPC Class Codes: E05D 3/12 with two parallel pins and one arm
• CPC Class Codes: E05D 3/122 Gear hinges
• CPC Class Codes: E05Y 2900/132 Doors
• CPC Class Codes: E05Y 2900/502 for aircraft or spacecraft

Abstract

A hinge assembly (14) for attaching a translating-motion-type aircraft door (10) to an aircraft fuselage (12) is disclosed. The hinge assembly (14) includes a fitting (28) that is pivotally attached to the portion of the aircraft fuselage (14) adjacent the door opening (16) in the fuselage in which the door (10) is normally seated. The door is attached to the hinge fitting (28) by way of a universal shaft (30) that is rotatably attached to the free end of the hinge fitting (28). A drivebelt (32) is anchored at one end to the aircraft fuselage (12) and is attached at the opposed end to the universal shaft (30) so as to move in unison with the shaft. When the hinge assembly (14) of this invention is opened, the hinge fitting (28) pulls on the drivebelt (32) so as to cause its movement and the subsequent movement of the universal shaft (30). The universal shaft (30) is rotated about the hinge fitting (28) so as to maintain the door (10) attached thereto in a constant angular relationship relative to the longitudinal axis of the aircraft fuselage (12).

Claims

1. A translating motion hinge assembly for connecting an aircraft door to a fuselage wherein, the door is adapted to be seated in a closed position in a door opening formed in the fuselage, the hinge assembly comprising:

a hinge fitting having first and second opposed ends, said hinge fitting first end being pivotally attached to the aircraft fuselage adjacent the door opening and said hinge fitting being positioned so that when said door is in the closed position, said hinge fitting is spaced from the door opening;

a universal shaft rotatably attached to said hinge fitting second end, said universal shaft including at least one linkage element for connecting the door to said universal shaft so that the aircraft door pivots around said second end of said hinge fitting in unison with the rotation of said shaft;

a first fixed sprocket attached to the aircraft fuselage adjacent the location said hinge fitting is attached to the fuselage and a second sprocket mounted for rotation to said universal shaft, and

a drive belt assembly including an open-ended rubber belt, said rubber belt having a pair of opposed ends, and an adjustable tensioner for connecting said ends of said drive belt wherein, said rubber belt is coupled to said sprockets so that when said hinge fitting is moved from the door closed position to a door open position, said drive belt causes said universal shaft to rotate so as to maintain the door in a substantially parallel orientation relative to the fuselage opening.

2. The hinge assembly of claim 1, wherein said hinge fitting is formed of at least two sections that are angularly offset from each other so that the door is moved from the door closed position to the door open position said hinge fitting is pivoted through the door opening and the door is laterally offset from the door opening.

3. The hinge assembly of claim 2, further including at least two linkage elements for connecting the aircraft door to said universal shaft, said linkage elements being pivotally connected to said universal shaft so that the door can move vertically relative to said hinge fitting.

4. The hinge assembly of claim 1, further including a pair of idler sprockets rotatably attached to said hinge fitting wherein said rubber belt is partially wrapped about each said idler sprocket.

5. The hinge assembly of claim 2, further including a pair of idler sprockets rotatably attached to said hinge fitting wherein said idler sprockets are positioned at a location where said hinge fitting sections meet and said rubber belt is partially wrapped about each said idler sprocket.

6. The hinge assembly of claim 2, wherein said shoulder section and said outboard section of said hinge fitting are axially offset by approximately 45°

.

7. The hinge assembly of claim 1, further including a snubber assembly attached between said universal shaft and said hinge fitting so as to slow the motion of said hinge fitting when said hinge fitting is moved from the door closed position to the door open position.

8. The hinge assembly of claim 1, wherein said fixed sprocket is rotatably attached to said hinge fitting and further including an anchor assembly connected between said fuselage and said fixed sprocket for preventing rotation of said sprocket.

9. A translating motion hinge assembly for connecting an aircraft door to a fuselage, wherein the door is adapted to be seated in a closed position in a door opening formed in the fuselage, comprising:

a hinge fitting having a shoulder section adjacent the fuselage and an outboard section connected to said shoulder section, said shoulder section being pivotally attached to the fuselage, said outboard section having a free end distal from said shoulder section wherein, said shoulder section and said outboard section are axially offset from each other so that when the aircraft door is in an open position, the aircraft door is laterally spaced from the door opening and said shoulder section and said outboard section are axially offset by less than 90°

;

a universal shaft rotatably attached to said free end of said hinge fitting outboard section wherein, said universal shaft includes at least one linkage element for connecting the door to said universal shaft so that the aircraft door pivots around said free end of said hinge fitting outboard section in unison with the rotation of said shaft;

a pulley assembly including a fixed pulley secured to the aircraft fuselage adjacent the location said hinge fitting is attached to the aircraft fuselage, a rotating pulley attached to said universal shaft to rotate in unison therewith, and a twin-spindle idler pulley rotatably mounted to said hinge assembly at a location approximately where said shoulder section in said outboard section of said hinge fitting meet; and

a drive belt in the form of a closed loop cable wrapped at a first end around said fixed pulley, at a second end around said rotating pulley, and wrapped at separate locations around said idler pulley so that the opposed sections of said cable are disposed over separate ones of said idler pulleys so that when said hinge fitting is moved from the door closed position to the door open position, said drive belt causes said universal shaft to rotate so as to maintain the door in a substantially parallel orientation relative to the fuselage door opening.

10. The hinge assembly of claim 9, further including a snubber assembly attached between said universal shaft and said hinge fitting so as to slow the motion of said hinge fitting when said hinge fitting is moved from the door closed position to the door open position.

11. The hinge assembly of claim 9, wherein said idler pulley is adjustably mounted to said hinge fitting.

12. The hinge assembly of claim 9, wherein said shoulder section and said outboard section of said hinge hitting are axially offset from each other by approximately 45°

.

13. The hinge assembly of claim 9, further including at least two linkage elements for connecting the aircraft door to said universal shaft, said linkage elements being pivotally connected to said universal shaft so that the door can move vertically relative to said hinge fitting.

14. A hinge assembly connecting a translating motion-type aircraft door to an aircraft fuselage wherein, the door is dimensioned to be seated in an opening formed in the fuselage, the fuselage including a plurality of stops preventing the outward movement of the door, the door including a latch-lock mechanism for selectively lifting the door above the fuselage stops, said hinge assembly comprising:

a hinge fitting having a pair of opposed ends, said hinge fitting having a first end pivotally attached to the aircraft fuselage adjacent the door opening and a second end distal from the aircraft fuselage, said hinge fitting being positioned so that, when said door is seated in the door opening, said hinge fitting is spaced from the door opening;

a universal shaft rotatably attached to said second end of said hinge fitting;

at least two linkage elements, said linkage elements being connected to said universal shaft at spaced-apart locations, said linkage elements being pivotally connected to said universal shaft and the aircraft door to allow the aircraft door to vertically shift position relative to said hinge fitting and move about the fuselage stops so that the aircraft door rotates around said second end of said hinge fitting in unison with the rotation of said shaft;

a first fixed sprocket attached to the aircraft fuselage adjacent the location said hinge fitting is attached thereto and a second sprocket mounted on said universal shaft for rotation in unison with said shaft; and

a drive belt assembly including an open-ended rubber belt, said rubber belt having teeth adapted to interlock with said sprockets and a pair of opposed ends, and an adjustable tensioner for connecting said ends of said rubber belt wherein, said rubber belt is coupled to said sprockets so as to cause said universal shaft to rotate so as to maintain the aircraft door in a substantially parallel orientation relative to the door opening and said drive belt assembly is separate from the aircraft door latch-lock assembly.

15. The hinge assembly of claim 14, wherein said hinge fitting is formed from at least two sections that are angularly offset from each other and said hinge fitting is attached to said aircraft fuselage so that said hinge fitting can be pivoted through the door opening, and so that when the door is moved to an open position, the door is laterally offset from the door opening.

16. The hinge assembly of claim 15, wherein said shoulder section and said outboard section of said hinge fitting are axially offset by approximately 45°

.

17. The hinge assembly of claim 14, further including a pair of idler sprockets rotatably attached to said hinge fitting on opposite sides of said fitting whereby said rubber belt is wrapped partially around each said idler sprocket.

18. The hinge assembly of claim 14, further including a snubber assembly attached between said universal shaft and said hinge fitting so as to slow the motion of said hinge fitting when said hinge fitting is moved from the door closed position to the door open position.

19. The hinge assembly of claim 14, wherein said fixed sprocket is rotatably attached to said hinge fitting and further including an anchor assembly connected between said fuselage and said fixed sprocket for preventing rotation of said fixed sprocket.