Quick release hinge

Patent metadata

Field	Value
Publication number	US-9758234-B2
Application number	US-201514592593-A
Country	US
Kind code	B2
Filing date	Jan 8, 2015
Priority date	Jan 8, 2015
Publication date	Sep 12, 2017
Grant date	Sep 12, 2017

Abstract

Aspects of the disclosure are directed to a system configured for installing or removing a door from an aircraft, the system comprising: a pin, a hinge comprising a slot that forms a cavity for rotatively coupling the hinge and the pin, a clamp coupled to the pin, and a retaining mechanism on the clamp that selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged.

First claim

The invention claimed is:

1. A system for an aircraft, the system comprising:
a nacelle door;
a pin having an axis;
a hinge coupled to the nacelle door, the hinge comprising a slot that forms a cavity for rotatively coupling the hinge and the pin, wherein the slot extends partially into the hinge at a distal end of the hinge, the slot extends through the hinge between opposing sides of the hinge, the hinge is configured as a gooseneck hinge, and the hinge does not radially, relative to the axis, encircle or encapsulate the pin;
a clamp coupled to the pin; and
a retaining mechanism on the clamp that selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged.

2. The system of claim 1 , wherein the nacelle door is a latch access door.

3. The system of claim 1 , wherein the clamp comprises a through hole that rotatively receives the pin for coupling the clamp and the pin.

4. The system of claim 1 , wherein the clamp is configured to removably rotate about the pin when the retaining mechanism is disengaged with respect to the hinge.

5. The system of claim 1 , further comprising:
an attachment mechanism to couple the pin to a structure of the aircraft.

6. The system of claim 5 , further comprising:
a thermal blanket that is positioned to physically obscure access to the attachment mechanism.

7. The system of claim 1 , further comprising:
a structure comprising a latch beam on a thrust reverser; and
an attachment mechanism to couple the pin to the structure.

8. The system of claim 1 , wherein the retaining mechanism comprises at least one of a screw, a nut, or a bolt.

9. A system comprising:
a nacelle door;
a hinge coupled to the nacelle door, the hinge comprising a slot that forms a cavity for rotatively coupling the hinge to a pin such that the hinge is operable to rotate about a longitudinal axis of the pin, wherein the slot laterally extends partially into the hinge at a distal end of the hinge from an exterior peripheral surface of the hinge to a parti-cylindrical interior surface of the hinge that defines the slot, and wherein the slot longitudinally extends through the hinge between opposing sides of the hinge;
a clamp coupled to the pin; and
a retaining mechanism that couples the clamp and the hinge when the retaining mechanism is engaged with respect to the hinge and decouples the clamp and the hinge when the retaining mechanism is disengaged with respect to the hinge, wherein the retaining mechanism comprises a fastener configured to project through an aperture in the clamp to engage the hinge.

10. The system of claim 9 , wherein the retaining mechanism is on the clamp and selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged.

11. The system of claim 9 , wherein the hinge does not radially, relative to the axis, encircle or encapsulate the pin.

12. A system for an aircraft, comprising:
a nacelle door;
a hinge coupled to the nacelle door, the hinge including a slot configured to form a passageway and a cavity for receiving a pin, wherein the slot laterally extends partially into the hinge from an exterior surface of the hinge at a distal end of the hinge such that, during mating of the hinge to the pin, the pin is operable to pass laterally through the passageway and then into the cavity, and wherein the passageway and the cavity longitudinally extend through the hinge between opposing sides of the hinge;
a clamp coupled to the pin; and
a retaining mechanism on the clamp that selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged.

13. The system of claim 12 , further comprising the pin having an axis, wherein the hinge is configured to rotate about the axis when the pin is received within the cavity.

14. The system of claim 13 , wherein the hinge does not radially, relative to the axis, encircle or encapsulate the pin.

15. The system of claim 12 , wherein the hinge is configured as a gooseneck hinge.

16. The system of claim 12 , wherein the nacelle door is a latch access door associated with an aircraft nacelle.

Assignees

• Rohr Inc

Inventors

• Harding David
• Heber William

Classifications

• B64D29/08

  Inspection panels for power plants · CPC title

• B64D29/00

  Power-plant nacelles, fairings or cowlings · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• E05Y2900/502

  for aircraft or spacecraft · CPC title

• E05D7/1061

  in a radial direction (E05D7/1005 takes precedence) · CPC title