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US 6,702,231 B2Granted
Door system for creating and maintaining a secured area
OwnerGary Wardinventor
Life of this patent
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Abstract
Several embodiments are disclosed for a door system to secure the cockpit of an aircraft. One embodiment includes a frame which is hingedly coupled to an interior wall of an aircraft, such that the frame can swing from a first configuration to a second configuration. In the first configuration, the cockpit door is accessible and is not in a secure area. In the second configuration, the cockpit door is not accessible allowing the cockpit door to be opened in a secure area.
Claims15
A door system for an aircraft, the system comprising:
- a cockpit door,
- a cockpit door frame hingedly coupled to the cockpit door, wherein the cockpit door frame is adapted to be coupled to a first interior wall of an aircraft,
- a lavatory door,
- a lavatory door frame hingedly coupled to the lavatory door, wherein the lavatory door frame is adapted to be coupled to a second interior wall of an aircraft and the second interior wall is substantially perpendicular to the first interior wall, the lavatory door frame further comprising:
- a first edge and a second edge,
- wherein the first edge is adapted to be hingedly coupled to the second interior wall such that the second edge can swing from a first coupling position to a second coupling position, and
- wherein in the first coupling position the lavatory door frame is adapted to be securely coupled to the second interior wall and in the second coupling position the lavatory door frame is adapted to be securely coupled to an interior structure of the aircraft such that a passageway to the cockpit is blocked.
4 more elements
A door system for an aircraft, the system comprising:
- a door, and
- a door frame disposed about the door wherein the door is hingedly coupled to the door frame, the door frame has a first edge and a second edge, the first edge is hingedly coupled to an interior wall of an aircraft such that the second edge can be moved from a first coupling configuration to a second coupling configuration, wherein the second edge is coupled to a second structure of the aircraft.
Dependencies are inferred from the claim text.