Retractable door pins for aircraft door
AssigneeTextron Innovations Inc.
InventorsJoseph Allan Smarsh, Evan Michael Johnson, Timothy Bachman, Richard S. Conkling
Life of this patent
Estimating the term…
Abstract
A system and method for unlatching an aircraft door is disclosed. The system includes a latch pin design which enables retraction of the pin in the event the ordinary unlatching mechanical systems fail. The system includes the use of a rod that is reversely threaded on each side. Rotation of the rod either extends or retracts the pin.
Claims20
An aircraft door comprising:
- a pin latch system on the aircraft door;
- a driving mechanism configured to translate the pin latch system in and out of a receptacle in an aircraft doorframe during normal operation;
- the pin latch system including a rod including an activation mechanism and an external thread arrangement;
- a pin bearing end connected to the driving mechanism;
- an extending member supporting an insertion end;
- the pin bearing end including internal threads configured to cooperate with the external thread arrangement on a first end of the rod;
- the extending member including internal threads configured to cooperate with the external thread arrangement on a second end of the rod;
- and
- the internal threads on the pin bearing end and the extending member and the external thread arrangement on the rod together configured to decrease or increase an overall length of the pin latch system using the activation mechanism.
A system for use in unlatching an aircraft door, the system comprising:
- a pin system, the pin system configured for insertion into a receptacle in a door frame;
- the pin system configured to be operated primarily by a driving mechanism in the aircraft door, the driving mechanism configured to present the pin system in or out of an aircraft doorframe during normal operation, wherein the pin system includes:
- a rod including an activation mechanism and an external thread arrangement;
- a pin bearing end including internal threads configured to cooperate with the external thread arrangement;
- an extending member including internal threads configured to cooperate with the external thread arrangement, wherein;
- the internal threads on the pin bearing end and the extending member and the external thread arrangement on the rod together are configured to decrease or increase an overall length of the pin system using the activation mechanism;
- and
- a backup retraction subsystem, the backup retraction subsystem configured to allow for user access and manual retraction of the pin system from the receptacle upon a mechanical failure.
A pin latch for an aircraft door including a backup length modification subsystem, the backup length modification subsystem comprising:
- a threaded rod having reversely oriented threads on each end;
- an extending member arranged on an opposite end of a threaded member from a bearing member, the bearing member configured to drive the pin latch under ordinary operation;
- the extending member and pin bearing members being reversely internally threaded and being translatable apart while also being secured against rotation;
- a removable pin keeper, the removable pin keeper being securable to the threaded member locking an overall length of the pin latch at a length for ordinary operation;
- a manual activation mechanism concealed behind a removable panel, the manual activation mechanism configured to drive the threaded member in the event of a mechanical failure.
Dependencies are inferred from the claim text.