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US 10,309,434 B2Granted
Thrust reverser honeycomb panel load distribution systems and methods
AssigneeThe Boeing Company
InventorsFedor Kleshchev, Kyle Thomas, Billy P. Tung, Michael Maffeo, Robert Shaun Farrell
Life of this patent
Estimating the term…
Abstract
Provided is an aircraft propulsor thrust reverser with a fastening system. The fastening system may include a male spool and a female spool configured to be threaded into the male spool. The male spool and the female spool may be coupled to a honeycomb structure and may evenly distribute force to the honeycomb structure to prevent plastic deformation of a honeycomb core of the honeycomb structure.
Claims20
An aircraft propulsor comprising:
- a core engine;
- and
- a thrust reverser comprising an inner wall located proximate the core engine, the inner wall comprising:
- a honeycomb structure comprising a first facesheet, a second facesheet, a honeycomb core disposed between the first facesheet and the second facesheet, and an aperture, and
- a fastening system disposed within the aperture, the fastening system comprising:
- a male spool comprising:
- a male through hole,
- a male shank portion comprising an external threaded portion disposed on at least a first end of the male spool,
- a male flange portion disposed on a second end of the male spool, coupled to the first facesheet, and configured to distribute load to the honeycomb structure, and
- a male shoulder portion disposed between the male shank portion and the male flange portion and contacting a side of the first facesheet to transfer a first bearing load to the first facesheet;
- and
- a female spool comprising:
- a female through hole,
- a female shank portion comprising an internal threaded portion disposed within the female through hole and on at least a first end of the female spool, wherein the female shank portion is coupled to the external threaded portion to fasten the male spool and the female spool to the honeycomb structure,
- a female flange portion disposed on a second end of the female spool, coupled to the second facesheet, and configured to distribute load to the honeycomb structure, and
- a female shoulder portion disposed between the female shank portion and the female flange portion and contacting a side of the second facesheet to transfer a second bearing load to the second facesheet.
13 more elements
A fastening system for an aircraft structure, the fastening system comprising:
- a male spool comprising:
- a male through hole,
- a male shank portion comprising an external threaded portion disposed on at least a first end of the male spool,
- a male flange portion disposed on a second end of the male spool and configured to couple to a first facesheet of a honeycomb structure and distribute load to the honeycomb structure when the male flange portion is coupled to the first facesheet, and
- a male shoulder portion disposed between the male shank portion and the male flange portion and configured to contact a side of the first facesheet to transfer a first bearing load to the first facesheet;
- and
- a female spool comprising:
- a female through hole,
- a female shank portion comprising an internal threaded portion disposed within the female through hole and on at least a first end of the female spool, wherein the female shank portion is configured to couple to the external threaded portion to fasten the male spool and the female spool to the honeycomb structure,
- a female flange portion disposed on a second end of the female spool and configured to couple to a second facesheet of the honeycomb structure and distribute load to the honeycomb structure when the female flange portion is coupled to the second facesheet, and
- a female shoulder portion disposed between the female shank portion and the female flange portion and configured to contact a side of the second facesheet to transfer a second bearing load to the second facesheet.
8 more elements
Dependencies are inferred from the claim text.