Landing gear pad assembly and method of reducing loading of fasteners upon installation thereof
AssigneeLord Corporation
InventorWilliam Scott Redinger
Life of this patent
Estimating the term…
Abstract
An elastomer landing gear pad assembly (20) and method of reducing loading of installation fasteners (17) including a cap (15) and an elastomer pad (21) including a crown (22) on at least one edge thereof extending between the top (26) and at least one of the peripheral sides (24). Upon tightening the fasteners (17), the crown (22) comes into progressive contact with the contact surface thereby compressing the pad (21). The crown minimizes stress buildup in the fasteners upon substantial compression of the pad.
Claims15
A landing gear pad assembly adapted to be fastened to a fuselage by way of fasteners to secure a landing gear cross tube to said fuselage, comprising:
- a) a rigid cap adapted to be mounted to said fuselage by said fasteners, and
- b) an elastomer pad including a top and peripheral sides, said elastomer pad received on an upper surface of said cap, said elastomer pad including an edge crown extending from at least one of said peripheral sides to said top wherein upon installation, said top first engages said cross tube and upon progressively applying tightening torque to said fasteners, said edge crown progressively engages said cross tube resulting in lessened stresses in said fasteners as a result of tolerance stack ups.
A method for reducing stresses in fasteners used to fasten a landing gear pad assembly to a fuselage to secure a landing gear cross tube in place relative to the fuselage, comprising the steps of:
- a) providing a rigid cap on said assembly, said cap adapted to be mounted to said fuselage by said fasteners,
- b) providing an elastomer pad on said assembly, said elastomer pad including a top and peripheral sides, said elastomer pad received on an upper surface of said cap,
- c) forming an edge crown on said elastomer pad which extends from at least one of said peripheral sides to said top, and
- d) installing said assembly to said fuselage by tightening said fasteners causing said top to first engage said cross tube and upon progressively applying tightening torque to said fasteners, said edge crown progressively engages said cross tube resulting is lessened stresses in said fasteners as a result of tolerance stack ups.
An elastomer pad assembly adapted to be fastened to a first structure by way of fasteners to secure a second structure to the first structure, the elastomer pad assembly comprising:
- a) a rigid cap adapted to be mounted to said first structure by said fasteners, and
- b) an elastomer pad received on an upper surface of said cap, said elastomer pad including a top and peripheral sides, said elastomer pad including an edge crown extending from at least one of said peripheral sides to said top wherein upon installation, said top first engages said second structure and upon progressively applying tightening torque to said fasteners, said edge crown progressively engages said second structure resulting is lessened stresses in said fasteners as a result of tolerance stack ups.
An elastomer pad assembly adapted to be fastened to a first structure by way of one or more fasteners to restrain motion of a second structure relative to the first structure, the elastomer pad assembly comprising:
- a) a rigid cap adapted to be mounted to said first structure by said fasteners, and
- b) an elastomer pad receivable between one of an engagement surface on said first structure and an engaging surface on said second structure or an engagement surface on said cap and an engaging surface on said second structure, said elastomer pad including a top and peripheral sides, said elastomer pad including an edge crown extending from at least one of said peripheral sides to said top wherein upon installation, said top first engages one of said engaging and said engagement surfaces and upon progressively applying tightening torque to said fasteners, said edge crown progressively engages said surface resulting is lessened stresses in said fasteners as a result of tolerance stack ups.
Dependencies are inferred from the claim text.