Gasket having a pliable resilient body with a perimeter having characteristics different than the body

Abstract

A single piece gasket is disclosed having a skeletal member, typically metallic, and a pliable body. The pliable body includes a first portion having a first firmness and a second perimeter portion have a firmer consistency. When such a composite body is placed under compression, the perimeter will tend to limit the flow of the softer inner material past the firmer perimeter region or portion of the gasket. In this manner, creep or overrun of the less firm portion material will be reduced.

1 . A seal assembly for use between an aircraft base structure having a substantially flat face and an aircraft workpiece structure having an outer perimeter and a substantially flat face positionable adjacent the flat face of the aircraft base structure, the seal assembly comprising:
 an open body skeleton including a first substantially planar surface and a second substantially planar surface, the first surface and the second surface being generally parallel with each other and extending in length and width to form an outer perimeter for the skeleton, the skeleton having a thickness between the upper surface and the lower surface, the thickness being much less than the length and width of the first surface and the second surface;   a flexible body comprising a pliable, resilient, deformable, gel body that surrounds and penetrates the skeleton before compression of the assembly between the aircraft base structure and the aircraft workpiece structure, the body including a first, inner portion and a second, outer perimeter portion, the first portion and the second portion being integrated with each other before being disposed on the aircraft base structure, the first portion having a first firmness and the second portion having a second firmness, the second firmness being greater than the first firmness, the second portion extending beyond the perimeter of the skeleton and generally conforming to the outer perimeter shape of the workpiece structure, at least the first portion of the body including a substantially flat first surface and a substantially flat second surface that are configured to be compressed between the aircraft base structure and the aircraft workpiece structure during operation, the first surface and the second surface of the skeleton being generally parallel to and lying between the first surface and the second surface of the body before compression.   
     
     
         2 . The assembly of  claim 1 , wherein the skeleton is a woven flexible material. 
     
     
         3 . The assembly of  claim 1 , wherein the skeleton is metallic. 
     
     
         4 . The assembly of  claim 1 , wherein the first portion of the body has a durometer hardness, as measured by a 37.5 g half cone penetrometer, of between 75 and 150. 
     
     
         5 . The assembly of  claim 1 , wherein the second portion of the body has a “00” durometer hardness of between 15 to 75. 
     
     
         6 . The assembly of  claim 1 , wherein the first portion of the body has a firmness of between 75 and 150, as measured by a 37.5 g half cone penetrometer, and wherein the second portion of the body has a “00” durometer hardness of between 15 to 75. 
     
     
         7 . The assembly of  claim 1 , wherein the first portion of the body is a polyurethane gel. 
     
     
         8 . The assembly of  claim 1 , wherein the flexible body has a thickness between the first surface and the second surface of the first portion, and the thickness of the flexible body before compression is approximately twice that of the skeleton. 
     
     
         9 . The assembly of  claim 1 , wherein the flexible body is approximately 30 mils thick before compression. 
     
     
         10 . The assembly of  claim 1 , wherein the perimeter of the skeleton extends into the second portion of the body. 
     
     
         11 . The assembly of  claim 10 , wherein the second portion of the body penetrates the skeleton. 
     
     
         12 . The assembly of  claim 1 , wherein the skeleton is configured to make electrical contact with at least one of the aircraft structures when the body is compressed. 
     
     
         13 . The assembly of  claim 1 , wherein the second portion of the body is tabular. 
     
     
         14 . The assembly of  claim 1 , wherein the second portion of the body is convex. 
     
     
         15 . The assembly of  claim 1 , wherein the second portion of the body is concave. 
     
     
         16 . The assembly of  claim 1 , wherein the second portion of the body is toothed. 
     
     
         17 . The assembly of  claim 1 , wherein the second portion of the body is trapezoidal. 
     
     
         18 . The assembly of  claim 1 , further including an adhesive portion configured for placement between the body and at least one of the workpiece or the base. 
     
     
         19 . The assembly of  claim 1 , further including an elastomeric perimeter gasket member configured to lay adjacent and be in contact with the second portion of the body. 
     
     
         20 . The assembly of  claim 1 , wherein the second portion of the body is undercut. 
     
     
         21 . The assembly of  claim 1 , wherein the second portion of the body is straight cut. 
     
     
         22 . The assembly of  claim 1 , wherein the second portion of the body is overcut. 
     
     
         23 . The assembly of  claim 1 , wherein the second portion of the body includes a substantially flat first surface that is generally parallel to the first surface of the first portion of the body. 
     
     
         24 . The assembly of  claim 23 , wherein the first surface of the second portion and the first surface of the first portion lie in the same plane. 
     
     
         25 . The assembly of  claim 1 , wherein the second portion of the body includes a substantially flat second surface that is generally parallel to the second surface of the first portion of the body. 
     
     
         26 . The assembly of  claim 25 , wherein the second surface of the second portion and the second surface of the first portion lie in the same plane. 
     
     
         27 . The assembly of  claim 1 , wherein the body is configured such that the aircraft workpiece structure contacts and compresses the inner portion and the outer portion of the body when the body is compressed. 
     
     
         28 . The assembly of  claim 1 , wherein the inner portion of the body has an inner perimeter. 
     
     
         29 . The assembly of  claim 28 , wherein the inner portion of the body is thinner than its inner perimeter. 
     
     
         30 . The assembly of  claim 29 , wherein the inner portion of the body is thinner than the second portion. 
     
     
         31 . The assembly of  claim 28 , wherein the inner perimeter has a firmness that is greater than the first firmness.