US2007084966A1PendingUtilityA1

Stowage bin with shear fittings

34
Individually held — no corporate assignee on recordPriority: Oct 14, 2005Filed: Oct 14, 2005Published: Apr 19, 2007
Est. expiryOct 14, 2025(expired)· nominal 20-yr term from priority
Inventors:Michael S. HaynesChad D. SchmitzJoseph Matthias Manhardt
B64D 11/003
34
PatentIndex Score
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Cited by
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References
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Claims

Abstract

An aircraft stowage bin assembly includes shear fittings configured to route a content load from the bucket of the bin assembly to the airframe in the event of a forward load condition, such as a crash or severe turbulence. When the forward inertial load factor on the stowage bin is greater than about 1 g, the shear fittings create an efficient load path from the bucket to the airframe which bypasses the large metallic or composite endframes required by the designs of many conventional overhead stowage bins. As a result, significant reductions in overall bulk and weight, as well as lower manufacturing costs, can be realized.

Claims

exact text as granted — not AI-modified
1 . A stowage bin assembly comprising: 
 an upper panel comprising one or more first shear fitting components;    a lower panel comprising one or more first shear fitting components; and    a bucket comprising one or more second shear fitting components,    wherein the bucket is configured to cooperate with the upper panel and the lower panel such that, when the bin assembly is in a closed position, the first shear fitting components engage with the second shear fitting components to create a plurality of shear fittings capable of withstanding a substantial shear force between the bucket and the panels of the bin assembly.    
   
   
       2 . The stowage bin assembly of  claim 1 , wherein the first shear fitting components comprise female components and the second shear fitting components comprise male components.  
   
   
       3 . The stowage bin assembly of  claim 1 , wherein the first shear fitting components comprise male components and the second shear fitting components comprise female components.  
   
   
       4 . The stowage bin assembly of  claim 1 , wherein the first and second shear fitting components comprise metal.  
   
   
       5 . The stowage bin assembly of  claim 1 , wherein the first and second shear fitting components comprise a composite material.  
   
   
       6 . The stowage bin assembly of  claim 1 , wherein the first shear fitting components are mounted on a back surface of the upper panel and lower panel and engage with the second shear fitting components through one or more cavities in the upper panel and lower panel.  
   
   
       7 . The stowage bin assembly of  claim 1 , wherein the second shear fitting components are surface mounted to the bucket.  
   
   
       8 . The stowage bin assembly of  claim 1 , wherein the shear fitting components are mounted to the upper panel, the lower panel, and the bucket with a bonding adhesive and one or more screws or rivets.  
   
   
       9 . The stowage bin assembly of  claim 1 , wherein the first shear fitting components are formed as an integral part of the upper panel and lower panel.  
   
   
       10 . The stowage bin assembly of  claim 1 , wherein the second shear fitting components are formed as an integral part of the bucket.  
   
   
       11 . The stowage bin assembly of  claim 1 , wherein each second shear fitting component comprises one extension having a thick portion near its base and a thinner portion near its tip.  
   
   
       12 . The stowage bin assembly of  claim 11 , wherein each first shear fitting component comprises one groove configured to engage with the extension of the second shear fitting components.  
   
   
       13 . The stowage bin assembly of  claim 1 , wherein the shear fittings are capable of withstanding a forward inertial load factor of at least about 9 g.  
   
   
       14 . The stowage bin assembly of  claim 1 , wherein the stowage bin assembly lacks a strongback panel.  
   
   
       15 . The stowage bin assembly of  claim 1 , wherein the stowage bin assembly is configured for use in an aircraft.  
   
   
       16 . The stowage bin assembly of  claim 1 , wherein the stowage bin assembly is configured for use in a bus, a train, or a ship.  
   
   
       17 . An aircraft overhead stowage bin comprising: 
 at least one support panel mounted to an interior portion of an airframe;    one or more side panels coupled to the at least one support panel;    a bucket coupled to the one or more side panels, the bucket configured to contain a selected weight load; and    means for routing the weight load from the bucket directly to the at least one support panel mounted to the airframe under a forward load condition.    
   
   
       18 . The aircraft overhead stowage bin of  claim 17 , wherein the means for routing the weight load comprises one or more shear fittings.  
   
   
       19 . The aircraft overhead stowage bin of  claim 17 , wherein the forward load condition comprises a forward inertial load factor on the overhead stowage bin which is greater than about 1 g.  
   
   
       20 . An aircraft comprising: 
 an airframe; and    one or more stowage bin assemblies mounted to the airframe, each stowage bin assembly configured to contain a selected weight load,    wherein each stowage bin assembly comprises one or more shear fittings configured to transfer the weight load directly from the stowage bin assembly to the airframe under a forward load condition.    
   
   
       21 . The aircraft of  claim 20 , wherein the forward load condition comprises a forward inertial load factor on the one or more stowage bin assemblies which is greater than about 1 g.  
   
   
       22 . The aircraft of  claim 20 , wherein the one or more shear fittings comprise metal.  
   
   
       23 . The aircraft of  claim 20 , wherein the one or more shear fittings comprise a composite material.  
   
   
       24 . The aircraft of  claim 20 , wherein the one or more stowage bin assemblies lack a strongback panel.  
   
   
       25 . The aircraft of  claim 20 , wherein the aircraft lacks an endframe configured to route the weight load to the airframe under a forward load condition.  
   
   
       26 . A method of securing a stowage bin within an aircraft, the method comprising: 
 providing at least one support panel coupled to an airframe;    providing a bucket coupled to the at least one support panel and configured to contain a selected weight load; and    securing the bucket to the at least one support panel with one or more shear fittings which, in the event of a forward load condition, transfer the weight load directly from the bucket to the at least one support panel coupled to the airframe.    
   
   
       27 . The method of  claim 26 , wherein the at least one support panel and the bucket comprise a composite material.  
   
   
       28 . The method of  claim 26 , wherein the one or more shear fittings comprise metal.  
   
   
       29 . The method of  claim 26 , wherein the one or more shear fittings comprise a composite material.  
   
   
       30 . The method of  claim 26 , wherein the forward load condition comprises a forward inertial load factor which is greater than about 1 g.

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