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Crash load attenuating valve for an aircraft landing gear shock strut
   
Document Number
US Patent 4126212
Issued Date
November 21, 1978
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Inventors
Crawley; R. W. (West Chester, PA)
Map
Abstract
In a shock strut for an aircraft landing gear having inner and outer elongated telescoping tubes and a primary orifice selected and designed to attenuate the load level to a certain design condition which is compatible with the aircraft's structural threshold up to a certain overload sink speed, a load attenuating valve which opens when the design velocity is exceeded. The load attenuating valve includes secondary orifices held closed by a tension fuse which ruptures and opens the orifices in parallel to the primary orifice for additional flow, thus keeping the pressure drop across the orifices to an acceptable level so as to permit full stroking of the strut. In this way, as much energy as possible is absorbed before the load is transmitted to the aircraft on failure.
Drawing
Crash load attenuating valve for an aircraft landing gear shock strut - US Patent 4126212 Drawing
Drawing from US Patent 4126212
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Number of Claims:
6
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Owner
The Boeing Co. (Seattle, WA)
Published
November 21, 1978
Application Number
05/847,389
Filed
October 31, 1977
US Classification
188/317   137/71 188/376
Int'l Classification
F16F   9/02   (20060101)   F16F   9/512   (20060101)   F16F   9/50   (20060101)   B64C   25/60   (20060101)   B64C   25/00   (20060101)  
Parent Case
This is a continuation of application Ser. No. 720,426, filed Sept. 3, 1976, and now abandoned.
USPTO Field of Search
188/1C   188/269   188/279   188/280   188/281   188/282   188/284   188/313   188/317   188/322   137/68R   137/71  
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Claims
Description
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