Title:
FUEL NOZZLE SYSTEM UNDER WING OF AIRCRAFT
Document Type and Number:
Japanese Patent JPS59163199
Kind Code:
A
Abstract:
A modular nozzle system particularly suitable for refueling aircraft fuel tanks includes a nozzle valve linkage mechanism which permits the nozzle body to have a shorter length than previous designs. The mechanism can be accommodated in a bearing which accepts a shaft connected to the valve. Nozzle length is further reduced by nesting the linkage in a concave sleeve valve in an adjacent pressure regulator section. The nozzle may include a mechanical fuse for releasing the connection between the nozzle body and a fuel tank upon the application of predetermined forces by means of spring biased detents in a collar around the nozzle. The nozzle may also include a swivel joint which facilitates positioning the nozzle for connection to a fuel tank. The nozzle may also include a quick disconnect assembly which facilitates connection of the nozzle to fuel supply lines. The system also may comprise an assembly fixture for assembling the mechanical fuse and a test fixture for testing the release force of the mechanical fuse.
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Inventors:
ARUBAATO DABURIYU BURAUN
Application Number:
JP3510884A
Publication Date:
September 14, 1984
Filing Date:
February 24, 1984
Export Citation:
Assignee:
ARUBAATO W BURAUN
International Classes:
B67D7/42; B64D37/16; B64F1/28; (IPC1-7): B67D5/37
Attorney, Agent or Firm:
Kuro Fukami