Patent ID: 7976078
Filing Date: 2011-07-12
Classification: E05B,E05C,F16B,Y10S,Y10T

Abstract:
1. Device ( 10 ) for the detachable connection of structural parts ( 80 , 84 ), in particular in an aircraft, comprising a clamping lever arrangement ( 12 ) associated with a first structural part ( 80 ) and a clamping pin ( 14 ) associated with a second structural part ( 84 ), wherein the clamping lever arrangement ( 12 ) comprises an eccentric shaft ( 20 ) rotatably mounted about a rotation axis (A) on the first structural part ( 80 ), a clamping lever ( 16 ) mounted eccentrically and swivellably with respect to the eccentric shaft ( 20 ), and a driving bushing ( 18 ) rotatably mounted relative to the eccentric shaft ( 20 ) about the rotation axis (A) and coupled in a geared manner to the clamping lever ( 16 ), wherein the clamping lever arrangement ( 12 ) is rotated from a release position, wherein the clamping lever ( 16 ) is not engaged to the clamping pin ( 14 ), to a readiness position, wherein the clamping lever contacts the clamping pin in a non-locked position, by means of a first actuator actuating on the driving bushing; and wherein further movement of the clamping lever arrangement ( 12 ) will allow an eccentric section ( 28 ) of the eccentric shaft ( 20 ) to abut a surface of a stop section ( 76 ) of the driving bushing ( 18 ), making the clamping lever ( 16 ) to slidably move, allowing the clamping pin ( 14 ) to be received in a cavity ( 52 ) of the clamping lever ( 16 ) to lock the clamping lever arrangement, by means of a second actuator actuating on the eccentric shaft.