An aircraft steering cable guide

Abstract

The invention provides an airplane operation control steel rope guide piece which is characterized by comprising a first semicylindrical guide piece, a second semicylindrical guide piece, two rubber rings and two outer rings for locking, wherein semicircular holes are formed in the centers of the first semicylindrical guide piece and the second semicylindrical guide piece; the first semicylindrical guide piece and the second semicylindrical guide piece form an integrated cylinder after being integrated; the two semicircular holes form a circular hole through which a steel rope passes; two groups of external threaded slots with opposite directions are formed outside the first semicylindrical guide piece; two groups of external threaded slots with opposite directions are formed in the second semicylindrical guide piece.

Description

technical field [0001] The invention relates to the field of clamps for control systems, in particular to the field of clamps for aircraft control cables. Background technique [0002] Existing guides usually need to be positioned on the structure to open holes and install nuts ( figure 1 ), and then the guide is fixed to the structural frame 4 by bolts 2. During the aircraft assembly process, due to the sagging of a certain section of the steel cable 5, it is often necessary to temporarily install the guide 3. For the aircraft that has entered the final assembly stage, the positioning is difficult to achieve, the installation process is difficult, and the impact of the opening position on the structural strength needs to be considered . Moreover, the existing guide member processing needs to consider the position of the center of the steel cable to determine the opening position, and then consider the position of the fixed point, so the structure is complicated. Moreover...

AI Technical Summary

Problems solved by technology

During the aircraft assembly process, due to the sagging of a certain section of the steel cable 5, it is often necessary to temporarily install the guide 3. For the aircraft that has entered the final assembly stage, the positioning is difficult to achieve, the installation process is difficult, and the impact of the opening position on the structural strength needs to be considered

In addition, the processing of the existing guide parts needs to consider the position of the center of the steel cable to determine the opening position, and then consider the position of the fixed point, so the structure is complicated

And different shapes need to be designed according to different installation positions, there is no versatility, the processing and design process is complicated, and the out-of-tolerance phenomenon is serious

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