Method for reaming on latch lock connectors of airplane cargo space

Abstract

The invention discloses a method for reaming on latch lock connectors of an airplane cargo space. The method includes that: an airplane cargo space door to be processed is clamped onto a frame, and an initial positioning pin (8) is used for positioning latch lock connector initial holes before reaming; appropriate reamers (7) are selected according to the size of the latch lock connector initial holes; the initial step positioning pin (8) of the latch lock connectors (6) is demounted and replaced by the reamers, and the latch lock connector initial holes are subjected to reaming processing with the rotating speed to be 2000r / min; the finish machining reamers (7) are sequentially replaced for at least one time, the latch lock connectors (6) are subjected to graded reaming processing with the rotating speed to be 2000r / min, and when the reamers (7) are needed to be replaced, a pneumatic drill is firstly demounted from an operation space formed among the latch lock connectors (6) and then the reamers (7) are taken out; a molded step positioning pin is used for positioning latch lock connector molded holes which are already subjected to finish machining; and other latch lock connectors (6) which are not processed are processed. The method is low in manufacture cost.

Description

technical field [0001] The invention relates to a reaming method in the field of mechanical processing, in particular to a method for reaming a latch joint of an aircraft cargo door. Background technique [0002] The commercial aircraft cargo door is an electric canopy door that is hinged along the top and opens outwards. The cargo door is latched with the corresponding unit parts of the fuselage through the latch mechanism on the lower edge, such as the main cargo door latch mechanism of the B747 passenger-to-cargo aircraft. It includes 5 main load-bearing locks distributed laterally at intervals within a length of 3.5 meters. Each main load-bearing lock has two latch joints at both ends. The axiality requirement is Φ0.13 mm. Since the processing space between the two latch joints is very small, only 237.6 mm, the reaming operation space is limited, so it cannot be reamed with a radial drilling machine; the latch is finely reamed abroad. When locking the joint, use the CNC...

AI Technical Summary

Problems solved by technology

[0003] Aiming at the shortcomings and deficiencies in the prior art that the cost of special reaming equipment and supporting fixtures is very high when reaming joint holes distributed at intervals with high coaxiality precision, the present invention provides an aircraft cargo door latch joint hinge Hole method, this method does not require the use of similar special reaming equipment and supporting fixtures

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