Sinking hinge type flap rocker arm support structure

Abstract

The invention relates to the technical field of the design of the support structure of the aircraft flap motion mechanism, in particular to a sinking hinge type flap rocker arm support structure comprising a flap rocker arm, a flap inner end rib, a flap rib II, two support tubes, four flange supports, two sets of through bolts A, two sets of through bolts B and 16 sets of connection bolts. On thebasis of the structure of combination of the support tubes and a flange support base, adjustment of mounting positions of the support tubes in any direction is realized, so that the design compensation requirement of the coaxiality adjustment of the intersection of the rocker arm of the flap is met; since the support tubes and the flange support base are designed to be split parts, the maintainability and interchangeability of the flap rocker arm and the connection structure are improved effectively, the requirements for the machining accuracy of the parts are also low, so that the manufacturing cost is lowered effectively; and the main bearing members such as connecting bolts of the support tubes and the flange support base mainly carry the shearing and bending loads, so that the stress form is good and the connection reliability is also high.

Description

technical field [0001] The invention relates to the technical field of supporting structure design of an aircraft flap motion mechanism, in particular to a sinking hinge type flap rocker arm supporting structure. Background technique [0002] Common sinking hinged flaps are located between the hinge mechanism in the wing body fairing and the flaps are usually connected to the rib web at the inner end of the flaps by integral joints, as shown in the ARJ21-700 aircraft as shown in the figure below. First of all, since the hinge mechanism in the wing body fairing is installed on the fuselage, while other hinge mechanisms are installed on the wing, different assembly frames lead to the coaxiality of the hinge points on the wing and the fuselage need to rely on improving the parts To ensure the manufacturing accuracy of the assembly tooling, the manufacturing cost of the aircraft is greatly increased; secondly, the front and rear connecting joints and the inner end ribs of the fl...

AI Technical Summary

Problems solved by technology

First of all, since the hinge mechanism in the wing body fairing is installed on the fuselage, while other hinge mechanisms are installed on the wing, different assembly frames lead to the coaxiality of the hinge points on the wing and the fuselage need to rely on improving the parts To ensure the manufacturing accuracy of the assembly tooling, the manufacturing cost of the aircraft is greatly increased; secondly, the front and rear connecting joints and the inner end ribs of the flaps are connected by multiple sets of bolts, and the disassembly and maintenance period is longer; finally, the flaps The moment generated by the hinge point load at the connection between the support structure and the flap end rib needs to be transmitted by the bolts to bear the tension and compression loads. This type of force is unfavorable to the end rib web and the connecting bolts, resulting in low connection reliability and would lead to a large increase in the weight of the structure

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