Aircraft flap and control method thereof

By setting up a translation and rotation mechanism on the aircraft flap, the translation and rotation of the flap is independently controlled, which solves the problem of traditional flap movement mechanisms increasing aerodynamic drag and not being able to be independently controlled, and improves the fuel economy and flight performance of the aircraft.

CN120397246AActive Publication Date: 2025-08-01SHANGHAI AIRCRAFT MFG
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Patent Information

Application Number
CN202410134064.4
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2024-01-31
Publication Date
2025-08-01
Estimated Expiration
2044-01-31

AI Technical Summary

Technical Problem

Traditional aircraft flap motion mechanisms require a larger fairing to wrap, increase aerodynamic drag, reduce fuel economy, and cannot independently control the translation and rotation of the flap, limiting flight performance.

Method used

The flap, a translation mechanism and a rotation mechanism are adopted to control the translation and rotation of the flap through the first connecting assembly and the second driving assembly respectively. The translation mechanism is fixed to the fixed trailing edge of the wing, and the rotation mechanism is movably installed on the fixed trailing edge. The two are electrically connected to the controller to achieve independent control.

Benefits of technology

It reduces the use area of the fairing, reduces aerodynamic drag, improves the working performance of the flap, can independently control the translation and rotation of the flap, and improves the flight performance of the aircraft.

✦ Generated by Eureka AI based on patent content.
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Abstract

The invention discloses an aircraft flap and an aircraft flap control method. The aircraft flap comprises a flap body, a translation mechanism, two rotating mechanisms and a controller. The translation mechanism comprises a first connecting assembly and a first driving assembly, one end of the first connecting assembly is fixedly connected to the fixed rear edge of the wing, the other end of the first connecting assembly is rotationally connected with a connecting joint of the flap, and the first driving assembly can drive the flap to unfold or fold; the two rotating mechanisms correspond to two end ribs of the flap in a one-to-one mode, each rotating mechanism comprises a second connecting assembly and a second driving assembly, one end of each second connecting assembly is movably installed on the fixed rear edge, the end ribs are movably connected with the second connecting assemblies, and the second connecting assemblies are further in transmission connection with the second driving assemblies; the second driving assembly can drive one end, connected with the fixed rear edge, of the second connecting assembly to rotate; the first driving assembly and the second driving assembly are electrically connected with the controller. According to the airplane flap, translation and rotation of the flap can be independently controlled, and the working performance of the flap is effectively improved.
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