Trailing Edge Flap Actuation With Independent Translation and Rotation
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Solution Overview
Problem
Existing actuation means for combined trailing edge flaps and ailerons in aircraft wings fail to satisfactorily enable both high-lift and aileron functions, particularly limiting aileron functionality to the fully extended flap position and restricting motion versatility.
Innovation Solution
An actuation assembly with a track, carriage, and a first actuator that allows the flap to be adjusted between retracted and extended positions, featuring a flap-to-carriage hinging axis at the leading edge, enabling independent translation and rotation for versatile high-lift and aileron functions, including Fowler motion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a single trailing edge flap is used to combine high-lift and aileron functions, then fuel efficiency is improved and device complexity is reduced, but the actuation versatility and aileron functionality are limited
Solution Approach 1:
The actuation system is segmented into two independent actuators: a first actuator for controlling flap rotation about the hinging axis (ailerons function), and a second actuator for controlling carriage translation along the track (Fowler motion). This segmentation allows each actuator to independently control one degree of freedom, enabling full actuation versatility without excessive system complexity.
Solution Approach 2:
The system employs dynamic actuation where the flap can be rotated by the first actuator at any position along the track, and the carriage can be positioned at any location by the second actuator. This dynamic control capability enables the flap to perform both high-lift and aileron functions across its entire range of motion, rather than being limited to fixed positions.
2Force
If the flap is extended to provide high-lift function, then lift is improved, but drag increases and aileron functionality is limited
Solution Approach 1:
The flap position is dynamically controlled by the second actuator along the track, allowing the system to optimize the balance between lift and drag. The flap can be positioned at intermediate extensions rather than fully extended, and can be rotated by the first actuator to provide aileron functionality at any position, enabling drag reduction while maintaining necessary lift and control.
Solution Approach 2:
The single trailing edge flap is designed to perform multiple functions: high-lift generation through Fowler motion (carriage translation), aileron control through rotation about the hinging axis, and combined functions at intermediate positions. This multi-functionality eliminates the need for separate high-lift devices and ailerons, reducing overall drag while maintaining all necessary aerodynamic functions.
3Reliability
If traditional separate high-lift devices and ailerons are used, then functional independence is achieved, but device complexity and weight increase
Solution Approach 1:
A single trailing edge flap structure performs both high-lift and aileron functions that traditionally required separate devices. The flap can be extended along the track for high-lift function and rotated about the hinging axis for aileron function, with both functions available simultaneously or independently. This multi-functionality reduces the number of components while maintaining functional independence through separate actuation systems.
Solution Approach 2:
While the flap structure is unified, the actuation system is segmented into two independent actuators that can control the flap's two degrees of freedom independently. This segmentation ensures functional independence and reliability while reducing overall device complexity compared to traditional separate high-lift devices and ailerons with their own actuation systems.
Data Source
AI summary
Actuation assembly for a trailing edge flap of an aircraft wing, comprising: a track fixable to the aircraft wing; a carriage arranged on the track so as to be movable across a range of carriage positions along the track; a flap-to-carriage connector configured to hingeably connect the carriage to a leading edge of the flap so as to determine a flap-to-carriage hinging axis extending transverse to a main track direction of the track at the leading edge of the flap; and a first actuator configured to controllably rotate the flap with respect to the carriage about the flap-to-carriage hinging axis, wherein the actuation assembly is configured to enable the flap, when connected, to be adjusted with respect to the wing between a retracted flap position and an extended flap position by moving the carriage within the range of carriage positions along the track.