Wing Assemblies Flap Actuator Positioning Torque Reduction
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Solution Overview
Problem
In large commercial aircraft, the internal placement of flap actuators relative to the fuselage results in uneven spacing and undesirable torques during flap actuation, affecting the efficiency and reliability of high-lift devices like flaps.
Innovation Solution
The inboard-most flap actuator is positioned outboard of the inboard edge of the flap, decoupled from the inboard-most flap support, allowing for even spacing and reduced torque application, with optional configurations using rotary actuators and tracks for enhanced support and control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the flap actuator is positioned internal to the fuselage, then the flap support structure is simplified, but the actuator spacing becomes uneven and undesirable torques occur during actuation
Solution Approach 1:
The flap actuator is extracted from the traditional internal fuselage location and repositioned to an external location on the wing structure. This extraction resolves the contradiction by enabling even actuator spacing along the flap length while maintaining structural simplicity through the use of the existing wing framework for actuator mounting.
Solution Approach 2:
The actuator positioning moves from a constrained internal three-dimensional space to a distributed external arrangement along the wing span. This dimensional transition allows actuators to be spaced evenly along the flap length while utilizing the wing's structural framework for support.
2Volume of moving object
If the flap actuator is positioned internal to the fuselage, then mounting space is utilized efficiently, but torque application during actuation becomes undesirable
Solution Approach 1:
The actuator is extracted from the internal fuselage volume and repositioned externally on the wing. This extraction eliminates the torque application problem by allowing the actuator to apply force more directly to the flap support, while mounting space efficiency is maintained through the use of the wing's external structure.
Solution Approach 2:
The wing structure serves as an intermediary element that provides both mounting support for the actuator and a favorable lever arm for torque application. This intermediary approach resolves the contradiction by using the wing framework to transmit actuator forces efficiently to the flap.
3Manufacturing precision
If the inboard-most flap actuator is spaced away from the inboard-most flap support, then actuator spacing is optimized, but the structural connection requires additional complexity
Solution Approach 1:
The structural connection is segmented into distinct components: the actuator mounting bracket, the wing structure, and the flap support. This segmentation allows for precise actuator spacing while distributing the structural complexity across separate, manageable components that can be independently manufactured and assembled.
Solution Approach 2:
A mounting bracket or adapter serves as an intermediary component between the actuator and the wing structure. This intermediary element enables precise actuator positioning and spacing while simplifying the overall structural connection by providing a standardized interface.
Data Source
AI summary
Wing assemblies (100) comprise one or more wing support structures (24), an inboard-most flap (32), one or more flap supports (28) that operatively couple the inboard-most flap (32) to the one or more wing support structures (24), and one or more flap actuators (31) configured to operatively move the inboard-most flap (32) relative to the one or more flap supports (28). The flap support(s) (28) comprise at least an inboard-most inboard-flap support (106), the flap actuator(s) (31) comprise at least an inboard-most inboard-flap actuator (108) that is outboard of the inboard edge (102) of the inboard-most flap (32), and the inboard-most inboard-flap actuator (108) is spaced-away from the inboard-most inboard-flap support (106).