Thin Wing Flap Actuation via Eccentric Coupler Rod Linkage
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Solution Overview
Problem
Modern thin wing aircraft face challenges in deploying aerodynamic surfaces like slats and flaps due to reduced cross-sectional area, making it difficult to house rotary actuators and drive mechanisms near the leading edge.
Innovation Solution
A flap system with a rotary actuator and a flap actuation mechanism that includes a coupler rod eccentrically supported at both ends, translating from an aft to a forward position, and driving a flap drive arm from a stowed to a deployed position.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a rotary actuator and drive mechanism are located near the leading edge of the wing, then the aerodynamic surfaces can be deployed effectively, but the device complexity increases and the available space is insufficient in thin wing profiles
Solution Approach 1:
The patent relocates the actuator from the traditional leading edge area to the trailing edge of the wing, utilizing the three-dimensional space within the wing structure. This dimensional relocation provides sufficient clearance for the actuator and drive mechanism while maintaining effective connection to the aerodynamic surfaces through the coupler rod linkage system.
Solution Approach 2:
The patent introduces a coupler rod as an intermediary component that transmits motion from the actuator to the aerodynamic surfaces. The coupler rod, working in conjunction with crank arms and linkages, serves as a mechanical mediator that bridges the gap between the remotely located actuator and the aerodynamic surfaces, enabling effective deployment without direct adjacency.
2Shape
If the cross sectional area of the wing is reduced to achieve thin wing profile, then the aerodynamic performance is improved, but the available space for housing actuators and motion linkages is significantly reduced
Solution Approach 1:
The patent exploits the third dimension by positioning the actuator at the trailing edge rather than confining it to the two-dimensional leading edge plane. This spatial redistribution allows the system to maintain a thin overall wing profile while providing sufficient volumetric space for the actuator and its linkage mechanism at the trailing edge location.
Solution Approach 2:
The patent divides the wing into functional zones, placing the actuator and drive mechanism in the trailing edge segment while keeping the leading edge segment thin and aerodynamically optimized. This segmentation allows different parts of the wing to serve different purposes - the leading edge maintains thin profile for aerodynamics while the trailing edge provides housing space for mechanical components.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This solution effectively extends the flap from a retracted to an extended position while minimizing load on the rotary actuator, overcoming the space constraints in thin wing profiles.
Implementation Method 1
A coupler rod eccentrically supported at an aft end and at a forward end is translated from an aft position to a forward position
Implementation Method 2
An inboard crank arm is coupled to the rotary actuator and engaged to the aft end of the coupler rod. The inboard crank is configured rotate responsive to rotation of the rotary actuator thereby inducing translation of the coupler rod
Implementation Method 3
An outboard crank arm engaged to a forward end of the coupler rod and is configured to rotate responsive to translation of the coupler rod
Implementation Method 4
A flap drive arm is attached to the outboard crank arm and is configured to rotate with the outboard crank arm from a stowed position to a deployed position responsive to translation of the coupler rod from the aft position to the forward position
Data Source
AI summary
A flap actuation mechanism incorporates a coupler rod eccentrically supported at an aft end and at a forward end. The coupler rod is configured to translate from an aft position to a forward position. An inboard crank arm is coupled to the rotary actuator and engaged to the aft end of the coupler rod. The inboard crank is configured rotate responsive to rotation of the rotary actuator thereby inducing translation of the coupler rod. An outboard crank arm engaged to a forward end of the coupler rod and is configured to rotate responsive to translation of the coupler rod. A flap drive arm is attached to the outboard crank arm and is configured to rotate with the outboard crank arm from a stowed position to a deployed position responsive to translation of the coupler rod from the aft position to the forward position.