Linear Actuator Driven Flap Mechanism for Aircraft Wing
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Solution Overview
Problem
Existing aircraft wing mechanisms, particularly those with rear spar mounted drooping spoilers, are oversized and overcomplicated, leading to increased high-speed drag, complex assembly and maintenance, and limited space for system components in thinner aircraft wings.
Innovation Solution
A flap mechanism comprising a frame rib, a motion linkage, and a non-mechanical linear actuator, where the frame rib is connected to the aircraft wing at two points, and the motion linkage and linear actuator are positioned between the frame rib's webs, reducing complexity and space requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If rear spar mounted drooping spoiler configuration is used, then flap deployment is achieved, but fairings become deeper and wider increasing high speed drag
Solution Approach 1:
The patent repositions the actuator and drive linkage from a conventional lower-wing location to the upper surface of the wing, utilizing the third dimension (vertical space above the wing) to avoid the need for deep and wide fairings. This dimensional relocation eliminates the drag penalty while maintaining flap deployment functionality.
Solution Approach 2:
The actuator and motion linkage are nested within the wing structure itself, specifically utilizing the space between the upper skin and the spar. This nesting approach integrates the mechanism into the existing wing architecture, eliminating the need for external fairings that would increase drag.
2Ease of manufacture
If complex drive linkage with custom hardware is used, then flap deployment is achieved, but assembly, installation, and maintenance become difficult
Solution Approach 1:
The patent replaces the complex mechanical drive linkage with custom hardware with a simpler actuator system that interfaces directly with the motion linkage. This substitution reduces the number of components, simplifies assembly procedures, and improves maintainability while achieving the same flap deployment function.
Solution Approach 2:
The actuator is designed to perform multiple functions: it provides the driving force for flap deployment, interfaces with the motion linkage, and integrates with the wing structure. This multi-functionality reduces the overall system complexity and eliminates the need for separate custom hardware components.
3Ease of manufacture
If large cutouts in wing ribs are made for attachment, then actuator installation is achieved, but wing structure integrity is compromised
Solution Approach 1:
Instead of making large cutouts in the wing ribs, the patent uses localized attachment points that maintain the overall integrity of the rib structure. The attachment hardware is designed to distribute loads over smaller areas, preserving the structural strength of the wing while enabling actuator installation.
4Ease of manufacture
If actuator is positioned low to clear spoiler inner mold line, then spoiler droop is achieved, but actuator interface becomes complex and heavy
Solution Approach 1:
The patent moves the actuator from a low position to the upper surface of the wing, utilizing vertical space to clear the spoiler inner mold line without requiring the actuator to be positioned low. This dimensional relocation simplifies the actuator interface and reduces weight while maintaining spoiler droop capability.
Data Source
AI summary
A linear actuator driven flap mechanism for an aircraft wing is contained within a wing support and fairing of the aircraft wing. The rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at a first and second point. The rib frame of the flap mechanism defines a width with a first and second web. A linear actuator and a motion linkage are positioned with the width between the first and second webs of the rib frame. The linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation. As a result of the compact construction, the flap mechanism can be employed in thinner, smaller aircraft wings being designed today.