Modular Rotary Actuation for Thin-Wing Control Surfaces
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Solution Overview
Problem
Existing aircraft actuators are too large for thin wing configurations, causing drag and reducing aerodynamic efficiency, and electromechanical actuators are prone to jamming and failure, posing safety risks.
Innovation Solution
A rotary driver actuation system with multiple interconnected electromechanical actuator modules, each with a lever arm and breakout mechanism, allowing for redundancy and smaller module sizes, and a force multiplier link to enhance torque output.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If a single large actuator is used to deliver required performance, then the actuator can provide sufficient force, but the actuator becomes too large to fit within thin aircraft wing sections
Solution Approach 1:
The patent divides a single large actuator into multiple smaller actuator modules (typically three or more). Each module contributes a portion of the total required force, allowing the system to achieve the necessary output force while each individual module remains compact enough to fit within thin wing sections. The modules are arranged in a distributed configuration rather than consolidating force in one location.
Solution Approach 2:
The patent combines the output of multiple actuator modules to achieve the total force required. The modules work together in unison, with their individual forces summing to meet the overall actuation requirement. This merging of multiple small force sources replaces the need for a single large force source.
2Extent of automation
If electromechanical linear actuators are used to enable electronic actuation, then electronic control is achieved, but the actuators become prone to jamming and failures
Solution Approach 1:
The patent segments the actuation system into multiple independent actuator modules. If one module jams or fails, the other modules can continue to operate, providing redundancy and maintaining system reliability. This segmentation isolates failures to individual modules rather than causing complete system failure.
Solution Approach 2:
The patent incorporates breakout mechanisms in each actuator module that allow the module to safely disengage or yield under excessive load or jamming conditions. This beforehand cushioning prevents catastrophic failure by providing a predetermined failure mode that protects the overall system when individual modules encounter problems.
3Volume of moving object
If actuators are housed in blisters on the wing to accommodate their size, then the actuators can be installed, but drag increases and aerodynamic efficiency is reduced
Solution Approach 1:
The patent segments the actuation system into multiple small modules that can be distributed within the wing structure rather than requiring a single large external housing. This allows the actuator components to be integrated into the existing wing geometry without adding external blisters that would increase drag.
Solution Approach 2:
The patent redistributes actuator modules along the span of the wing rather than concentrating them in one location. This spatial distribution in another dimension allows the actuators to be housed within the wing's internal volume without requiring external protrusions, thereby maintaining aerodynamic efficiency.
Data Source
AI summary
An actuation system for an aircraft control surface. The actuation system may include a rotary driver and three or more actuator modules, and each actuator module may be connected to the rotary driver such that the three or more actuator modules are configured to drive rotation of the rotary driver in combination.