Trailing Edge Flap Actuation Assembly for Compact Fowler and Aileron Motion
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Solution Overview
Problem
Existing actuation assemblies for aircraft trailing edge flaps are bulky and heavy, which affects fuel efficiency and emissions, and there is a need for improved load efficiency, robustness, and reduced weight and size.
Innovation Solution
An actuation assembly for a trailing edge flap comprising a base unit, an intermediate unit, and two actuators that allow for controllable adjustability and rotation of the flap, with a symmetrical mechanical arrangement and fairing to reduce drag, using linear and rotary actuators for balanced force transmission.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a traditional actuation assembly for a multifunctional trailing edge flap is used, then the flap can perform both Fowler motion and aileron motions, but the assembly becomes bulky and heavy
Solution Approach 1:
The patent combines the Fowler motion actuation and aileron motion actuation into a single integrated actuation assembly. The intermediate unit serves dual purposes: it provides the Fowler motion relative to the base unit while simultaneously allowing the second actuator to rotate the flap for aileron motions. This merging of functions reduces the overall weight compared to having separate actuation systems for each function.
Solution Approach 2:
The intermediate unit is designed as a multi-functional component that handles both types of motion. It is hingeably connected to the flap and can perform Fowler motion relative to the base unit while also supporting the second actuator for aileron rotations. This universal design allows a single component to fulfill multiple roles, reducing the total number of parts and weight of the assembly.
2Adaptability or versatility
If a traditional actuation assembly for a multifunctional trailing edge flap is used, then the flap can perform both Fowler motion and aileron motions, but the assembly size increases
Solution Approach 1:
The patent integrates both Fowler motion and aileron motion capabilities into a single compact actuation assembly. The intermediate unit is positioned between the base unit and the flap, allowing it to provide Fowler motion while also supporting the second actuator for aileron rotations. This integration eliminates the need for separate actuation systems, reducing the overall volume of the assembly.
Solution Approach 2:
The actuation assembly is arranged with the intermediate unit nested between the base unit and the flap. The second actuator is mounted on the intermediate unit, creating a nested configuration where components are arranged in a compact hierarchy. This nesting approach minimizes the spatial footprint of the assembly while maintaining full functionality.
3Weight of moving object
If the actuation assembly weight is reduced, then fuel efficiency improves, but load efficiency may be compromised
Solution Approach 1:
The patent employs composite materials and optimized structural designs in the actuation assembly components. The base unit, intermediate unit, and fairing are designed with material selections and structural configurations that provide high strength-to-weight ratios. This allows the assembly to be lightweight while maintaining the structural integrity and load-bearing capacity required for reliable operation.
Solution Approach 2:
The actuation assembly is divided into modular components (base unit, intermediate unit, fairing) that can be independently optimized. Each segment is designed to perform specific functions with minimal weight, and the modular structure allows for efficient load distribution. This segmentation enables the assembly to achieve low weight while maintaining overall structural strength and reliability.
4Volume of moving object
If the actuation assembly size is reduced, then aerodynamic drag decreases, but manufacturing complexity may increase
Solution Approach 1:
The compact actuation assembly is designed as a modular system with distinct base unit, intermediate unit, and fairing components. Each module has a specific function and can be manufactured independently using standardized processes. The intermediate unit serves as a bridge between the base unit and the flap, providing a clear structural hierarchy that simplifies manufacturing while achieving compact dimensions.
Solution Approach 2:
The intermediate unit is designed as a multi-functional component that simplifies the overall assembly. It provides Fowler motion relative to the base unit while also serving as the mounting structure for the second actuator. This universal design reduces the total number of parts needed and simplifies manufacturing compared to having separate structures for each function, even though the overall assembly is compact.
Data Source
Figure 1A~1B
Figure 2~3B
Figure 4A~5C
AI summary
Actuation assembly for a trailing edge flap of an aircraft wing, comprising: a base unit configured to be fixated to a main body of the aircraft wing; an intermediate unit movably connected to the base unit and configured to be hingeably connected to the flap at a leading edge of the flap about a first hinging axis extending along the leading edge of the flap, wherein the movability provides adjustability of the flap between a retracted flap position and an extended flap position; and a second actuator configured to controllably rotate the flap with respect to the intermediate unit about the first hinging axis, the second actuator being configured to be movable along with the intermediate unit with respect to the at least one base unit.