Aircraft Flow Body Trailing-Edge Structure for Larger De-Iced Area
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
The use of honeycomb parts at the trailing edge of aircraft flow bodies limits the effective anti- or de-iced area and increases manufacturing costs.
Innovation Solution
A flow body design for aircraft wings featuring a simplified trailing-edge component made through extrusion or machining, which is combined with a front skin to form a hollow structure, allowing for a larger anti- or de-iceable area and reduced manufacturing costs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a honeycomb structure is used at the trailing edge of a flow body, then mechanical stability is achieved, but the anti- or de-iced area is reduced and manufacturing costs increase
Solution Approach 1:
The flow body is divided into modular components: a front skin and a separate trailing-edge component. This segmentation allows the trailing edge to be designed independently with optimized geometry for de-icing, while the front skin can be maximized for anti-icing coverage. The modular design enables the trailing-edge component to be manufactured separately and attached to the front skin, achieving both mechanical stability and maximum de-iced area without the constraints of a continuous honeycomb structure.
Solution Approach 2:
The trailing-edge component is constructed using composite materials, specifically a solid structure made from fiber-reinforced plastics through RTM (Resin Transfer Molding) or similar processes. This composite construction provides the necessary mechanical stability and strength at the trailing edge while allowing for complex geometries that maximize the de-iced area. The composite material enables a solid trailing-edge component that is both structurally sound and aerodynamically optimized.
2Strength
If a honeycomb structure is used at the trailing edge of a flow body, then mechanical stability is achieved, but manufacturing costs increase
Solution Approach 1:
By segmenting the flow body into a front skin and a separate trailing-edge component, each part can be manufactured using optimized processes. The trailing-edge component can be produced via RTM or similar composite manufacturing techniques, which are cost-effective for producing complex structural parts. This segmentation avoids the need to manufacture an entire honeycomb structure, reducing material costs and manufacturing complexity while maintaining mechanical stability at the critical trailing edge.
Solution Approach 2:
The invention changes the manufacturing approach from traditional honeycomb construction to composite material fabrication using RTM or similar processes. This parameter change in manufacturing methodology reduces costs by eliminating the need for expensive honeycomb core materials and complex assembly procedures, while still achieving the required mechanical stability through the solid composite trailing-edge component.
3Strength
If a separate trailing edge made from metal honeycomb is used, then mechanical stability is achieved, but the weight increases
Solution Approach 1:
The trailing-edge component is constructed from fiber-reinforced plastic composites rather than metal honeycomb structures. These composite materials provide high strength-to-weight ratios, achieving the necessary mechanical stability at the trailing edge while significantly reducing the overall weight compared to traditional metal honeycomb constructions. The solid composite structure eliminates the need for heavy metal cores and fasteners required in honeycomb assemblies.
Data Source
Figure 1~2
Figure 3
AI summary
A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.