Aircraft Leading Edge Outer Wall Element Extension
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Solution Overview
Problem
Existing leading edge structures for aircraft flow control systems have a 'two-step' flow surface due to the limited extension of the outer wall element, creating obstacles for ambient flow and reducing flow efficiency, especially in downstream regions where the effect of micro pores is lower.
Innovation Solution
Extending the outer wall element from the first attachment end to the second attachment end to create a continuous, smooth flow surface, with a core assembly comprising elongate stiffeners and hollow chambers for improved airflow and increased micro pore area, and using titanium sheets for structural support.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If the outer wall element is limited in extension downstream from the leading edge point, then manufacturing is simplified and material usage is reduced, but a 'two-step' flow surface is created that forms obstacles for ambient flow and reduces flow efficiency
Solution Approach 1:
The outer wall element is divided into multiple sections (first section from leading edge to first attachment end, second section from first attachment end to second attachment end) that can be manufactured separately and then joined together. This segmentation allows each section to be optimized independently while maintaining the continuous flow surface requirement, resolving the contradiction between manufacturing simplicity and flow efficiency.
Solution Approach 2:
The first and second sections of the outer wall element are merged through a joint connection to form a continuous flow surface extending from the leading edge point to both attachment ends. This merging eliminates the flow obstacle created by discontinuous surfaces while preserving the manufacturing advantages of modular construction.
2Strength
If titanium sheet panels with sufficient width to reach from the first attachment end to the second attachment end are used, then structural integrity and flow surface continuity are improved, but material availability and cost increase
Solution Approach 1:
The titanium sheet is segmented into multiple narrower sections that can be individually manufactured and then joined together. This segmentation overcomes the limitation of unavailable wide sheets while maintaining the structural integrity and continuous flow surface required for optimal performance.
Solution Approach 2:
The leading edge structure uses a composite construction combining titanium sheets (for the outer wall element requiring strength and flow surface continuity) with other materials for the inner wall element and core assembly. This composite approach allows optimization of each component for its specific function while maintaining overall structural integrity.
3Device complexity
If the outer wall element does not extend to the attachment ends, then manufacturing complexity is reduced, but the attachment ends lack structural support from the outer wall element
Solution Approach 1:
The outer wall element is extended to merge with the attachment ends, providing direct structural support. This extension is achieved through joint connections that integrate the outer wall element with the attachment end structures, creating a unified load-bearing path without significantly increasing overall structural complexity.
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 design enhances flow efficiency by eliminating obstacles, increasing the flow control effectiveness, and optimizing weight and cost by providing full outer coverage and supporting the attachment ends, while maintaining structural integrity and smooth laminar flow.
Implementation Method 1
The outer wall element comprises a plurality of micro pores, such as perforations, forming a fluid connection between the core assembly and the ambient flow
Implementation Method 2
The inner wall element comprises openings forming a fluid connection between the core assembly and the plenum
Implementation Method 3
a leading edge structure for a flow control system of an aircraft, in particular for a Hybrid Laminar Flow Control (HLFC) system, where air is sucked in or blown out of a porous surface of a flow body in order to extend the region of laminar flow along the flow body
Data Source
AI summary
A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) surrounding a plenum (7). The leading edge panel (3) has a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing the plenum (7), an outer wall element (23) for contact with an ambient flow (25), a core assembly (97). The outer wall element (23) includes micro pores (31) forming a fluid connection between the core assembly (97) and the ambient flow (25). The inner wall element (21) includes openings (33) forming a fluid connection between the core assembly (97) and the plenum (7). The outer wall element (23) extends from the first attachment end (17) to the second attachment end (19).