Aircraft Heated Leading Edge Structure With Reinforcing-Member Conduction
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Solution Overview
Problem
Existing heated leading edge structures for aircraft are either complex and heavy or provide inhomogeneous heating, leading to undesired cold spots and ice accretion.
Innovation Solution
A lightweight heated leading edge structure for aircraft using an indirect heating device mounted on a reinforcing member to conduct heat to the leading edge panel, combined with a direct heating device and a control unit for temperature regulation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Temperature
If bleed air heating devices are used to warm the leading edge structure, then heating effectiveness is improved, but device complexity and weight increase
Solution Approach 1:
The patent replaces complex pneumatic heating systems with simple electric heating devices. The electric heating devices directly generate heat through resistive heating, eliminating the need for complex bleed air systems while achieving effective heating of the leading edge panel.
Solution Approach 2:
The patent extracts the heating function from complex integrated systems and implements it through simple, separate electric heating devices mounted directly on the leading edge panel. This separation allows for simpler device design and easier maintenance.
2Device complexity
If electric heating devices are mounted directly on leading edge panels, then device complexity and weight are reduced, but heating homogeneity deteriorates due to cold spots at reinforcing member connections
Solution Approach 1:
The patent applies local quality by positioning heating devices at specific locations where cold spots occur, particularly at the connection regions between reinforcing members and the leading edge panel. This targeted placement ensures uniform heat distribution across the entire panel surface.
Solution Approach 2:
The patent introduces thermal conductive material as an intermediary between the electric heating device and the leading edge panel. This intermediary ensures efficient heat transfer from the heating device to the panel, particularly at connection regions where heat transfer might be compromised.
3Temperature
If heating devices are placed at connection regions, then heating homogeneity is improved, but device complexity increases
Solution Approach 1:
The patent merges the heating function with the existing reinforcing member structure by mounting heating devices directly on these structural elements. This integration utilizes the existing structural framework to support the heating system, avoiding additional complexity while achieving uniform heating.
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
The solution provides homogeneous heating, reduces weight, and ensures efficient ice prevention while allowing easy maintenance and improved safety.
Implementation Method 1
indirect heating device being configured for heating the leading edge panel at least by conduction through the reinforcing member
Implementation Method 2
heating arrangements that are configured for heating a leading edge panel. These arrangement are critical to prevent accretion of ice on the leading edge panel of the structure
Data Source
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AI summary
This heated leading edge structure (14) for an aircraft (10), comprises: - a leading edge panel (20) having an outer surface (32) configured for contacting with an ambient flow (A), and an inner surface (34) opposite the outer surface (32), - a reinforcing member (22), connected to the inner surface (34) of the leading edge panel (20), and - a heating arrangement (24) configured for heating the leading edge panel (20); the heating arrangement (24) comprising at least one indirect heating device (44) mounted on the reinforcing member (22), said indirect heating device (44) being configured for heating the leading edge panel (20) at least by conduction through the reinforcing member (22).