Retrofit Wing Tip Device and Movable Flight Control Surface
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Solution Overview
Problem
Existing aircraft retrofits with wing tip devices often fail to optimize span loading without internal structural alterations, particularly in aircraft designed before modern computational fluid dynamics techniques, limiting performance improvements.
Innovation Solution
A method of retrofitting a wing by replacing the existing movable flight control surface with a new one of different shape and pairing it with a wing tip device, optimizing wing loading and reducing drag without requiring internal structural changes, thereby improving lift-to-drag ratio and operational flexibility.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If wing tip devices are retrofitted to existing aircraft wings, then aircraft performance is improved, but span loading is not optimized without internal structural alterations
Solution Approach 1:
The patent applies local quality by modifying the aerodynamic characteristics of the wing tip region through the addition of a wing tip device and corresponding flight control surface, rather than requiring global structural alterations. The wing tip device changes the local flow patterns and pressure distribution at the wing tip, which optimizes span loading in that specific region without affecting the internal structure of the entire wing.
Solution Approach 2:
The patent utilizes parameter changes by adjusting the aerodynamic parameters of the wing tip through the addition of the wing tip device and modified flight control surface. By changing the geometry and configuration of these external components, the span loading distribution is optimized without requiring changes to the fundamental structural parameters of the wing itself.
2Reliability
If existing movable flight control surfaces are replaced with different shaped surfaces, then wing loading optimization is improved, but manufacturing complexity increases
Solution Approach 1:
The patent applies segmentation by separating the wing modification into distinct modules: the wing tip device and the corresponding flight control surface. This modular approach allows the aerodynamic optimization to be achieved through replaceable external components rather than requiring complex internal structural modifications, thereby improving manufacturability while maintaining optimization benefits.
Solution Approach 2:
The patent demonstrates universality by designing the wing tip device and flight control surface combination to serve multiple functions: optimizing span loading, improving aerodynamic efficiency, and providing controllable flight characteristics. This multi-functional design achieves complex aerodynamic goals through relatively simple external additions rather than complex internal modifications.
3Ease of manufacture
If wing tip devices are added without structural alterations, then retrofit ease is improved, but span loading optimization is limited
Solution Approach 1:
The patent resolves this contradiction by concentrating the optimization effect in the local wing tip region where the wing tip device is added. By focusing the aerodynamic modification at this specific location, the patent achieves meaningful span loading optimization without requiring global structural alterations, thus maintaining retrofit ease while improving performance.
Solution Approach 2:
The patent overcomes the limitation of simple additive retrofits by carefully selecting and adjusting aerodynamic parameters of the wing tip device and flight control surface combination. Through parameter optimization in these external components, the patent achieves span loading optimization comparable to more complex structural modifications, thereby maintaining ease of retrofit while improving reliability.
Data Source
AI summary
An aircraft wing is disclosed having a root end, a tip end, a span extending between the root end and the tip end, a leading edge, a trailing edge and a chord extending between the leading edge and the trailing edge, and including a main fixed wing portion having an inboard portion adjacent the root end, and an outboard portion adjacent the tip end. A wing tip device attached to the tip end of the wing; and a movable flight control surface connected at the outboard portion of the main fixed wing portion and having a leading edge, a trailing edge and a chord extending between the leading edge and the trailing edge. A ratio of the local chord length of the movable flight control surface to the local chord length of the wing varies in the spanwise direction.