Movable Wing Tip Device for Airport Span Limits
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Solution Overview
Problem
Large passenger aircraft with increased performance efficiency face limitations due to maximum wing span restrictions imposed by airport operating rules, leading to sub-optimal performance in flight configurations, as existing moveable wing tip devices are not adequately tailored for different flight conditions.
Innovation Solution
A method for configuring a wing tip device on an aircraft to adjust its lift coefficient and sweep angle across multiple configurations, including a ground configuration, take-off configuration, and flight configurations, allowing the wing tip device to be optimized for specific phases of flight, such as take-off, climb, and cruise, while ensuring airport compatibility limits are maintained.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the wing span is increased to improve performance efficiency, then fuel burn reduction is achieved, but the aircraft exceeds airport compatibility limits for ground operations
Solution Approach 1:
The patent applies a moveable wing tip device that can dynamically change its configuration between a flight configuration (extending outward to increase span for fuel efficiency) and a ground configuration (retracting or folding to reduce span for airport compatibility). This dynamic adjustment allows the aircraft to optimize wing span based on operational phase, resolving the contradiction between needing large span for fuel efficiency and small span for ground operations.
2Device complexity
If a single flight configuration is used for all flight conditions, then device complexity is reduced, but performance is sub-optimal across different flight phases
Solution Approach 1:
The patent implements a wing tip device with multiple discrete configurations (first flight configuration with first sweep angle for take-off/climb, second flight configuration with second sweep angle for cruise) that can be actively adjusted based on flight phase. This dynamic reconfiguration optimizes aerodynamic performance for each specific flight condition, resolving the contradiction between simple single-configuration design and optimal multi-phase performance.
Solution Approach 2:
The patent changes geometric parameters of the wing tip device, specifically the sweep angle, between different flight configurations. By adjusting the sweep angle parameter (first sweep angle vs. second sweep angle), the device optimizes lift and drag characteristics for different flight phases, achieving superior performance across the full flight envelope while maintaining a relatively simple mechanical structure.
3Productivity
If the wing tip device is moved to increase span beyond airport limits, then performance efficiency is improved, but compliance with gate limits is violated during ground operations
Solution Approach 1:
The patent employs a dynamically adjustable wing tip device that transitions between ground configuration (compliant with airport gate limits) and flight configuration (exceeding gate limits for optimal performance). This dynamic adaptability allows the aircraft to meet regulatory requirements during ground operations while achieving superior performance efficiency during flight, resolving the contradiction between fixed span compliance and variable performance needs.
Data Source
AI summary
A method of configuring a wing tip device (7) on an aircraft (1), including: undertaking ground-based operations at an airport with the wing tip device (7) in a ground configuration, in which the span of the aircraft is within an airport compatibility limit, moving the wing tip device (7) to a take-off configuration in which the wing tip device (7) is moved away from the ground configuration such that the span of the aircraft is increased and such that the wing tip device (7) has a first lift coefficient; taking-off with the wing tip device (7) in the take-off configuration; moving the wing tip device from the take-off configuration to a flight configuration, in which the wing tip device has a second lift coefficient, the second lift coefficient being lower than the first lift coefficient. The lift coefficient may be changed by adjusting the sweep of the wing tip device (7).