Differential Flap Control via Single Power Drive Link
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Solution Overview
Problem
Current aircraft systems move all trailing edge high lift devices in unison during takeoff and landing, leading to sub-optimal drag/lift tradeoffs, decreased efficiency, increased fuel costs, and noise due to non-equivalent incremental motion requirements for inboard, outboard, and midspan flaps.
Innovation Solution
A system utilizing a single power drive link with a controller to differentially adjust flap positions based on desired positions, aircraft speed, weight, and altitude, allowing optimal positioning of flaps without the need for multiple drive links.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If all flap surfaces are moved in unison with the same increment, then the aircraft structure is simpler and requires only a single power drive unit, but the drag/lift tradeoff is sub-optimal leading to decreased efficiency and increased fuel costs
Solution Approach 1:
The patent segments the flap control system by providing independent control for inboard, midspan, and outboard flaps. Each flap surface can be positioned independently according to its optimal deflection angle for specific flight conditions, rather than moving all flaps in unison. This segmentation enables optimized drag/lift tradeoffs while maintaining acceptable system complexity through a coordinated control strategy.
Solution Approach 2:
The patent applies local quality by allowing different flap surfaces to have different deflection increments based on their specific aerodynamic requirements. The control system determines optimal deflection angles for each flap location (inboard, midspan, outboard) independently, recognizing that each location experiences different airflow characteristics and requires tailored positioning for optimal performance.
2Loss of energy
If multiple independent power drive units are used for each flap surface, then optimal positioning of each flap is achieved, but the aircraft weight and structural complexity increase
Solution Approach 1:
The patent merges the control functions for multiple flap surfaces into a single coordinated control system. Instead of using separate power drive units for each flap, the system uses one control architecture that independently positions inboard, midspan, and outboard flaps by calculating optimal deflection angles for each surface based on flight conditions, thereby achieving differential flap control without the weight penalty of multiple independent drive units.
Solution Approach 2:
The control system exhibits universality by using a single control mechanism that can independently manage multiple flap surfaces. The system universally applies the same control logic to determine optimal deflection angles for different flap locations, allowing one control system to perform the function of multiple independent systems would otherwise require.
3Ease of operation
If a trade-off position is used for all flap surfaces, then a compromise drag/lift tradeoff is achieved, but the flaps are not in their optimal positions leading to further potential efficiency gains
Solution Approach 1:
The patent implements dynamic flap control by continuously determining optimal deflection angles for inboard, midspan, and outboard flaps based on real-time flight conditions such as aircraft speed, weight, and altitude. Rather than using a static trade-off position, the system dynamically adjusts each flap's deflection angle to its optimal value for the current flight phase, maximizing fuel efficiency while maintaining operational simplicity through automated control.
Data Source
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AI summary
A method for differentially adjusting a first deployable lift device (111) and a second deployable lift device (116) on a wing (110). The first deployable lift device (111) and said second deployable lift device (116) are coupled to a single power drive link. The method comprises: determining a first desired position for said first deployable lift device and a second desired position for said second deployable lift device, based on a desired position signal; activating a first motor to move said first deployable lift device by a first total movement amount, said first total movement amount being determined by subtracting a first current position of said first deployable lift device from said first desired position; determining a second total movement amount for said second deployable lift device by subtracting a second current position of said second deployable lift device from said second desired position; determining a first differential movement amount by subtracting said first movement amount from said total amount said second deployable lift device will move; and activating a second motor to move said second deployable lift device by first differential movement amount.