Aircraft Wing Load Reduction via Proactive Control Surface Deflection
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Solution Overview
Problem
Current methods for reducing aerodynamic disturbances on aircraft, such as discrete gusts and continuous turbulence, often require reactive deflection of control surfaces, which may not adequately prevent overload on the wing structure, limiting the potential for reducing structural mass and increasing manufacturing and operational costs.
Innovation Solution
A method and device that proactively determine a load overrun range based on altitude and speed values, allowing for preventive deflection of control surfaces to mitigate potential aerodynamic disturbances, thereby reducing the risk of exceeding design load limits and allowing for a structural mass reduction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of time
If reactive deflection of control surfaces is used to reduce aerodynamic disturbances, then the response time is reduced, but the ability to prevent overload on the wing structure is insufficient
Solution Approach 1:
The patent applies preliminary action by determining a load overrun range before actual aerodynamic disturbances occur. The system proactively identifies flight conditions (altitude and speed combinations) where load thresholds might be exceeded and pre-deflects control surfaces to prevent overload, rather than waiting for disturbances to be detected and reacted to.
Solution Approach 2:
The patent implements preliminary anti-action by deflecting control surfaces in advance to counteract potential aerodynamic disturbances. The system determines deflection commands that will oppose future disturbances before they occur, based on predicted load conditions in the load overrun range, thereby preventing wing overload rather than merely responding to it.
2Strength
If larger structural mass is used in the wing, then the strength and load-bearing capacity increase, but the manufacturing and operational costs increase
Solution Approach 1:
The patent applies parameter changes by dynamically modifying the deflection angle of control surfaces based on flight conditions (altitude and speed). The system adjusts the deflection parameter in real-time to maintain wing loads within safe thresholds, allowing the wing structure to operate within optimized load ranges that reduce the required structural mass while maintaining safety.
Solution Approach 2:
The patent substitutes mechanical strengthening (increasing structural mass) with an active control system that uses aerodynamic forces (control surface deflection) to manage wing loads. Instead of relying solely on a heavier, stronger wing structure, the system uses aerodynamic counter-forces to prevent overload, thereby reducing the required structural mass while maintaining load-bearing capacity.
3Speed
If control surfaces are deflected at maximum steering speed, then the flexion of the wings is limited, but the structural mass reduction potential is not fully realized
Solution Approach 1:
The patent applies preliminary action by determining and applying control surface deflection commands before aerodynamic disturbances cause wing flexion. By proactively deflecting control surfaces in the load overrun range, the system prevents wing overload from occurring in the first place, rather than merely limiting flexion through high-speed reactive deflection, thereby enabling greater structural mass reduction.
Data Source
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AI summary
- Method and device for reducing the actual loads generated on an aircraft by an aerodynamic disturbance. - According to the invention, the device (1) comprises means (3) for determining a load overshoot range and means (4, 5, 10) for determining, when the aircraft (AC) is in said load overshoot range, steering commands for control surfaces (S1, S2, P1, P2) of the aircraft (AC) in order to reduce the loads applied to the latter.