Passive Gust Alleviation via Pressure Relief Valve Piston
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Solution Overview
Problem
Aircraft experience uncomfortable rides and increased metal fatigue due to wind gusts, which current gust alleviation systems struggle to mitigate effectively, especially in turbulent air conditions.
Innovation Solution
A passive gust alleviation system is implemented using a piston assembly connecting a trailing edge aerodynamic surface to the aircraft wing, with a pressure relief valve that opens when a lift load exceeds a threshold, allowing the surface to rotate and reduce lift loads, and closes when the load decreases, returning to a neutral position.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If active feedback control systems are used to reduce gust loads, then gust alleviation effectiveness is improved, but device complexity and weight increase due to electronic actuators and feedback loops
Solution Approach 1:
The aerodynamic surface is designed to automatically respond to gust loads through direct mechanical coupling via the piston assembly, eliminating the need for external sensors, controllers, and actuators. The system serves itself by utilizing the aerodynamic forces and mechanical leverage inherent in the structure to deflect the surface and reduce loads.
Solution Approach 2:
The invention extracts and eliminates the complex electronic control system (sensors, feedback loops, electronic actuators) from the gust alleviation mechanism, retaining only the essential mechanical elements (piston assembly and aerodynamic surface) needed to achieve load reduction.
2Reliability
If active feedback control systems are used to reduce gust loads, then gust alleviation effectiveness is improved, but structural weight increases due to electronic actuators and control systems
Solution Approach 1:
The aerodynamic surface is designed to automatically respond to gust loads through direct mechanical coupling via the piston assembly, eliminating the need for external sensors, controllers, and actuators. The system serves itself by utilizing the aerodynamic forces and mechanical leverage inherent in the structure to deflect the surface and reduce loads.
Solution Approach 2:
The invention extracts and eliminates the complex electronic control system (sensors, feedback loops, electronic actuators) from the gust alleviation mechanism, retaining only the essential mechanical elements (piston assembly and aerodynamic surface) needed to achieve load reduction.
3Ease of operation
If aerodynamic surfaces are deflected to counteract gust loads, then passenger comfort is improved, but metal fatigue increases due to additional structural stress
Solution Approach 1:
The piston assembly incorporates a pressure relief valve that dynamically adjusts the structural coupling between the aerodynamic surface and wing. During severe gusts, the valve opens to allow surface deflection for comfort, then closes to maintain structural integrity, creating a dynamic response that balances comfort and fatigue resistance.
Solution Approach 2:
The pressure relief valve is pre-configured to open at specific pressure thresholds, providing beforehand protection by allowing controlled deflection before excessive loads can cause metal fatigue. This preemptive mechanism cushions the structure against damaging stress cycles.
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
This system effectively reduces gust loads on the aircraft wing, minimizing metal fatigue and providing a smoother ride without the need for electronic actuators or feedback loops, thus enhancing passenger comfort and reducing structural weight.
Implementation Method 1
The piston assembly may include a pressure relief valve. The pressure relief valve may be configured to open responsive to a lift load exerted on the wing exceeding a first threshold.
Implementation Method 2
The piston assembly may be implemented using a pneumatic piston or a hydraulic piston. The piston assembly holds the trailing edge aerodynamic surface in a neutral position relative to the aircraft wing at a constant supply pressure.
Data Source
AI summary
Described herein is an apparatus comprising an aircraft wing and a trailing edge aerodynamic surface connected to a trailing edge of the aircraft wing via a piston assembly in which the piston assembly holds the trailing edge aerodynamic surface in a neutral position relative to the aircraft wing at a constant supply pressure. The piston assembly may be implemented using a pneumatic piston or a hydraulic piston. A first end of the piston assembly may be connected to the aircraft wing and a second end of the piston assembly may be connected to the trailing edge aerodynamic surface. The piston assembly may include a pressure relief valve which may open or close, raising or lowering the aerodynamic surface, responsive to lift load on the aircraft wing.