Integrated Control Valve for Aircraft Surface Vibration Suppression
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Solution Overview
Problem
Current Stability Control Augmentation Systems (SCAS) for aircraft flight control surfaces are complex and massive, limiting their effectiveness in counteracting vibrations and fluctuations, and there is a need for a more efficient and integrated solution to improve stability control.
Innovation Solution
A stability control augmentation system that integrates a piezoelectric element into the control valve, allowing for fine-tuning of hydraulic fluid flow by adjusting the cross-section of the fluid flow path, complementing the primary control provided by a spool, to enhance the stability of flight control surfaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a traditional SCAS architecture with separate mechanical linkage and hydraulic actuators is used, then stability control function is provided, but the system becomes massive and complex
Solution Approach 1:
The patent combines the control valve and augmentation mechanism into a single integrated unit. The piezoelectric element is mounted directly on the control valve body, eliminating the need for separate mechanical linkages and external augmentation devices. This merging of components directly reduces system complexity while maintaining the stability control function.
Solution Approach 2:
The control valve is designed to serve multiple functions: it acts as both the primary control element for the hydraulic actuator and the mounting base for the piezoelectric augmentation mechanism. The control valve body incorporates both the fluid control passages and the piezoelectric element mounting structure, allowing one component to perform multiple roles in the system.
2Weight of moving object
If the augmentation mechanism is integrated into the control valve, then system weight and complexity are reduced, but the control precision requirement increases
Solution Approach 1:
The patent replaces traditional mechanical augmentation mechanisms with a piezoelectric element that directly modulates the control valve opening. The piezoelectric element converts electrical signals into precise mechanical displacement at the valve needle, enabling fine control of hydraulic fluid flow without complex mechanical linkages. This substitution achieves high control precision with minimal weight.
Solution Approach 2:
The piezoelectric element changes the physical state of the control valve needle through electro-mechanical parameter changes. By applying voltage to the piezoelectric element, it undergoes dimensional changes that directly adjust the valve opening size, thereby precisely controlling the hydraulic fluid flow rate. This parameter-based control achieves fine adjustment capability.
3Object-affected harmful factors
If the piezoelectric element is used to fractionally adjust fluid flow, then vibration suppression is improved, but the system sensitivity to failure increases
Solution Approach 1:
The control valve needle acts as an intermediary between the piezoelectric element and the hydraulic fluid flow. The piezoelectric element provides fine adjustment of the needle position, which in turn precisely modulates the fluid flow. This intermediary mechanism allows the system to achieve vibration suppression through fractional flow adjustment while maintaining a degree of isolation between the sensitive piezoelectric element and the high-energy hydraulic system.
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 solution provides improved stability control by fractionally adjusting hydraulic fluid flow, effectively suppressing vibrations and fluctuations, while being compact and reducing the overall weight and complexity of the system, ensuring reliable operation even if the augmentation mechanism fails.
Implementation Method 1
The augmentation mechanism comprises a piezoelectric element operable to increase or decrease the cross-section of the fluid flow path
Data Source
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AI summary
A stability control augmentation system and method for a flight control surface of an aircraft. The system comprises an actuator 200 operable for actuating the flight control surface, and a control valve 100 comprising a spool 140 and an integrated augmentation mechanism 130, 150. The spool 140 and the actuation mechanism 130, 150 are both moveable to open and close a fluid flow path through the control valve 100 to control the actuator 200.