Integrated Control Valve for Flight 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, requiring improvements for more efficient vibration and fluctuation control.
Innovation Solution
A stability control augmentation system integrated into the control valve, featuring a spool and an augmentation mechanism that adjusts hydraulic fluid flow by modifying the cross-section of the fluid flow path, allowing for fine-tuning of actuator control and suppression of vibrations, with a piezoelectric element for fractional adjustments.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a traditional SCAS architecture is used with separate mechanical linkage and hydraulic actuators, then stability control function is provided, but the system becomes massive and complex
Solution Approach 1:
The patent merges the control valve and augmentation mechanism into a single integrated unit. The control valve includes a spool for primary control and an integrated augmentation mechanism with a separate spool that can be actuated independently to provide stability control augmentation. This consolidation eliminates the need for separate mechanical linkages and reduces system complexity while maintaining the stability control function.
Solution Approach 2:
The control valve is designed to serve multiple functions: primary actuator control through the main spool and stability control augmentation through the integrated mechanism. The single control valve component performs both control functions that would traditionally require separate systems, reducing overall system complexity while providing multi-functionality.
2Power
If the control valve cross-section is increased to allow greater fluid flow, then actuator power is improved, but the system weight increases
Solution Approach 1:
The control valve is designed with dynamic adjustability through two independently actuable spools. The main spool controls primary fluid flow while the augmentation mechanism spool can dynamically adjust the cross-section of the fluid flow path by a fraction (e.g., 6-12%) to fine-tune actuator power. This dynamic adjustment capability allows optimal power delivery without requiring a permanently oversized valve that would increase weight.
Solution Approach 2:
The system changes the fluid flow parameters dynamically through the augmentation mechanism. By adjusting the cross-section of the fluid flow path in response to detected vibrations or fluctuations, the system optimizes hydraulic fluid flow rates and pressures to the actuator, providing enhanced power when needed while avoiding the weight penalty of a continuously oversized control valve.
3Ease of operation
If mechanical linkages are used for pilot control input, then direct control is provided, but vibrations and fluctuations are not sufficiently suppressed
Solution Approach 1:
The augmentation mechanism is configured to receive feedback regarding vibrations or fluctuations of the flight control surface and automatically adjust the fluid flow path cross-section to counteract these disturbances. This feedback loop suppresses vibrations and fluctuations that would otherwise affect pilot control quality, while the mechanical linkage maintains direct pilot control input capability.
Solution Approach 2:
The integrated augmentation mechanism acts as an intermediary between the pilot's mechanical control input and the hydraulic actuator. It receives the pilot's direct control input through the mechanical linkage and simultaneously provides vibration suppression by adjusting fluid flow based on detected disturbances, thereby enhancing control quality without interfering with direct pilot input.
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
The system provides enhanced stability control by fine-tuning the actuator's hydraulic fluid flow, reducing vibrations and fluctuations in flight control surfaces, while maintaining system reliability and reducing weight and complexity.
Implementation Method 1
The piezoelectric element may be operable to expand and/or contract. The configuration of the piezoelectric element may be controlled by changing a voltage applied thereto.
Data Source
AI summary
A stability control augmentation system and method for a flight control surface of an aircraft. The system includes s an actuator operable for actuating the flight control surface, and a control valve comprising a spool and an integrated augmentation mechanism. The spool and the actuation mechanism are both moveable to open and close a fluid flow path through the control valve to control the actuator.