Integrated Control Valve for Aircraft Flight Surface Stability
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Solution Overview
Problem
Existing Stability Control Augmentation Systems (SCAS) for aircraft flight control surfaces are bulky and complex, necessitating improvements for reduced weight and complexity.
Innovation Solution
An integrated stability control augmentation system for flight control surfaces, incorporating a control valve with a spool and augmentation mechanism, utilizing a rocking pin that rotates about two points to adjust hydraulic fluid flow, and a piezoelectric element to fine-tune fluid flow through the control valve, enhancing stability control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the SCAS is provided as a separate system outside the control valve, then the stability control function is achieved, but the system becomes massive and complex
Solution Approach 1:
The patent integrates the augmentation mechanism directly into the control valve assembly, combining two previously separate systems (control valve and SCAS) into a single unified component. This merging eliminates the need for separate mounting brackets, external linkages, and independent adjustment mechanisms, thereby achieving stability control functionality while reducing overall system complexity and mass.
2Device complexity
If the augmentation mechanism is integrated into the control valve, then the weight and complexity are reduced, but the control precision must be maintained
Solution Approach 1:
The augmentation mechanism is nested within the control valve structure, with the augmentation spool positioned inside the control valve body. This nested arrangement allows the augmentation mechanism to operate within the existing control valve footprint, maintaining compact dimensions while preserving the precision control capabilities of both the original spool and the augmentation spool through coordinated operation.
3Ease of operation
If the spool provides most of the control over the actuator, then the control range is sufficient, but fine-tuning capability is limited
Solution Approach 1:
The augmentation mechanism provides a fractional adjustment (excessive action) to the control valve output, fine-tuning the fluid flow by a small percentage (e.g., 6-12%) of the total flow range. This partial action叠加 on top of the spool's primary control enables precise vibration suppression without compromising the overall control range established by the spool.
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 fine-tuned stability control with reduced weight and complexity by integrating the augmentation mechanism into the control valve, allowing for efficient suppression of vibrations and fluctuations in flight control surfaces.
Implementation Method 1
a piezoelectric element to fine-tune fluid flow through the control valve
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.