Wing Flap Hydraulic Damping for Aerodynamic Flutter Mitigation
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Solution Overview
Problem
Aircraft wing flaps experience undesirable levels of aerodynamic flutter due to actuation mechanism failures, leading to increased cost, weight, and reduced performance when traditional mitigation techniques like using thicker materials or shorter dimensions are employed.
Innovation Solution
Implement a damper system comprising a piston rod, chambers, and a hydraulic fluid system to dampen flap movements, including pressure transducers, relief valves, and anti-cavitation valves to mitigate flutter without increasing weight or reducing performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional mitigation techniques like using thicker materials or shorter dimensions are employed to reduce aerodynamic flutter, then flutter resistance is improved, but weight increases and performance is reduced
Solution Approach 1:
The patent employs a hydraulic damper system connected to the flap mechanism. The damper contains hydraulic fluid that flows through restricted passages, creating damping forces that counteract aerodynamic flutter vibrations. This hydraulic approach provides effective flutter mitigation without requiring increases in structural material thickness or weight
Solution Approach 2:
The patent changes the physical state and flow parameters of hydraulic fluid within the damper system. By controlling fluid viscosity, flow rate, and pressure through adjustable valves and restricted passages, the system dynamically adjusts damping characteristics to counteract flutter across different flight conditions, achieving vibration control without structural modifications
2Reliability
If traditional mitigation techniques like using thicker materials or shorter dimensions are employed to reduce aerodynamic flutter, then flutter resistance is improved, but manufacturing cost increases
Solution Approach 1:
The hydraulic damper system provides a cost-effective alternative to expensive structural modifications. By using commercially available hydraulic components and standard manufacturing processes for the damper assembly, the solution avoids the high costs associated with redesigning and manufacturing thicker or shorter flap structures
Solution Approach 2:
The damper acts as an intermediary device between the flap structure and the actuation mechanism. This separate, modular component handles the flutter mitigation function without requiring modifications to the primary flap structure, simplifying manufacturing and reducing overall system cost
3Reliability
If a damper system is implemented to reduce aerodynamic flutter, then flutter is mitigated, but device complexity increases
Solution Approach 1:
The damper system is integrated with the existing actuation mechanism by coupling it to the actuator and flap structure. This merging approach allows the damper to leverage existing mechanical connections and hydraulic infrastructure, minimizing additional complexity while achieving effective flutter mitigation
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 damper system effectively reduces aerodynamic flutter while maintaining aircraft performance and reducing costs by avoiding the need for thicker materials or additional supports, thus enhancing fuel efficiency and lift capabilities.
Implementation Method 1
a damper disposed in the fairing, the damper coupled to and extending between the wing and the flap, the damper comprising: a piston rod having a first end and a second end located opposite the first end, the first end coupled to the wing, the second end coupled to the flap; a first gland retainer, a first gland, a second gland retainer, and a second gland; a cylinder having a first chamber and a second chamber
Implementation Method 2
damping movement of the flap to mitigate aerodynamic flutter of the flap
Implementation Method 3
The housing comprises a first pressure transducer, a first relief check valve, and a first anti-cavitation valve, fluidly coupled to the first side of the rod head in the second chamber; a second pressure transducer, a second relief check valve, and a second anti-cavitation valve, fluidly coupled to the second side of the rod head in the second chamber
Implementation Method 4
the first and second relief check valves are configured to open when a pressure within the second chamber exceeds the thresholds of the first and second pressure transducers
Implementation Method 5
the first anti-cavitation valve and the second anti-cavitation valve are configured to mitigate cavitation while the pressurized hydraulic fluid is being supplied to the damper
Data Source
Figure 1
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AI summary
Example methods and apparatus for mitigating aerodynamic flutter of aircraft (100) wing (104, 106) flaps (112) are disclosed. An example apparatus includes a fairing (200), an actuator (400), and a damper (600, 1300, 1400). The fairing (200) is located on a bottom side (210, 212) of a wing (104, 106) of an aircraft (100). The actuator (400) is disposed in the fairing (200). The actuator (400) is coupled to and extends between the wing (104, 106) and a flap (112, 114) of the wing (104, 106). The damper (600, 1300, 1400) is disposed in the fairing (200). The damper (600, 1300, 1400) is coupled to and extends between the fixed wing (104, 106) and the moveable flap (112, 114).