Flutter Control Actuator Using Residual Angular Rate Feedback
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Solution Overview
Problem
Current aircraft flight control systems face challenges in managing flutter and high-frequency vibrations at control surfaces, leading to increased weight and fuel consumption due to the need for larger surfaces and actuators to counteract buffeting effects.
Innovation Solution
A method and apparatus that utilize rate sensors to estimate angular rates of control surfaces and base members relative to an inertial frame, calculating a residual angular rate to control vibrations by generating signals that adjust the position of the control surfaces, thereby reducing flutter and vibrations without the need for excessive additional structure or actuation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If large additional aircraft surfaces and structures are utilized to counteract buffeting effects, then flutter control capability is improved, but aircraft weight increases
Solution Approach 1:
The system uses rate sensors to continuously monitor the actual angular rate of the control surface and feeds this information back to the controller. The controller compares the actual angular rate with the commanded angular rate and adjusts the actuator output accordingly, creating a closed-loop feedback system that actively counteracts flutter without requiring additional structural mass
Solution Approach 2:
The invention replaces the need for large mechanical structures and additional actuators with an electronic control system. By using sensors to detect flutter conditions and electronic control to adjust the control surface position in real-time, the system achieves flutter suppression without the weight penalty of larger mechanical components
2Reliability
If large additional aircraft surfaces and structures are utilized to counteract buffeting effects, then flutter control capability is improved, but fuel consumption increases
Solution Approach 1:
The closed-loop feedback system continuously monitors and adjusts control surface position to minimize flutter, allowing the aircraft to operate more efficiently. By preventing flutter through active control rather than relying on oversized structures, the system reduces energy consumption and fuel burn
Solution Approach 2:
The system dynamically changes the operational parameters of the control surface by adjusting its position and angular rate in real-time based on detected flutter conditions. This dynamic parameter adjustment allows the control surface to operate within optimal ranges, reducing energy consumption compared to static oversized structures
3Manufacturing precision
If rate sensors and control systems are used to control angular parameters, then vibration control precision is improved, but device complexity increases
Solution Approach 1:
The system uses rate sensors to measure the actual angular rate of the control surface and feeds this information back to the controller. The controller compares the actual angular rate with the commanded angular rate and adjusts the actuator output accordingly, creating a closed-loop feedback system that achieves precise vibration control
Solution Approach 2:
The invention replaces complex mechanical vibration control mechanisms with an electronic control system. By using sensors to detect vibration conditions and electronic control to adjust the control surface, the system achieves precise vibration suppression with simpler overall architecture compared to mechanical alternatives
Data Source
AI summary
A method and apparatus for controlling an angular parameter between a base member and a control surface of an aircraft is disclosed. An estimate is obtained of an angular rate of the control surface with respect to an inertial frame of the aircraft using a rate sensor. A residual angular rate that is a difference between a commanded angular rate and the estimate of the angular rate of the control surface is determined. The residual angular rate is used to control the angular parameter of the control surface or the angular parameter of the base member.