Aircraft Modal Suppression with Span-Wise Gust Segmentation
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Solution Overview
Problem
Existing aircraft modal suppression systems fail to accurately capture the effects of non-uniform wind gusts, leading to inadequate performance in reducing aircraft vibrations during turbulence, as they rely on uniform gust models that do not accurately represent natural wind patterns.
Innovation Solution
The system utilizes a non-uniform gust model to generate observers from on-board inertial sensor signals, which are used to determine control law commands for control surfaces like ailerons and flaperons, effectively reducing vibrations induced by both uniform and non-uniform lateral and vertical wind gusts by segmenting the airframe into span-wise gust segments and applying operations such as addition and filtering.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If uniform gust models are used in modal suppression control laws, then the system design is simplified, but the accuracy of capturing natural wind gust effects is insufficient
Solution Approach 1:
The airframe is segmented into multiple span-wise gust segments, with each segment having its own observer that processes sensor signals independently. This segmentation allows the system to capture non-uniform gust effects across different portions of the aircraft while maintaining modular, manageable control design.
Solution Approach 2:
The system transitions from a single uniform gust model to a multi-dimensional approach by dividing the airframe into multiple span-wise segments along the vertical dimension. Each segment operates in its own dimensional space, allowing independent estimation and control of local gust effects.
2Reliability
If multiple span-wise gust segments are used to capture non-uniform gusts, then the accuracy of vibration reduction is improved, but the system complexity increases
Solution Approach 1:
The control law commands from multiple span-wise segments are merged and applied to control surfaces. This combining approach integrates the benefits of multiple localized observers while utilizing the existing control surface architecture, avoiding the need for separate control systems for each segment.
Solution Approach 2:
The segmented observer system is designed to work with existing control surfaces (aileron, flaperon, rudder) that serve multiple functions. The control law can adaptively distribute commands across these universal control elements based on the specific vibration modes and gust conditions detected.
3Ease of manufacture
If existing sensors and control surfaces are utilized, then cost-effectiveness is improved, but the system may lack optimal performance compared to dedicated components
Solution Approach 1:
The system is designed to utilize existing onboard inertial sensors and control surfaces already present on the aircraft, making the existing components serve the additional function of modal suppression. This self-service approach eliminates the need for dedicated expensive sensors and actuators while achieving effective vibration reduction.
Data Source
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AI summary
Systems and methods of aircraft modal suppression informed by an underlying non-uniform vertical turbulence model and uniform lateral turbulence model. The systems and methods include receiving a plurality of signals from on-board inertial sensors of an aircraft, utilizing the plurality of signals to generate a plurality of observers, utilizing the observers to determine a control law command for controlling one or more control surfaces of the aircraft, and moving the one or more control surfaces of the aircraft in accordance with the determined control law command such that lateral mode vibrations of the aircraft are diminished.