Aircraft Control Surface Vibration Detection During Pilot Input
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft vibration detection systems struggle to accurately differentiate between vibrations caused by faults in the control circuitry and those intentionally induced by pilot manipulation, leading to potential false detection and unnecessary system shutdowns.
Innovation Solution
An aircraft vibration detecting device and method that utilize a piloting operation determining unit to differentiate between vibrations caused by pilot manipulation and those caused by system faults, using threshold values and elapsed time measurements to determine the nature of the vibrations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If vibration detection is implemented to identify system faults, then reliability of control system is improved, but false detection occurs when pilot manipulation is misinterpreted as fault-induced vibration
Solution Approach 1:
The patent applies dynamics by making the detection thresholds adaptive rather than fixed. The first and second thresholds are dynamically adjusted based on the target value of the moving surface angle. When the target value changes (indicating pilot manipulation), the thresholds are adjusted accordingly, allowing the system to distinguish between fault-induced vibrations and pilot-induced movements. This dynamic adjustment resolves the contradiction by maintaining high detection precision while avoiding false positives.
Solution Approach 2:
The patent changes the parameters of the detection system by adjusting the thresholds based on the target value. Instead of using fixed thresholds, the system modifies the detection parameters (thresholds) according to the operational state (target value). This parameter change enables the system to adapt to different flight conditions and pilot inputs, improving measurement precision without compromising reliability.
2Device complexity
If fixed thresholds are used for vibration detection, then device complexity is reduced, but detection accuracy deteriorates when target values change due to pilot input
Solution Approach 1:
The patent implements dynamics by transitioning from fixed thresholds to dynamically adjusted thresholds. The thresholds are automatically modified based on the target value changes, which occur during pilot manipulation. This dynamic approach maintains detection accuracy across varying operational conditions without significantly increasing device complexity, as the adjustment logic is integrated into the existing control system.
Solution Approach 2:
The patent applies universality by making the detection system multi-functional. The same detection mechanism handles both fault detection and pilot manipulation identification. By adjusting thresholds based on target value changes, the system universally addresses different sources of moving surface angle variations, maintaining high detection accuracy without requiring separate detection systems for different scenarios.
Data Source
Figure 1
Figure 2
Figure 3
AI summary
An aircraft vibration detecting device (70) applicable to an aircraft (10) having a moving surface (12) to be driven by an actuator (30) includes a difference calculating unit (72) for calculating a difference (Z) between a target value (P2) of an angle of the moving surface (12) and an actual measured value of the angle of the moving surface (12), a threshold value determining unit (74) for determining whether an absolute value of the difference (Z) is equal to or greater than a threshold value, and a vibration determining unit (82) for determining that the moving surface (12) is vibrating if the absolute value of the difference (Z) is equal to or greater than the threshold value.