Tiltrotor Pylon Fault Management Synchronization
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Solution Overview
Problem
Tiltrotor aircraft face the challenge of maintaining synchronized pylon positions during conversion between helicopter and airplane modes, as differences in pylon positions or movement rates can lead to faults, potentially causing loss of the aircraft if not detected and corrected.
Innovation Solution
A system and method that monitor the difference between commanded and actual pylon positions, declaring a fault if exceeding a preset limit, and adjusting the control logic to ensure the 'good' pylon follows the 'bad' pylon's position to maintain synchronization, thereby preventing crashes and enabling safe emergency landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the pylon position monitoring system is implemented to detect faults, then the safety and reliability of the aircraft is improved, but the system complexity and computational load increase
Solution Approach 1:
The system performs preliminary fault detection by continuously monitoring pylon positions and comparing them against commanded positions before faults can develop into dangerous situations. The fault detection logic proactively identifies when a pylon is not moving sufficiently relative to its commanded position, allowing early intervention and preventing catastrophic failures.
Solution Approach 2:
The system implements feedback control by continuously measuring actual pylon positions, comparing them with commanded positions, and using this information to detect faults. The feedback mechanism provides real-time information about pylon behavior, enabling the control system to respond to deviations and maintain safe operation.
2Productivity
If the control logic is adjusted to synchronize pylon positions by having the good pylon follow the bad pylon, then the operational continuity is improved, but the conversion performance and precision deteriorate
Solution Approach 1:
The system applies partial synchronization control where only the necessary degree of synchronization is enforced to maintain safe operation. When a fault is detected, the good pylon is commanded to match the bad pylon's position to the extent needed to prevent dangerous asymmetry, rather than forcing complete synchronization that would prevent operation entirely.
Solution Approach 2:
The control system dynamically adjusts its behavior based on fault conditions. During normal operation, both pylons follow independent commanded positions for optimal performance. When a fault is detected, the system dynamically switches to a synchronized mode where the good pylon follows the bad pylon, allowing the aircraft to continue operating safely despite the fault.
Data Source
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AI summary
The difference between a first position (110) of a first pylon of a tiltrotor aircraft and a second position (120) of a second pylon of the aircraft is prevented from becoming too large. An actuator position error (140) for the first pylon is calculated from a difference between the first position (110) and a commanded first position (150) of the first pylon. An actuator position error (160) for the second pylon is calculated from a difference between the second position (120) and a commanded second position (170) of the second pylon. An absolute value (165) of the actuator position error for the first pylon is compared (135) to the preset limit (130). If the absolute value of the actuator position error for the first pylon is greater than or equal to a preset limit, the actuator position error for the second pylon is calculated from the difference between the first position and the second position.