Aircraft Steering Monitoring with Adaptive Control Limits
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft heading control systems are limited by fixed angular ranges, which restrict their effectiveness in maintaining stable steering due to unpredictable component wear and external influences, potentially masking abnormal conditions until maintenance intervals.
Innovation Solution
A monitoring system that determines dynamic operating characteristics based on aircraft and environmental conditions, comparing expected and actual steering system performance to issue alerts and adjust control parameters, thereby expanding the effective range of steering control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If fixed angular ranges are used for heading control systems, then the system structure is simple and reliable, but the effective range of steering control is limited and abnormal conditions may be masked
Solution Approach 1:
The patent applies dynamics by transitioning from fixed angular ranges to dynamic adaptive ranges. The heading control system continuously adjusts the angular range based on real-time monitoring of aircraft conditions ( tyre pressure, engine thrust, brake performance) and environmental factors (wind, runway surface). This allows the control system to adapt its authority to match actual aircraft health and operational conditions, expanding the effective steering control range while maintaining safety through context-aware limitations.
Solution Approach 2:
The patent implements parameter changes by modifying the angular range parameter dynamically. Instead of using a static angular range, the system changes this parameter based on monitored conditions such as component wear indicators, environmental factors, and aircraft performance data. The controller adjusts the angular range parameter in real-time, allowing the heading control system to operate effectively across varying conditions while automatically detecting when parameters indicate abnormal aircraft states.
2Reliability
If the angular range is limited to avoid masking component wear, then abnormal conditions are detected, but the range over which heading control is effective is reduced
Solution Approach 1:
The patent applies local quality by implementing different angular range limitations for different segments of the operational envelope. Rather than applying a uniform angular range limit across all conditions, the system tailors the angular range to specific local conditions such as tyre pressure status, engine performance, brake health, and environmental factors. This allows the heading control to be highly effective in normal conditions while maintaining detection capability for abnormal conditions through localized monitoring and adaptive adjustment.
Solution Approach 2:
The patent implements feedback through continuous monitoring of aircraft conditions and environmental factors, with the controller using this information to dynamically adjust the angular range. The system receives feedback from sensors monitoring tyre pressure, engine thrust, brake performance, and other parameters, then adjusts the heading control authority accordingly. This closed-loop feedback mechanism ensures that the angular range is optimized for both effectiveness and abnormal condition detection based on real-time aircraft state.
3Ease of operation
If fixed angular ranges are used, then the control system is easy to operate, but it cannot compensate for unpredictable component wear between maintenance intervals
Solution Approach 1:
The patent applies self-service by enabling the heading control system to automatically adjust its own angular range based on monitored aircraft conditions. The system performs self-diagnosis through continuous monitoring of component performance indicators and automatically compensates for detected degradation without requiring manual intervention. This self-adjusting capability maintains ease of operation while significantly improving reliability by adapting to component wear between maintenance intervals.
Solution Approach 2:
The patent implements preliminary action by proactively adjusting the angular range before component failure occurs. The system continuously monitors aircraft conditions and preemptively modifies the heading control authority in response to detected degradation trends. This preliminary adjustment allows the system to compensate for component wear before it leads to failure, maintaining reliable operation while requiring minimal crew intervention.
Data Source
Figure 1
Figure 2~3
Figure 4
AI summary
Disclosed is a monitoring system (300) for an aircraft (100). The monitoring system comprises a controller (301) to determine, based on one or more conditions, one or more expected operating characteristics of a steering system of the aircraft. The one or more conditions comprise one or more aircraft conditions indicative of an internal condition of the aircraft and/or one or more external conditions indicative of an external influence on the aircraft. The controller is to compare the one or more expected operating characteristics with the one or more actual operating characteristics. The controller is configured to determine, based on the compare, whether to issue a signal indicating a condition of the aircraft. Also disclosed is an avionics system (3000) comprising the monitoring system, an aircraft comprising the monitoring system or the avionics system, and a method (600) of monitoring an aircraft.