Aircraft Rollover Detection Using Dynamic Critical Roll Angles
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Solution Overview
Problem
Existing aircraft systems lack effective methods to detect and prevent dynamic and static rollover conditions, particularly in rotary-wing aerial vehicles like helicopters, which can lead to potential damage and safety hazards due to improper pilot response.
Innovation Solution
A system and method utilizing onboard sensors and controllers to dynamically determine roll angles, angular rates, and critical rollover angles, generating alerts and potentially adjusting aircraft operations to prevent rollover through sensors measuring landing gear heights and processing data from various sources to predict and mitigate rollover risks.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If no rollover detection system is implemented, then the aircraft structure remains simple and operation is straightforward, but the safety against dynamic and static rollover conditions is insufficient
Solution Approach 1:
The system performs preliminary detection of rollover conditions by continuously monitoring roll angle and angular rate before actual rollover occurs. The controller calculates critical rollover angles and compares them with current aircraft state, enabling early warning and preventive action to avoid the harmful rollover event.
Solution Approach 2:
The system implements feedback by continuously measuring roll angle and angular rate, comparing these values against critical thresholds, and adjusting aircraft operations accordingly. The controller receives real-time data from sensors, processes it to determine rollover risk, and provides corrective guidance to the pilot or automated control system.
2Loss of time
If manual monitoring of roll conditions is used, then system complexity is low, but response time to critical rollover conditions is insufficient
Solution Approach 1:
The aircraft system performs self-monitoring of its own rollover risk by incorporating sensors and controllers that automatically detect and evaluate critical conditions. The system serves itself by continuously assessing its state without external intervention, enabling immediate detection and response to developing rollover situations.
Solution Approach 2:
The system replaces manual mechanical monitoring with electronic sensor-based detection and automated control. Instead of relying on pilot observation and manual assessment, the system uses electronic sensors to measure roll angle and angular rate, processes this data automatically, and provides instant electronic warning or corrective control input.
3Measurement precision
If conservative roll angle thresholds are used, then false alerts are reduced, but the system becomes less sensitive to early rollover indicators
Solution Approach 1:
The system uses dynamic thresholding where the critical rollover angle threshold is not fixed but adapts based on real-time aircraft conditions such as landing gear configuration, flight phase, and operational mode. This allows the system to maintain high detection sensitivity across varying conditions while reducing false alerts by adjusting thresholds to match actual aircraft risk profiles.
Solution Approach 2:
The system changes the parameter of critical rollover angle threshold dynamically based on aircraft state. By modifying this parameter according to landing gear position, flight phase, and other operational factors, the system achieves both high sensitivity for early detection and low false alert rate, as the threshold adapts to the specific risk context of each operational moment.
Data Source
AI summary
Systems and methods are provided for detecting and warning of aircraft rollover conditions. The systems include one or more sensors onboard the aircraft and a controller onboard the aircraft that is in operable communication with the one or more sensors. The controller is configured to, by one or more processors: receive input data from the one or more sensors and, optionally, one or more other sources, process the input data to dynamically determine a roll angle of the aircraft, an angular roll rate of the aircraft, and a critical rollover angle of the aircraft, determine whether current or potential static or dynamic rollover conditions of the aircraft exist based, at least in part, on the roll angle, the angular roll rate, and the critical rollover angle, and generate an alert in response to determining that the current or potential static or dynamic rollover conditions exist.