Rotorcraft Bearing Temperature and Load Indicator
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Solution Overview
Problem
Conventional flight envelope limitations in aircraft are overly conservative, reducing operational capability and difficult to apply during high-workload operations like combat maneuvering or terrain following, and strain gages are unreliable and costly for monitoring critical component loads and temperatures in rotorcrafts.
Innovation Solution
A feathering, flapping, and rotor loads indicator system that calculates and dynamically displays the temperature and load of critical rotor assembly components using flight control parameters, providing pilots with real-time feedback to avoid critical conditions and expand the aircraft's operational envelope.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional flight envelope limitations are used, then flight safety is maintained, but operational capability is reduced
Solution Approach 1:
The system continuously monitors rotorcraft component status through strain gages and displays real-time feedback to the pilot via a visual indicator. This feedback mechanism allows the pilot to understand current component conditions and adjust operations accordingly, enabling safer expansion of the flight envelope beyond conservative limitations.
Solution Approach 2:
The patent replaces complex mechanical monitoring systems with a simplified visual indicator driven by a single critical component's strain gage output. This substitution provides sufficient information to the pilot without the complexity of multiple dedicated instrumentation systems, reducing cost and maintenance requirements while maintaining effectiveness.
2Loss of information
If strain gages are used to monitor critical component loads, then real-time component status information is provided, but system complexity and maintenance cost increase
Solution Approach 1:
The visual indicator serves multiple functions: it displays component status information, provides flight safety monitoring, and guides pilot decision-making. By making the indicator universal and multi-functional, the system reduces the need for separate dedicated instrumentation for each function, thereby reducing overall system complexity.
Solution Approach 2:
The patent extracts the essential information function from complex multi-parameter monitoring systems and concentrates it into a single visual indicator driven by one critical strain gage. This extraction provides sufficient component status information to the pilot while eliminating the complexity of monitoring and displaying multiple parameters simultaneously.
3Reliability
If multiple dedicated instrumentation systems are installed, then comprehensive component monitoring is achieved, but maintenance cost increases
Solution Approach 1:
The patent extracts the essential monitoring function from complex multi-system instrumentation and concentrates it into a single visual indicator driven by one critical component's strain gage. This extraction maintains reliable component monitoring while significantly reducing the number of systems requiring maintenance, thereby lowering maintenance costs.
Solution Approach 2:
The system uses a simple, inexpensive visual indicator that can be easily replaced if needed, rather than investing in expensive, complex dedicated instrumentation systems. This approach prioritizes cost-effectiveness while maintaining sufficient monitoring reliability through the use of a single critical strain gage and simple display mechanism.
Data Source
AI summary
A feathering, flapping and rotor loads indicator for use in a rotorcraft includes a calculation unit configured to calculate (a) a current temperature of a bearing of the rotor assembly using a first calculation model, (b) a projected temperature of the bearing using the first calculation model and (c) a load exerted on a selected component of the rotor assembly using a second calculation model, the first and second calculation models adapted to calculate, respectively, the projected and the current temperatures of the bearing and the load exerted on the selected component based on flight control parameters; and a display unit configured to display on a common scale a movable indicator, the movable indicator being driven by the highest value between the projected temperature of the bearing and the load exerted on the selected component. The display unit displays another movable indicator driven by the current temperature of the bearing.