Dynamic Power Margin Display for Rotary Wing Aircraft
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Solution Overview
Problem
Current dashboard instruments and aids for rotary-wing aircraft pilots do not accurately represent the real limitations of turbine engines, leading to suboptimal power usage and increased risk of accidents during maneuvers, as they rely on predetermined guaranteed minimum power rather than maximum available power.
Innovation Solution
A method and device that determine and display the current real limits of characteristic parameters, such as power and torque, in relation to the specific conditions and aging of the engines, allowing pilots to visualize the available power margin for each engine and adjust accordingly.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If predetermined guaranteed minimum power is used for power plant limitations, then safety is improved by ensuring sufficient power margin, but power plant productivity deteriorates due to suboptimal power usage
Solution Approach 1:
The power plant limitation values are made dynamic rather than static. The system continuously determines current limitation values based on real-time operating conditions (altitude, temperature, flight phase) and engine aging state, allowing the limitations to adapt to actual conditions. This enables the power plant to operate at optimal power levels for each specific situation rather than being constrained by conservative predetermined values.
Solution Approach 2:
The invention changes the parameters used for power plant limitations from fixed predetermined values to variable values that depend on multiple factors including flight phase, environmental conditions, and engine aging. By modifying these parameters dynamically, the system achieves both safety (through adequate power margins) and productivity (through optimized power usage).
2Loss of information
If multiple characteristic parameters are monitored on dashboard instruments, then operational awareness is improved, but pilot workload increases due to the need to continuously monitor and compare multiple parameters
Solution Approach 1:
The invention merges multiple characteristic parameters (power, torque, temperature, etc.) and their limitation values into a single integrated display showing the current power margin. Instead of requiring the pilot to monitor multiple separate instruments and mentally compare values, the system combines all this information into one comprehensive indicator that directly shows the available power margin, significantly reducing pilot workload while maintaining full operational awareness.
Solution Approach 2:
The system introduces an intermediary computational layer that automatically processes and compares multiple characteristic parameters against their limitations. This intermediary (the determination device) performs the complex comparisons and calculations, then presents the results in a simplified format to the pilot, acting as a mediator between the complex engine parameters and the pilot's decision-making process.
3Device complexity
If predetermined limitation values are used for power plant parameters, then device complexity is reduced by using fixed values, but measurement precision deteriorates as the values do not reflect real engine capabilities
Solution Approach 1:
The system enables the power plant to self-assess its current capabilities by automatically monitoring its own operating conditions and aging state. The determination device uses sensors and computational algorithms to continuously evaluate the engine's actual performance characteristics and determine accurate limitation values without requiring external intervention or complex manual adjustments, thus maintaining low device complexity while achieving high precision.
Solution Approach 2:
The invention implements a feedback mechanism where the system continuously monitors actual engine performance and uses this information to adjust the limitation values. The determined limitation values are fed back to the display system, creating a closed-loop system that automatically adapts to changing engine conditions. This feedback approach allows the system to maintain accurate limitation values without requiring complex manual calibration procedures.
Data Source
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AI summary
The present invention relates to a method for determining characteristic parameters of the operation of an aircraft (10) comprising a propulsion system (20) equipped with at least one engine (21, 22) and a mechanical transmission means (23), sensors and a display means (4). During this method, various information relating to said aircraft (10), its state and/or its operation and/or its environment is measured, and then, for at least one parameter Pi relating to the state and operation of said aircraft (10), a first limit value PI-lim of said parameter Pi is determined, a second value Pi_X of each parameter Pi so that said aircraft (10) can perform a predetermined maneuver X, and a third instantaneous value Pi_inst of each parameter Pi is determined.Next, we simultaneously display each first, second and third value Pi_lim, Pi_X, Pi_inst in order to highlight the relative position of a second and third value Pi_X,Pi_inst with respect to a first value Pi_lim for each parameter Pi.