Rotorcraft Engine Failure Simulation via Mass-Adaptive Power Capping
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Solution Overview
Problem
Current methods for simulating engine failure in multi-engine rotorcrafts are not optimal, especially when the aircraft is lighter than its maximum authorized mass, as they do not accurately replicate the conditions of an engine failure at maximum mass, affecting the training effectiveness for pilots.
Innovation Solution
A method that uses a controller to determine the initial mass of the rotorcraft, comparing it to the maximum mass, and adjusts the control restriction values of the engines to simulate an engine failure by capping engine torque or power, ensuring the weight/power ratio is equivalent to that at maximum mass, thereby optimizing training by mimicking the most unfavorable conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If training mode is activated on a rotorcraft with mass far lower than maximum mass, then the training setup is simpler, but the training effectiveness is reduced because the power required is less than the maximum power of the emergency rating
Solution Approach 1:
The controller dynamically adjusts the control restriction values of the engines based on the determined mass of the rotorcraft. When the rotorcraft mass is lower than maximum mass, the controller reduces the control restriction values proportionally to maintain equivalent weight/power ratio conditions. This allows training to be conducted at any mass while preserving training effectiveness by adapting engine power limitations to match the actual mass conditions.
2Reliability
If extra ballast is added to the rotorcraft to increase mass, then the training conditions better replicate maximum mass scenarios, but the device complexity and operational restrictions increase
Solution Approach 1:
The patent replaces the mechanical approach of adding physical ballast with an electronic control system. The controller determines the actual mass of the rotorcraft and automatically calculates and applies appropriate control restriction values to the engines. This electronic substitution eliminates the need for physical ballast while achieving the same training objective of replicating maximum mass emergency conditions.
3Measurement precision
If control restriction values are adjusted based on rotorcraft mass, then training accuracy is improved, but the control system complexity increases
Solution Approach 1:
The controller automatically determines the mass of the rotorcraft and autonomously calculates the appropriate control restriction values without requiring manual intervention. The system self-adjusts the engine power limitations based on the actual mass conditions, eliminating the need for complex manual setup procedures while maintaining high training accuracy.
Data Source
AI summary
A method for simulating an engine failure on a rotorcraft comprising several engines for setting a rotary wing in motion. The method comprises a training mode that comprises controlling each engine with a controller in order to simulate an engine failure, this control comprising limiting the power of each engine to a respective control restriction value. The training mode comprises the following steps: i) determining, with the controller, a maximum mass at least as a function of external conditions, and an initial mass of the rotorcraft at least as a function of an unladen mass of the rotorcraft, a mass of a crew present in the rotorcraft, and an estimated mass of fuel on-board; ii) comparing, with the controller, the initial mass with the maximum mass; and iii) determining, with the controller, each control restriction value as a function of the comparison.