Rotary Wing Aircraft Instantaneous Mass Estimation
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Solution Overview
Problem
Current methods for estimating the mass of rotary wing aircraft are inaccurate and do not account for fuel consumption during flight, leading to suboptimal performance and potential safety risks due to overestimation or underestimation of the aircraft's mass.
Innovation Solution
A method that measures flight, power, and atmospheric characteristics to determine the instantaneous mass of the aircraft using performance curves and sensors, allowing for accurate calculation of the mass during different flight stages, including hovering, altitude-changing, and level flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the aircraft mass is estimated before takeoff and kept constant throughout flight, then the estimation process is simple, but the accuracy deteriorates as fuel is consumed and the aircraft mass decreases
Solution Approach 1:
The patent applies dynamics by transitioning from a static mass estimation (constant before flight) to a dynamic mass estimation that continuously updates during flight. The system dynamically adapts the mass value based on real-time fuel consumption measurements, ensuring the mass estimate remains accurate throughout the flight lifecycle as fuel is depleted.
Solution Approach 2:
The patent implements feedback by continuously measuring actual fuel consumption during flight and using this information to update the aircraft mass estimate. The system feeds back the difference between expected and actual fuel consumption to refine the mass calculation, creating a closed-loop system that maintains accuracy without requiring complex real-time measurements of all aircraft components.
2Reliability
If safety margins are applied to the mass estimation, then the reliability of the estimation is improved, but the accuracy deteriorates due to overestimation
Solution Approach 1:
The patent applies partial action by selectively applying safety margins only to specific components of the mass estimation (such as payload and cargo) while using precise real-time measurements for other components (such as fuel consumption and basic aircraft weight). This approach maintains sufficient safety margins where needed while avoiding unnecessary overestimation that would degrade accuracy.
3Reliability
If the aircraft mass is overestimated, then the safety is improved, but the flight performance optimization deteriorates due to reduced flight envelope
Solution Approach 1:
The patent applies dynamics by enabling the aircraft mass estimate to dynamically adapt during flight based on actual fuel consumption. This dynamic adjustment allows the flight performance parameters (such as maximum speed, range, and maneuverability) to be accurately optimized in real-time, preventing the degradation of flight envelope that would result from static overestimation, while still maintaining appropriate safety margins.
4Measurement precision
If multiple sensors and performance curves are used to measure flight characteristics, then the measurement precision is improved, but the device complexity increases
Solution Approach 1:
The patent applies segmentation by dividing the mass estimation problem into distinct measurable components: basic aircraft weight, fuel mass (separately measuring fuel volume and using density), payload, and cargo. Each component is measured or calculated independently using appropriate sensors and methods, then summed to obtain the total mass. This segmentation allows high precision without requiring a single complex measurement system.
Data Source
AI summary
A method and a device for estimating the instantaneous mass of a rotary wing aircraft, the aircraft having a power plant driving at least one main rotor and an anti-torque rotor in rotation, and also having a plurality of sensors. The method uses functional characteristics and flight characteristics of the aircraft, atmospheric characteristics, and performance curves for the aircraft to determine the measured instantaneous mass Mm of the aircraft. Furthermore, the method makes it possible to consolidate the measured instantaneous mass Mm of the aircraft by comparing it in arithmetical or statistical manner during a flight of the aircraft with a calculated instantaneous mass Mc determined from the variation in the quantity of fuel present in the aircraft.