Airspeed Determination via Synthetic Air Data and Voting Logic
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Solution Overview
Problem
Aircraft pitot-static systems are prone to failures due to extreme in-flight conditions, leading to incorrect airspeed readings, which can be catastrophic as they are critical for pilot decisions and autopilot actions.
Innovation Solution
The method involves determining aircraft airspeed using synthetic air data parameters derived from aircraft parameters and standard values, independent of pitot-static systems, through iterative calculations and voting logic to validate air data sources, ensuring accurate airspeed determination even in the event of pitot-tube failures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If pitot-static systems are used to determine airspeed, then airspeed measurement is achieved, but reliability deteriorates due to failures from extreme in-flight conditions
Solution Approach 1:
The patent creates a synthetic airspeed parameter that copies the functional output of the pitot-static system but derives it through an entirely different computational path using aircraft performance models, sensor fusion, and iterative calculations based on weight, drag, thrust, and atmospheric conditions, thereby providing a redundant measurement that is immune to pitot-tube failures
Solution Approach 2:
The patent replaces the mechanical pitot-static measurement system with a computational model-based system that uses digital calculations, sensor data fusion, and iterative algorithms to determine airspeed, substituting physical pressure measurement with mathematical modeling and computational derivation
2Reliability
If synthetic air data parameters are used to determine airspeed independently of pitot-static systems, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent creates a multi-functional computational framework that simultaneously determines multiple flight parameters (airspeed, Mach number, altitude, weight, drag) using a unified set of equations and sensor inputs, allowing the same computational infrastructure to serve multiple aviation functions rather than requiring separate dedicated systems for each parameter
Solution Approach 2:
The patent employs iterative feedback loops where the computed airspeed and Mach number are continuously refined by comparing calculated values with measured values from available sensors, adjusting the computational model parameters until convergence is achieved, thereby automatically improving accuracy without requiring manual intervention
Data Source
AI summary
Embodiments of a method to determine airspeed for aircraft include determining critical air data parameters without the use of pitot-static systems. Airspeed may be determined by iteratively repeating the method until converging on a stable airspeed value that differs from a previous airspeed value by less than a predetermined threshold. Airspeed may be determined by modeling aircraft lift and repeatedly updating dynamic pressure to converge on an airspeed based on the balance between aircraft lift and weight. Airspeed may be determined based on predetermined relationships between a horizontal control surface position and dynamic pressure. A voting logic method validates or invalidates airspeeds from dissimilar sources, including airspeeds determined using the methods described herein and conventional pitot-static systems.