Aircraft Airspeed Estimation Using Weather Buffer Model
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Solution Overview
Problem
Existing airspeed estimation systems, particularly those relying on pitot probes, face inaccuracies during extreme flight conditions due to factors like contamination, damage, or maintenance issues, and struggle to accurately calculate airspeed when aircraft operate under unsteady or highly dynamic conditions.
Innovation Solution
A system utilizing processors and memory to determine model-based and bridge-based dynamic pressures, assessing aircraft steadiness through angles of attack, sideslip, and bank angles, and estimating airspeed parameters using a weather buffer model that transitions between steady and extreme flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a pitot probe is used to measure airspeed, then airspeed measurement is obtained under normal conditions, but measurement accuracy deteriorates during extreme flight conditions due to contamination, damage, or maintenance issues
Solution Approach 1:
The patent introduces an intermediary computational model that processes multiple sensor inputs (accelerometers, GPS, barometric pressure, temperature sensors) to calculate airspeed when the pitot probe is unreliable. This intermediary system acts as a backup calculation path that activates during extreme conditions, providing continuous airspeed estimation without direct dependence on the contaminated or damaged pitot probe.
Solution Approach 2:
The system changes the measurement parameters by switching from direct pitot probe pressure differential measurement to an indirect calculation method using acceleration, position, and environmental parameters. The computational model transforms these alternative parameters into airspeed estimates, effectively changing how airspeed is obtained when traditional measurement fails.
2Stability of the object's composition
If airspeed estimate is frozen during extreme flight conditions, then calculation stability is maintained, but measurement accuracy deteriorates over time
Solution Approach 1:
The patent implements a dynamic estimation approach where the airspeed calculation continuously adapts to changing flight conditions through the computational model. Rather than freezing the estimate, the system dynamically updates airspeed calculations using real-time sensor data from accelerometers, GPS, and environmental sensors, allowing the estimation to track actual airspeed changes during extreme maneuvers while maintaining numerical stability through proper filtering and integration.
3Device complexity
If traditional airspeed calculation methods are used, then system simplicity is maintained, but adaptability to extreme flight conditions deteriorates
Solution Approach 1:
The computational model serves multiple functions: it provides airspeed estimation during normal flight as a backup to pitot probes, activates as the primary measurement method during extreme conditions when pitot probes fail, and continuously validates pitot probe readings by comparing against its own calculations. This multi-functional approach allows a single system to handle both normal and extreme flight conditions effectively.
Data Source
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AI summary
A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprising a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a model based dynamic pressure based on the operating parameters. The model based dynamic pressure is estimated based on steady flight conditions of the aircraft. The system is further caused to determine a bridge based dynamic pressure based on at least a temperature deviation and an inertial speed vector. The bridge based dynamic pressure is estimated for extreme flight conditions of the aircraft.