Aircraft Airspeed Estimation via Static Pressure and Mach Number Weighting

The patent changes the parameter used for airspeed estimation from relying solely on the lift equation (which is accurate only at low speeds) to using static pressure measurements that vary with Mach number. This parameter change enables accurate airspeed estimation across the entire flight envelope, including cruising speeds where the lift equation alone fails.

The patent creates a universal airspeed estimation method that works across all flight conditions by combining multiple approaches: using static pressure sensors positioned to detect Mach number effects, applying corrections based on flight envelope parameters, and integrating these with traditional estimation methods. This multi-functional approach ensures accuracy whether the aircraft is at low speed, high speed, or any intermediate condition.

The patent extracts the airspeed measurement function from the Pitot probe system entirely, replacing it with a method based on static pressure sensors. By removing the dependency on Pitot probes and their vulnerable ducting system, the invention eliminates the problem of external elements blocking the ducts while maintaining airspeed measurement capability through alternative physical principles.

The patent introduces static pressure sensors as an intermediary measurement device that indirectly determines airspeed through Mach number relationships rather than directly measuring dynamic pressure like Pitot probes. This intermediary approach uses pressure sensors positioned on the fuselage surface, which are not susceptible to duct blocking, thereby improving reliability while still enabling airspeed estimation.

The patent implements a dynamic estimation system that automatically adapts its method and parameters based on the current flight condition. The system uses flight envelope parameters (Mach number, altitude, speed) to dynamically select and weight different estimation approaches, ensuring optimal accuracy for the current operating regime without requiring manual intervention or complex fixed architecture.

The patent segments the flight envelope into different operational regions (low speed, high speed, cruising) and applies optimized estimation methods for each segment. By dividing the overall estimation problem into condition-specific segments, the system achieves high accuracy across the entire envelope while maintaining relatively simple individual method implementations that can be selectively activated.