Aerodynamic Angle Estimation Using Inertial and Airspeed Data
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Solution Overview
Problem
Existing methods for estimating the aerodynamic angles of a flying body, such as aircraft, require multiple sensors and calibration procedures, which can be complex and prone to errors, especially in real-time applications.
Innovation Solution
A computer-based estimation method that uses direct or indirect measurements of the time derivative of airspeed and inertial acceleration projections to calculate the angles of attack and sideslip, eliminating the need for multiple sensors and calibration.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If multiple sensors (flow angle vanes, pressure sensors, multifunction probe) are used to detect aerodynamic angles, then measurement precision is improved, but device complexity increases and maintenance requirements increase
Solution Approach 1:
The patent creates a virtual sensor system that computes aerodynamic angles (flow angle, angle of attack, sideslip angle) by processing data from existing flight parameters (accelerometer data, airspeed, altitude) rather than using physical flow angle sensors. This virtual copying approach eliminates the need for complex physical sensing hardware while providing the required measurement precision.
Solution Approach 2:
The patent replaces mechanical flow angle sensors with a computational method that uses mathematical models and processing of data from standard flight instruments. This substitution eliminates moving mechanical parts that require maintenance while achieving the same measurement objectives through software-based angle computation.
2Measurement precision
If flow angle vanes and pressure sensors are installed to measure aerodynamic angles, then measurement precision is improved, but ease of operation deteriorates due to calibration requirements and maintenance needs
Solution Approach 1:
The system uses virtual sensors that compute aerodynamic angles from standard flight data rather than relying on physical sensors that require calibration. This computational approach copies the function of physical sensors without the associated calibration and maintenance requirements.
Solution Approach 2:
The virtual sensor system automatically computes aerodynamic angles using real-time flight data from existing instruments without requiring external calibration procedures. The system serves itself by continuously calculating angles based on current flight conditions, eliminating the need for periodic maintenance and calibration operations.
3Device complexity
If analytical estimators or virtual sensors are used to estimate aerodynamic angles, then device complexity is reduced, but measurement precision may deteriorate without proper calibration
Solution Approach 1:
The patent replaces the need for calibration-based virtual sensor systems with a direct computational approach that calculates aerodynamic angles from fundamental flight parameters using mathematical relationships. This substitution eliminates the calibration step that introduces potential errors in other virtual sensor methods.
Solution Approach 2:
The system performs preliminary computation of aerodynamic angles using established mathematical models that relate flight parameters to angle measurements. By pre-establishing the computational framework based on aerodynamic principles, the system ensures accurate measurements without requiring flight-specific calibration data.
Data Source
AI summary
A computer implemented method for estimating angles of attack and/or an angle of sideslip of a flying body includes the steps of: providing data or measurements representative of a time derivative of a module of a speed of the flying body with respect to an air; providing data or measurements representative of corresponding projections of coordinate accelerations on a Cartesian reference frame fixed to the flying body; and calculating the angles of attack and/or the sideslip on a basis of an mathematical relationship of the angles of attack and the sideslip with the coordinate accelerations and the time derivative of the module of the speed of the flying body with respect to the air.