Aircraft Static-Pressure Probe Error Detection via Theoretical Differential
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Solution Overview
Problem
Existing methods for detecting errors in static-pressure measurements of aircraft static-pressure probes are not fine enough, as they rely on a predefined differential threshold, which may not capture subtle measurement errors.
Innovation Solution
A method involving electronic circuitry that computes the right-left static-pressure differential from actual measurements and compares it with a theoretically calculated differential, using functions or trained neural networks, to generate a warning when the difference exceeds a predetermined threshold.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a predefined differential threshold (e.g., 30 millibars) is used to detect static-pressure measurement errors, then measurement errors can be detected, but the detection precision is insufficient and cannot capture subtle measurement errors
Solution Approach 1:
The patent introduces an intermediary theoretical model that computes expected static-pressure differentials based on aircraft flight parameters (Mach number, altitude, angle of attack, sideslip angle). This intermediary computation acts as a mediator between the raw probe measurements and the error detection logic, enabling finer-grained detection by comparing actual differentials against theoretically expected values rather than using a fixed threshold
Solution Approach 2:
The patent changes the detection parameter from a fixed differential threshold to a dynamic threshold based on multiple flight parameters. The theoretical differential ΔPsitheo is computed as a function of Mach number, altitude, angle of attack, and sideslip angle, allowing the detection system to adapt to varying flight conditions and detect subtle errors that would be masked by a static threshold
2Measurement precision
If a theoretical model with multiple parameters (Mach number, altitude, angle of attack, sideslip angle) is used to compute expected differential, then detection precision is improved, but computational complexity increases
Solution Approach 1:
The patent leverages the existing ADIRU system that already computes flight parameters (Mach number, altitude, angle of attack, sideslip angle) for other aircraft functions. By reusing these already-computed parameters, the system avoids redundant calculations and reduces the additional computational burden, making the multi-parameter theoretical model more feasible
Solution Approach 2:
The system uses the aircraft's own existing flight data and computational resources to generate the theoretical differential. The ADIRU system essentially serves itself by providing its own computed parameters to the error detection function, eliminating the need for external sensors or separate computational systems
Data Source
AI summary
To detect a measurement error in a pair of right-left static-pressure probes of an aircraft, a system including electronic circuitry is configured to obtain right/left static-pressure measurements from the pair of right-left static-pressure probes, compute a right-left static-pressure differential from the obtained measurements, determine a theoretical right-left static-pressure differential using data from other equipment of the aircraft, compare the difference between the computed right-left differential and the determined theoretical right-left differential with a predetermined threshold, and when the comparison shows that the difference between the computed right-left differential and the determined theoretical right-left differential is greater than the predetermined threshold, generate a static-pressure-measurement error warning. Thus, it is possible to finely detect any errors in static-pressure measurements.