Air Data Sensor Anomaly Detection Using Spectral Signal Monitoring

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Solution Overview

Problem

Existing systems fail to detect subtle errors in pressure sensors used for air data systems, particularly in multi-probe environments, leading to undetected faults that can affect flight safety.

Innovation Solution

A prognostic monitoring system that analyzes pressure sensor data using frequency, noise, and rate processing, along with comparative analysis across multiple sensors, to identify anomalies and potential failures.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If redundant sensors and basic range checking are used, then sensor failure detection capability is improved, but subtle errors remain undetected

Engineering Contradiction:
Improvesensor failure detection capabilityVSAvoiderror detection sensitivity
Core Design Contradiction:
ReliabilityVSMeasurement precision

Solution Approach 1:

The patent replaces basic mechanical threshold checking with spectral analysis (frequency domain processing) to detect sensor errors. By transforming pressure sensor signals into frequency spectra and analyzing spectral characteristics, the system can identify subtle errors that do not manifest as obvious range violations, thereby improving detection sensitivity while maintaining reliability.

Inventive Principle:
Principle #28Mechanics substitution (Replace mechanical system)

Solution Approach 2:

The patent changes the parameter space for error detection by moving from time-domain threshold checking to frequency-domain spectral analysis. This parameter transformation enables the detection of subtle sensor errors through spectral signature comparison, allowing the system to identify anomalies that would be invisible to conventional range-based monitoring.

Inventive Principle:
Principle #35Parameter changes

2Measurement precision

If advanced spectral analysis is implemented, then error detection sensitivity is improved, but system complexity increases

Engineering Contradiction:
Improveerror detection sensitivityVSAvoidprocessing system complexity
Core Design Contradiction:
Measurement precisionVSDevice complexity

Solution Approach 1:

The patent implements a multi-functional processing system where the same spectral analysis infrastructure serves multiple purposes: baseline generation, real-time error detection, and sensor identification. By creating a universal processing framework that handles various air data sensors (pitot, static, angle of attack) through common spectral analysis routines, the system achieves high detection sensitivity without proportionally increasing complexity.

Inventive Principle:
Principle #6Universality (Multi-functionality)

Solution Approach 2:

The patent performs preliminary spectral baseline generation during normal operation before errors occur. This pre-computed baseline serves as a reference for rapid error detection, allowing the system to compare current spectral signatures against historical norms without requiring complex real-time analysis of every parameter, thereby reducing ongoing processing complexity while maintaining high sensitivity.

Inventive Principle:
Principle #10Preliminary action

Data Source

PatentEP3739342B1Prognostic monitoring of complementary air data system sensors
Publication Date: 2026.01.28 ROSEMOUNT AEROSPACE INC
  • EP3739342B1 patent drawingFigure 1~2
  • EP3739342B1 patent drawingFigure 3
  • EP3739342B1 patent drawingFigure 4

AI summary

A aircraft health management system for identifying an anomalous signal from one or more air data systems (ADS) includes one or more of a frequency processor (120), configured to provide a spectral signal that is representative of a frequency content of the first ADS signal, a noise processor (124), configured to provide a noise signal that is representative of a noise level of the first ADS signal, and a rate processor (128), configured to provide a rate signal that is representative of a rate of change of the first ADS signal. The aircraft health management system also includes a comparator (132) configured to provide a differential signal between the first ADS signal and the second ADS signal, and a prognostic processor (142) configured to determine if the ADS signal is anomalous by comparing values representative of a flight condition signal, the differential signal, and the spectral, noise, and/or rate signals.