Aircraft Sensor System for Air Velocity Measurement
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Solution Overview
Problem
Current methods for determining air velocities on aircraft, such as pitot tubes, lack redundancy and accuracy, particularly in measuring air velocities past the aircraft surface, and are susceptible to interference from engine excitations and structural behavior.
Innovation Solution
A sensor system comprising sensors attached or embedded in the aircraft structure to detect local pressure fluctuations, generating signals that are processed by an evaluation device to determine air velocities, potentially using multiple sensors and databases to correlate structural responses with air velocities, and accounting for flow separation and eddy velocities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If pitot tubes are used to measure air velocity, then air velocity can be determined, but the measurement lacks redundancy and accuracy and is susceptible to interference
Solution Approach 1:
The aircraft structure is divided into multiple sensor locations where several sensors are distributed across different structural elements. Each sensor independently measures local pressure fluctuations, providing multiple data sources that segment the measurement task and eliminate single-point failure risks.
Solution Approach 2:
The sensors serve dual functions: they measure local pressure fluctuations in the boundary layer for air velocity determination while simultaneously monitoring structural responses. This multi-functionality integrates velocity measurement with structural health monitoring, enhancing both accuracy and redundancy.
2Reliability
If sensors are attached to the aircraft structure to detect pressure fluctuations, then redundant measurements are obtained, but interference from engine excitations and structural behavior must be accounted for
Solution Approach 1:
The evaluation device extracts and isolates the signal components related to boundary layer pressure fluctuations from those caused by engine excitations and structural behavior. By separating the harmful interference signals from the useful measurement signals, the system maintains redundancy while eliminating interference effects.
Solution Approach 2:
The system continuously monitors structural responses and uses this feedback to adjust and refine the air velocity determination. By incorporating real-time structural behavior data into the evaluation process, the system compensates for interference effects and maintains accurate measurements despite engine excitations.
3Measurement precision
If multiple sensors are used to improve accuracy and redundancy, then measurement precision increases, but device complexity increases
Solution Approach 1:
Multiple sensors are merged into a unified evaluation system that processes all sensor signals simultaneously. The evaluation device combines data from all sensor locations and applies correlation analysis to determine air velocity, achieving high precision through integrated processing rather than separate independent measurements.
Solution Approach 2:
The system uses identical sensor types and evaluation algorithms across multiple locations, creating replicated measurement units. This copying approach standardizes the measurement process, simplifies calibration and maintenance, and enables straightforward scalability without proportionally increasing system complexity.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach provides a redundant and accurate method for determining air velocities, reducing interference and enhancing measurement precision by correlating structural responses with air velocities, and can replace conventional pitot tubes.
Implementation Method 1
The first sensor is configured for determining a first response of the structure to a first local pressure fluctuation of a boundary layer of the air flowing past the aircraft
Implementation Method 2
The first response of the structure to a first local pressure fluctuation of a boundary layer of the air flowing past the aircraft may refer to a reaction of the structure to said local pressure fluctuation. For example, the first response may be a vibration or oscillation of the structure
Data Source
Figure 1A~3C
Figure 4A~4B
Figure 5~6
AI summary
The invention relates to a sensor system for an aircraft (500) for determining the air velocity of air flowing past the aircraft. The sensor system comprises a first sensor (101) and an evaluation device (102). The first sensor is configured for being arranged at the structure (501) of the aircraft and determines a first response of the structure to a first local pressure fluctuation of a boundary layer of the air flowing past the aircraft. Furthermore, the first sensor generates a first signal on the basis of the determined first response of the structure. The evaluation device is configured for processing said first signal and for determining the actual air velocity on the basis of the first signal. The invention also relates to an aircraft, a method, a program element and a computer-readable medium.