Dual Channel Air Data System with Inertial Compensation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Modern aircraft air data systems face challenges in achieving accurate air data parameter determination, especially during sideslip conditions, due to limitations in existing multi-function probes and inertial reference units, which can lead to errors in angle of attack and pressure altitude calculations, and require redundant and dissimilar data sources for increased accuracy and reliability.
Innovation Solution
The system employs multi-function probes (MFPs) electrically coupled with an inertial reference unit (IRU) to generate independent sets of air data parameter outputs, compensating for sideslip conditions using inertial data such as lateral acceleration and yaw, and eliminates the need for additional sensors by using the IRU to determine angles of sideslip and attack, thereby increasing system dissimilarity and reducing common mode errors.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If cross-coupled pneumatic probes are used for sideslip compensation, then measurement precision is improved, but device complexity increases
Solution Approach 1:
The patent replaces the mechanical pneumatic coupling system with an electronic signal processing system. Electronic multi-function probes (MFPs) use electrical signals to transmit pressure information between probes, eliminating the need for physical pneumatic connections. This substitution maintains the sideslip compensation capability while significantly reducing system complexity, weight, and maintenance requirements.
Solution Approach 2:
The electronic MFPs are designed to perform multiple functions: measuring total pressure, static pressure, and temperature, while also providing sideslip compensation through cross-coupled signal exchange. The single probe structure integrates all sensing capabilities, eliminating the need for separate pneumatic coupling mechanisms and reducing overall system complexity.
2Reliability
If multiple independent air data sources are used, then reliability is improved, but device complexity increases
Solution Approach 1:
The patent combines multiple air data measurement functions into a single electronic MFP structure. The probe integrates total pressure ports, static pressure ports, and temperature sensors, consolidating what would traditionally require multiple separate pneumatic systems. This merging maintains measurement independence and reliability while reducing system complexity.
Solution Approach 2:
The system uses electronic signal copying and processing to create multiple independent data streams from the physical probe measurements. The MFP generates redundant air data parameters through electronic computation, providing the required independence and dissimilarity for reliability without requiring multiple physical probe systems.
3Measurement precision
If pneumatic couplings between probes are used, then measurement precision is improved, but weight increases
Solution Approach 1:
The patent replaces heavy pneumatic coupling mechanisms with lightweight electronic signal transmission systems. Electrical wires and signal processors replace the physical pneumatic connections, dramatically reducing the weight of the probe system while maintaining the sideslip compensation functionality through electronic data exchange between sensors.
4Measurement precision
If pneumatic couplings between probes are used, then measurement precision is improved, but cost increases
Solution Approach 1:
The patent replaces expensive pneumatic coupling components with more economical electronic signal processing systems. Electrical connections and digital signal processing are less costly to manufacture and install than precision pneumatic couplings, reducing overall system cost while maintaining measurement accuracy through electronic cross-coupled signal exchange.
Data Source
Figure 1
Figure 2
Figure 3
AI summary
An air data system for an aircraft (10) includes a multi-function probe (MFP) (12A, 12B, 12C) and an inertial reference unit (IRU) (14). The MFP (12A, 12B, 12C) is positioned to sense a pressure of airflow about an exterior of the aircraft (10). A first electronics channel (51) of the MFP (12A, 12B, 12C) is electrically coupled to the IRU (14) to generate air data parameter outputs based on the pressure sensed by the MFP (12A, 12B, 12C) and inertial data sensed by the IRU (14).