Integrated Air Data Test System for Simultaneous Pitot-Static Verification
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Solution Overview
Problem
Current aircraft pitot-static and ADS-B systems require separate and costly test systems, with operational challenges such as pneumatic leaks causing significant errors in altimeter readings and lack of simultaneous testing capabilities for pilot and co-pilot systems.
Innovation Solution
An integrated Air Data Test System (ADTS) with a pneumatic pump, manifold system, and signal processor that simultaneously tests both pilot and co-pilot pitot-static systems, incorporating precision pressure control and a mobile device with a graphical user interface for inputting pressure values, and optionally integrates with ADS-B for cross-validation of test results.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If separate test systems are used for pitot-static and ADS-B systems, then each system can be tested independently, but the cost and complexity of testing increases
Solution Approach 1:
The patent combines separate pitot-static test system and ADS-B test system into a single integrated test platform. The unified system uses common hardware resources (pneumatic pump, pressure sensors, control unit) to perform both types of testing, eliminating the need for multiple separate systems while maintaining independent testing capability for each system type.
Solution Approach 2:
The integrated test system is designed with multi-functionality to handle both pitot-static system testing and ADS-B system testing. The control unit can selectively execute different test protocols, and the pressure supply system serves both the pneumatic test circuit and the ADS-B transponder testing, making the system universally applicable to multiple testing requirements.
2Productivity
If pneumatic leaks occur in the test system, then testing can continue, but significant errors occur in altimeter readings
Solution Approach 1:
The test system incorporates pressure sensors that continuously monitor the pneumatic circuit for leaks. When a leak is detected through pressure deviation from expected values, the control unit receives feedback and can either alert the operator or automatically adjust testing parameters to compensate, preventing significant measurement errors while maintaining testing continuity.
Solution Approach 2:
The system performs preliminary leak detection tests before conducting actual altitude and airspeed measurements. By checking the integrity of the pneumatic circuit in advance and establishing baseline pressure values, the system cushions against the impact of potential leaks during critical measurement phases, ensuring measurement precision is maintained.
3Reliability
If pilot and co-pilot systems are tested separately, then each system receives dedicated testing attention, but simultaneous testing capability is lost
Solution Approach 1:
The test system employs dynamic switching mechanisms that allow seamless transition between testing pilot and co-pilot systems. The pneumatic circuit can be dynamically reconfigured to supply pressure to either system, and the control unit dynamically adjusts test parameters based on which system is being tested, enabling flexible simultaneous or sequential testing without compromising thoroughness.
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
The system provides precise and simultaneous testing of both pilot and co-pilot pitot-static systems, reducing errors due to leaks and ensuring accurate altitude and airspeed measurements, while also validating ADS-B system functionality, thereby enhancing operational safety and reducing testing costs.
Implementation Method 1
at least one pneumatic pump configured to generate at least one air pressure value
Implementation Method 2
a manifold system in fluid communication with the pneumatic pump and each pair of impact and static ADTS ports
Data Source
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AI summary
An Air Data Test System (ADTS) 10 for testing an aircraft pitot-static system 12, 14 including at least one pneumatic pump 100 configured to generate an air pressure, at least two pairs of impact and static ADTS ports 120a, 120b, 130a, 130b, a manifold system 140 in fluid communication with the pneumatic pump 100 and each pair of impact and static ADTS ports 120a, 120b, 130a, 130b, and a signal processor 150 operatively coupled to, and controlling, the at least one pneumatic pump 100 and the manifold system 140. The signal processor 150 is configured to issue control signals for independently and/or collectively testing each of the pilot and co-pilot pitot-static systems 12, 14. One pair of ADTS ports 120a, 120b, 130a, 130b is configured to supply air pressure to the pilot pitot-static system 12 and the other pair of ADTS ports 120a, 120b, 130a, 130b is configured to supply air pressure to the co-pilot pitot-static system 14. A mobile device 30 wirelessly communicates with the signal processor 150 to input the pressure values for testing the pilot and co-pilot pitot-static systems 12, 14.