Aircraft Probe Embedded Electronics Removable Design
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Solution Overview
Problem
Current air data systems face challenges in detecting degraded performance and intruding into the aircraft fuselage due to their architecture, particularly with integrated probes and pneumatic connections, which complicates maintenance and conflicts with aircraft structure.
Innovation Solution
A fully integrated digital air data probe with removable and replaceable electronics, including pressure sensors and a control circuit, is embedded within a strut, eliminating the need for external transducers and minimizing fuselage intrusion by using pneumatic connections and a health monitoring circuit to sense pressures and temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Extent of automation
If integrated probes and air data computers are used, then computational and digital capabilities are provided at the air data probe, but significant intrusion into the fuselage occurs which conflicts with aircraft structure
Solution Approach 1:
The air data system is segmented into modular components: the probe assembly with embedded electronics, removable electronics assemblies, and distributed transducers. This segmentation allows computational capabilities to be distributed rather than concentrated in a single fuselage-mounted unit, reducing overall fuselage intrusion while maintaining automation.
Solution Approach 2:
The electronics assembly is nested within the probe structure itself, with the removable electronics card housed inside the probe body. This nesting eliminates the need for separate fuselage-mounted electronics boxes, providing computational capabilities while minimizing intrusion into the fuselage volume.
2Quantity of substance
If pneumatic connections are used between probes and remotely located transducers, then air data can be transmitted, but the ability to detect degraded performance is inadequate
Solution Approach 1:
The system incorporates health monitoring circuits that continuously monitor the condition of pneumatic connections, pressure sensors, and other components. This feedback mechanism detects degraded performance by comparing actual readings against expected ranges and triggers maintenance alerts, significantly improving reliability monitoring compared to traditional pneumatic-only systems.
Solution Approach 2:
Electronic sensors and health monitoring circuits act as intermediaries between the pneumatic system and the flight data system. These intermediaries convert pneumatic signals into electronic signals that can be monitored, analyzed, and used to detect degraded performance, bridging the gap between traditional pneumatic systems and modern monitoring requirements.
3Ease of repair
If integrated probes with embedded electronics are used, then maintenance is simplified, but the complexity of detecting degraded performance increases due to architecture definition
Solution Approach 1:
The embedded electronics include self-diagnostic capabilities and health monitoring circuits that automatically detect and report degraded performance conditions. This self-service approach simplifies maintenance by providing automatic fault detection and localization, reducing the need for complex manual testing procedures despite the increased electronic complexity.
Solution Approach 2:
Traditional mechanical testing and manual inspection methods are replaced with electronic health monitoring circuits and digital diagnostic capabilities. This substitution automates the detection of degraded performance, making the system electronically more complex but operationally simpler for maintenance personnel.
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 solution allows for accurate calculation of airspeed, altitude, and angle of attack without significant fuselage intrusion, simplifying maintenance and improving detection of degraded performance by embedding electronics within the probe, enhancing reliability and ease of maintenance.
Implementation Method 1
at least one pressure sensor positioned to be pneumatically connected to at least one port of the aircraft probe
Implementation Method 2
a health monitoring circuit configured to receive a sensed temperature from a temperature sensor positioned within the aircraft probe
Data Source
Figure 1
Figure 2A
Figure 2B
AI summary
An aircraft probe (12) includes a base (24), a strut (22) that extends from the base (24), at least one port (26, 28, 30), and an electronics assembly insertable into the strut (22) and removable from the strut (22). The electronics assembly includes at least one pressure sensor (42a, 42b, 42c) that is pneumatically connected to the at least one port (26, 28, 30) to sense a first pressure when in the inserted position.