Low Profile Air Data System Using Acoustic Sensing
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Traditional aircraft air data systems rely on externally mounted Pitot probes, which increase drag and reduce survivability, and lack redundant sensing mechanisms, making them vulnerable to failures due to environmental conditions.
Innovation Solution
The integration of low-profile pneumatic sensors and acoustic sensors, including static ports and microphones, to provide redundant and dissimilar measurement sources for air data parameter outputs, reducing the impact on aerodynamics and enhancing system reliability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional externally mounted Pitot probes are used for air data sensing, then air data parameters can be measured, but drag increases and survivability is reduced
Solution Approach 1:
The patent replaces traditional mechanical Pitot probes with acoustic sensors that use sound waves to measure air data parameters. The acoustic sensors detect pressure changes and flow characteristics through acoustic signals, eliminating the need for protruding mechanical structures and thereby reducing drag while maintaining measurement capability
Solution Approach 2:
The patent introduces acoustic waves as an intermediary medium to sense air data parameters. Instead of direct mechanical contact with protruding probes, the acoustic sensors use sound wave propagation through the airflow to indirectly measure pressure, temperature, and flow characteristics, achieving measurement without harmful protrusions
2Reliability
If traditional externally mounted Pitot probes are used for air data sensing, then air data parameters can be measured, but system survivability is reduced
Solution Approach 1:
The patent replaces vulnerable mechanical Pitot probes with acoustic sensors that have no moving parts and no protruding structures. The acoustic sensors are integrated into the aircraft surface, making them resistant to damage from debris, birds, or combat conditions, thereby significantly improving system survivability
Solution Approach 2:
The patent merges the acoustic sensing elements with the aircraft skin or surface structure, eliminating separate protruding components. This integration makes the sensing system more robust and survivable by removing vulnerable external structures that could be damaged in flight or combat
3Device complexity
If single-type sensors are used for air data sensing, then system complexity is reduced, but reliability is reduced due to common-mode failures
Solution Approach 1:
The patent changes the measurement parameter domain from purely pneumatic/mechanical to acoustic. By measuring the same air data parameters (pressure, temperature, flow) through acoustic wave propagation characteristics rather than direct pneumatic contact, the system achieves dissimilar sensing that prevents common-mode failures while maintaining measurement accuracy
Solution Approach 2:
The patent makes the acoustic sensor system universal by enabling it to measure multiple air data parameters (static pressure, dynamic pressure, temperature, flow angle) through a single acoustic measurement platform. This multi-functionality provides redundant sensing capability 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 configuration allows for robust and flush or semi-flush air data systems that determine parameters like angle of attack, sideslip, airspeed, and temperature, reducing the risk of common-mode failures and minimizing drag, thereby improving aircraft performance and survivability.
Implementation Method 1
an acoustic sensor system to sense acoustic signals as second sensed data
Implementation Method 2
a low profile pneumatic sensor system to sense one or more of a total (or pitot) pressure, a static pressure, an angle of attack, and an angle of sideslip
Data Source
Figure 1
Figure 2A~2B
Figure 3A
AI summary
A system and method for an aircraft (50) includes a low profile pneumatic sensing system and an acoustic sensing system. The low profile pneumatic sensing system includes a pneumatic sensor (30; 52a, 52b) positioned to sense first sensed data of an airflow about an exterior of the aircraft (50) and does not extend beyond a boundary layer of the aircraft (50). The first sensed data is used to determine first air data parameters. The acoustic sensing system is configured to emit acoustic signals about the exterior of the aircraft (50) and sense the acoustic signals as second sensed data. The second sensed data is used to determine second air data parameters.