Aircraft Probe System Integrating Optical Window for Redundant Measurement
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Solution Overview
Problem
Existing aircraft probe systems are prone to failures due to external factors like dust, insects, lightning strikes, and mechanical impacts, leading to erroneous measurements, and existing redundant solutions either replicate the same failure risks or require costly certification changes.
Innovation Solution
A probe system with a base integrated into the aircraft cockpit, featuring regularly spaced static pressure taps and an optical window transparent to laser radiation, allowing for additional primary reference measurements without altering the aircraft skin or requiring recertification, and incorporating a deicing system to prevent ice obstruction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If protruding probes are used for measuring primary references, then measurements can be obtained, but the probes are exposed to meteorological or mechanical factors that alter their operation and cause failures
Solution Approach 1:
The patent combines multiple probe functions (static pressure measurement and laser radiation transmission) into a single integrated base structure. The base serves both as a pressure measurement platform with multiple taps and as a mounting structure for the optical window, reducing the number of separate protruding elements exposed to harmful factors.
Solution Approach 2:
The optical window acts as an intermediary element that allows laser radiation to pass through the base while maintaining the integrity of the pressure measurement system. It enables the laser anemometer to measure airspeed without requiring additional protruding probes that would be vulnerable to damage.
2Reliability
If redundant probes are added to offset failure risks, then measurement reliability improves, but the redundant probes are also of protruding type and have the same failure risks
Solution Approach 1:
The base is designed as a multifunctional structure that simultaneously serves as a static pressure probe with multiple taps and as a mounting platform for optical components. This universal structure provides redundant measurement capabilities (both pressure and laser-based airspeed) without adding separate vulnerable protruding probes.
Solution Approach 2:
The patent replaces traditional mechanical protruding probes with a hybrid system where a static pressure probe is combined with a laser anemometer that transmits radiation through an optical window. This substitution reduces the number of mechanical protruding elements that are susceptible to physical damage from birds, ice, and mechanical impacts.
3Reliability
If the skin of the aircraft is altered to accommodate additional probes, then redundant measurement means are obtained, but certification requirements are triggered requiring costly recertification
Solution Approach 1:
The patent merges the additional probe functionality into the existing base structure rather than creating separate modifications to the aircraft skin. The integrated base with multiple static pressure taps and optical window provides redundant measurements without requiring separate cutouts or modifications in the aircraft fuselage.
Solution Approach 2:
The base structure is designed to perform multiple functions: static pressure measurement through multiple taps, mounting for the optical window, and structural support. This universal design allows the addition of laser anemometer capability without requiring separate structural modifications or triggering recertification processes.
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 solution provides reliable, redundant primary reference measurements that minimize disruption to the aircraft's pressure and flow fields, reducing failure risks and eliminating the need for costly certification changes, while maintaining the aircraft's structural integrity and operational uptime.
Implementation Method 1
an optical window transparent to laser radiation and inserted into the base
Implementation Method 2
laser anemometer and arranged across from the optical window of the probe system
Implementation Method 3
a plurality of regularly spaced static pressure taps, arranged through the base and designed to be connected to means for measuring the pressure
Implementation Method 4
incorporating a deicing system to prevent ice obstruction
Data Source
AI summary
A probe system, mixed primary reference probe for an aircraft, associated aircraft and measuring method are disclosed. In one aspect, the probe system includes a base designed to be fastened on the cockpit of an aircraft, a plurality of regularly spaced static pressure taps, arranged through the base and designed to be connected to a pressure measurement device. The system includes at least one optical window transparent to laser radiation and inserted into the base.