Passive Flow Generator for Aircraft Gas Sampling
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Solution Overview
Problem
Current aircraft measurement tools require orientation with the main gas flow and high-speed thrust to produce accurate measurements, limiting their application, especially for slow-moving or hovering aircraft, which do not generate sufficient forward velocity for forward-facing devices to function effectively.
Innovation Solution
A low-profile, non-powered passive flow generator system that converts propelling thrust into a continuous flow, allowing gas samples to be drawn into a sample chamber without the need for orientation or high-speed motion, using a pressure-lowering device based on the Bernoulli principle to create a low-pressure source independent of aircraft motion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional electric vacuum pump systems are used to generate continuous flow, then reliable gas sample measurements can be obtained, but the weight, size, and power requirements increase significantly
Solution Approach 1:
The system uses the aircraft's own propelling thrust to generate the flow needed for measurements. The pressure-lowering device is positioned in the propeller slipstream, where it utilizes the existing high-velocity air flow to create a low-pressure zone that draws gas samples through the measurement system, eliminating the need for separate powered pump systems
Solution Approach 2:
The invention employs a pressure-lowering device based on Bernoulli's principle that converts kinetic energy from the propeller-driven air flow into pressure differential. The device creates a low-pressure zone that passively draws gas samples through the measurement system without requiring mechanical pumping, thereby reducing weight and power requirements
2Measurement precision
If forward-facing devices are used to generate sampling flow, then accurate measurements can be obtained at high speeds, but the system becomes ineffective for slow-moving or hovering aircraft
Solution Approach 1:
The system adapts to different aircraft motion states by utilizing the propeller's rotational motion rather than relying on forward velocity. The pressure-lowering device is positioned to intercept the turbulent flow generated by the propeller blades during rotation, creating a consistent low-pressure zone regardless of whether the aircraft is moving forward, hovering, or moving laterally
Solution Approach 2:
The invention introduces the propeller slipstream as an intermediary flow source. Instead of directly relying on the aircraft's forward motion or using complex active flow generation systems, the system uses the propeller-generated air flow as an intermediate medium to create the pressure differential needed for sample acquisition, thereby simplifying the system and improving adaptability
3Ease of operation
If passive flow systems relying on aircraft forward motion are used, then device orientation with main flow is not required, but high-speed thrust is necessary to generate sufficient flow
Solution Approach 1:
The system changes the parameter used for flow generation from aircraft forward velocity to propeller rotational velocity. The pressure-lowering device is positioned in the propeller slipstream where the high-velocity turbulent flow generated by blade rotation creates sufficient pressure differential for sample acquisition, eliminating the need for high-speed forward motion while maintaining ease of operation
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
Enables reliable and repeatable gas sample measurements across sensors, improving response time and reducing weight, size, and power requirements, suitable for various applications including UAS, petrochemical, and environmental monitoring, without the limitations of traditional electric vacuum pump systems or forward-facing devices.
Implementation Method 1
using a pressure-lowering device based on the Bernoulli principle to create a low-pressure source independent of aircraft motion
Data Source
AI summary
A system for converting propelling thrust to produce a continuous flow is provided. The system can be integrated and/or retrofitted to the body of an aircraft. The system includes a pressure-lowering device and a sample chamber. The pressure-lowering device is used produce a low-pressure, continuous flow from a high-velocity propelling thrust source. Moreover, the pressure-lowering device is a passive flow generator that does not require a power source in order to produce a continuous flow from a propelling thrust. The design of the pressure-lowering device produces a flow rate that is independent of the aircraft motion. The sample chamber is used to measure and analyze ambient gases which are pulled through the sample chamber by the pressure-lowering device, as a result of the high-velocity air stream produced by the propelling thrust source.