Wing Model With Embedded Piezometer Tubes For Pressure Measurement
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Solution Overview
Problem
Traditional wing models for static aeroelasticity wind tunnel tests lack the capability for real-time pressure distribution measurement, which is crucial for accurately researching static aeroelasticity effects on high-aspect-ratio wings, such as torsion divergence and load redistribution, and do not integrate force and pressure measurement.
Innovation Solution
A wing model incorporating a composite material skin, piezometer wing ribs, embedded piezometer tubes, and piezometer wires, connected to a spar frame and lightweight filling foam, allowing for real-time pressure distribution measurement during wind tunnel tests.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If traditional wing models are used for static aeroelasticity wind tunnel tests, then the structure is simple and easy to manufacture, but the capability for real-time pressure distribution measurement is lost
Solution Approach 1:
The piezometer tubes are embedded within the wing rib structure, with the tubes nested inside the ribs and connected to the skin through piezometer holes. This nesting approach integrates the measurement function into the structural components, adding measurement capability while minimizing additional structural complexity.
Solution Approach 2:
The patent combines the force measurement function (through the wing structure) and pressure measurement function (through embedded piezometer tubes) into a single integrated model system. The piezometer tubes are merged with the wing rib structure, allowing simultaneous measurement of both forces and pressures without requiring separate independent systems.
2Measurement precision
If embedded piezometer tubes are added to the wing model, then real-time pressure distribution measurement is enabled, but the manufacturing complexity increases
Solution Approach 1:
The piezometer holes are reserved in the composite material skin during the manufacturing process, and the piezometer tubes are embedded in the wing ribs before final assembly. This preliminary preparation of holes and embedding positions simplifies the overall manufacturing process by planning the measurement system integration upfront rather than adding it as a post-processing step.
Solution Approach 2:
The piezometer tubes are selectively embedded only in specific wing rib locations where pressure measurement is required, rather than throughout the entire structure. This localized approach allows pressure measurement capability to be added only where needed, minimizing the impact on overall manufacturing complexity.
3Adaptability or versatility
If the wing model is designed for both force and pressure measurement, then comprehensive aerodynamic data is obtained, but the device complexity increases
Solution Approach 1:
The wing model structure serves multiple functions: it provides the aerodynamic surface, supports force measurement, and accommodates pressure measurement through embedded piezometer tubes. The wing ribs serve both structural support functions and as carriers for the piezometer tubes, demonstrating multi-functionality that reduces overall system complexity.
Solution Approach 2:
The patent merges the force measurement capability (inherent in the wing structure under load) with pressure measurement capability (added through embedded piezometer tubes) into a single unified measurement system. This combination allows comprehensive aerodynamic data collection without requiring separate independent measurement systems.
Data Source
AI summary
A wing model for static aeroelasticity wind tunnel test belongs to the technical field of aeroelasticity tests. In the wing model, the model steel joint and the spar frame are connected with the composite material skin. The piezometer wing ribs are arranged among the spar frame and the plurality of supporting wing ribs. The embedded piezometer tubes are arranged in the piezometer wing ribs, the lightweight filling foam is arranged among the spar frame and the plurality of supporting wing ribs. An outer surface of a frame segment formed by the lightweight filling foam, the plurality of supporting wing ribs, the piezometer wing ribs and the spar frame is covered with the composite material skin. The frame segment is assembled on the model steel joint to form the wing model for the static aeroelasticity wind tunnel test.